* GB785143 (A)

Description: GB785143 (A) ? 1957-10-23

An automatic control for the air circulating fans of liquid-coolantradiators in internal combustion engines

Description of GB785143 (A)

PATENT R Pi',Tcl Tn, A TT N 9 P Date of Application and No 22826/55. A q r' Complete Specification P Index at acceptance: C Iass 7 ( 2), B 2 C( 3 A 1: 7 H: 9). International Classification: -F 02 b Ail, m %A an,ta,, 785143 filing Complete Specification Aug 8, 1955. ublished Oct 23, 1957 COMPLETE SPECIFICATION An Automatic Control for the Air Circulating Fansof LiquidCoolant Radiators in Internal Combustion 'Engines We, WILLI FRANK of 26, Albrechtstrasse, Ludwigsburg/Wurttemberg and GE Rii ARD CAROLI, of 49, Klopstokstrasse, Stuttgart-W, Germany, both German Subjects, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement: - The present invention relates to a device for automatically controlling, in conformity with the requirements of an internal combustion engine liquid-coolant radiator, the air circulated thereover by a fan It is frequently impossible, for instance for reasons of space, to drive the radiator fan of an internal combustion engine directly from the engine In such cases it is usual to arrange for the internal combustion engine to drive an electric generator and to use the current generated by the same for the purpose of driving the fan or fans Apart from the unavoidable loss in power which such an arrangement entails, the automatic control of the fan to vary the rate at which air is circulated over the radiator calls at least for the provision of cumbersome and complicated arrangements. Electric motors with change-over poles have been used to give at least a limited measure of control, and it has also been proposed to drive the fan by means of synchronous motors and to use a synchronous

generator to control the motor speed in ratio with the engine speed. However, in such an arrangement the fan velocity is strictly proportional to the engine speed and this is not entirely in accord with actual requirements. Hydrokinetic hydraulic transmissions have also been used with a view to controlling the circulation of air but they entail a considerable wastage in power especially as such transmissions themselves require to be cooled. It is the object of the present invention to provide for the automatic control, for a liquid coolant radiator of an internal combustion engine, of the rate at which air is circulated over the radiator so as to maihtain, under varylPrice 3 s 6 d l ing operating conditions of the engine, an air circulation rate adapted to the rate at which heat is conveyed to the radiator, by means of 50 a device -that does not suffer from the disadyantages inherent in the known types of arrangement and also ensures that the power consumed is efficiently utilised. According to the present invention this is 55 achieved by driving the radiator fan by means of a hydrostatic hydraulic motor the speed of which can be controlled by a hydrostatic liquid pump which delivers hydraulic fluid to the motor at an infinitely variable rate which is 60 controlled thermostatically' in dependence on the temperature of the liquid coolant The arrangement may be such -that the output -of the liquid pump, is determined by variation of -the speed at which the pump is driven and/or 65 by a controlling device which acts in dependence upon the temperature of the coolant by varying, for instance in the case of direct drive from the engine, the displacement volume of the pump or alternatively or additionally the 70 rate at which fluid is delivered to the hydraulic motor may be controlled in dependence upon the liquid-coolant temperature by means of a controllable by-pass Such an arrangement will have a high efficiency and at the same time 75 allow the speed of the fan to be infinitely varied in conformity with the amount of air required for cooling Both the liquid pump and the hydraulic motor can be adapted to the needs of existing circumstances For example, 80 the liquid pump, may be directly coupled with the shaft of the internal combustion engine and it may form a structural unit with the hydraulic motor On the other hand, the liquid pump may be structurally separate from the 85 hydraulic motor and connected with the same only through the pressure lines. The drawing illustrates an exemplary form of construction in order that the invention, and the manner wherein the same is to be per 90 formed, may be the more readily understood. In the drawing, the internal combustion engine 1 transmits torque to

the hydrostatic liquid pump 2 which is connected by means Die O 4 Ei "-1, ' ' J t ' 1', 2 785,143 of pressure pipes 3 with the hydrostatic the output of the hydraulic pump is controlled hydraulic motor 4 of the fan 5 for the liquid by variation of the speed at which the pump coolant radiator -6 The pipe line 7 which is driven and/or by a controlling device which 35 carries -thei c 6-lmit 2 finy;'mcluide-a themrnostat regulates for instance the displacement volume 8 which acts directly or through a pipe-line of the-pump in dependence upon the tempera9 on a controlling device 10, which, for ture of the liquid coolant.

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* GB785144 (A)

Description: GB785144 (A) ? 1957-10-23

Improvements in or relating to aircraft arresting gear

Description of GB785144 (A)

p_ m 'Th PATENT SPECIFICATION Date of Application and filing Complete Specification: Aug IS, 1955. 785,144 No 23431/55. Application made in United States of America on Jan 13, 1955. Complete Specification Published: Oct 23, 1957. Index at Acceptance:-Class 4, G 7. International Classification:-B 64 f. COMPLETE SPECIFICATION Improvements in or relating to Aircraft Arresting Gear We, ACME PRECISION PRODUCTS, Inc, a corporation organised and existing under the laws of the State of Ohio, United States of America, of 215 North

Findlay Street, Dayton, County of Montgomery, State of Ohio, United States of America, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:- The invention relates to aircraft arresting gears and more particularly to aircraft arresting gears designed to absorb the kinetic energy of jet propelled aircraft. The aircraft arresting gears with which we are familiar are designed for use principally on aircraft carriers and are comprised essentially of a series of arresting cables raised at the proper time to engage either a lateral hook or the forward and central parts of the aircraft and then to pick up a drag attached to both ends of the arresting cables (weights of different -kinds such as sand bags, or to engage air compressor devices or to actuate spring loaded cables and the like) which gradually increases the retarding force on the forward speed of the aircraft until its forward motion is stopped. The problem of deceleration of jet propelled aircraft on aircraft carriers is relatively simple since the runway (flight deck of carrier) is narrow, about eighty feet wide At present, several lengths of material such as woven nylon are strung in the form of a net between two stanchions which may be raised from the flight deck and will require little or no intermediate support A more recent type of aircraft arresting gear utilizes an actuator strap or cable of woven nylon raised about three or four feet above the runway when in position to be employed This actuator strap is attached to an arresting cable of wire rope or the like by means of a plurality of lifter straps The arresting cable is attached at either end to a drag When the aircraft engages the woven nylon actuator strap, it stretches and ultimately lPrice 3 s 6 d l breaks This action raises the arresting cable by means of the lifter straps into the air Since, at the point of impact, the actuator strap is stretched the furthest, the lift exerted on the arresting cable will be greatest at this point 50 Hence, an arc or loop is formed in the arresting cable at this point It is this arc or loop which is designed to engage the landing gear of the aircraft. It has been found in practice that the speeds 55 of jet propelled aircraft using land runways requiring the emergency use of the aircraft arresting gear such as the invention range from thirty miles per hour to one hundred ninety miles per hour which is frequently 60 encountered during an abortive take-off. Since the transverse widths of the present land runways vary from one hundred fifty feet to four hundred feet, many problems not present in carrier aircraft arresting gears must 65 be faced and solved before a

gear is feasible for use on land runways. The main problem present in designing an aircraft arresting gear for any runway is to provide a means to absorb the kinetic energy of 70 the moving aircraft without causing substantial damage to the structural parts or to the skin of the aircraft The speeds that are likely to be encountered make it impracticable to employ the well known dependent hook and cable 75 arrangement The woven nylon net also has proven unsatisfactory for use on land runways because of the problems involved as will appear from this specification The most desirable method to stop a moving aircraft is to provide 80 some means to engage the running gear of the swiftly moving aircraft to a gradually increasing drag. An aircraft arresting gear that is adapted to normally lay on the runway and which can be 85 raised instantly to stop an aircraft is highly desirable since only emergency use is contemplated The means of raising such an aircraft arresting gear are well known For that reason, the means of raising our arresting 9 Q gear herein described will not be set forth except in general terms since it forms no part of our invention. However, the aircraft arresting gears with which we are familiar employing an arresting cable flung into the air to engage an aircraft have proven unsatisfactory from the standpoint of uniformity of performance We have found that attaching the arresting cable directly to the drag produces a very erratic performance. Sometimes the arresting cable is flung into the air in the form of an arc or loop outside the point of engagement of the aircraft with the barrier and thus entangles the aircraft This causes the arresting cable to engage parts of the aircraft not stressed for the forces exerted with the result that substantial damage is done to the skin and frame of the aircraft If the arc or loop of the arresting cable is not sufficiently high at the proper time to engage either the main landing gear, the bomb or rocket launcher racks, or the in-board fuel tank hangers, the arresting gear will fail and the aircraft will not be engaged to the drag If there are no bomb or rocket launcher racks, or inboard fuel tank hangers on the aircraft, the arc or loop in the arresting cable must be sufficiently high to engage the main landing gear struts over the main landing gear wheels. The arc or loop of this type of arresting cable must be raised into the air after the nose wheel of the aircraft has passed over the arresting cable to a height of approximately three feet while the aircraft moves forward only approximately six feet if the arresting cable is to engage bomb or rocket launcher racks, or in-board fuel tank hangers The arc or loop of the arresting cable must also be approximately two and onehalf feet to three feet high if it is to

engage the main landing gear struts which are approximately nineteen and one-half feet in the rear of the nose wheel, depending upon the type of aircraft The speed of the aircraft will vary from thirty miles per hour to one hundred and ninety miles per hour as set forth above. Hence, the performance of the arresting cable takes place in a very short space of time. The invention is directed to controlling the performance of the arc or loop in the arresting cable as it is flung into the air to engage the aircraft In the practice of the invention, we employ, as far as possible, the present arrangement of this type of aircraft arresting gear. Thus, we employ the usual actuator strap and lifter straps to snap or raise the arresting cable into position to engage the aircraft However, we have-discovered a means of controlling the performance of the arc or loop developed in the arresting cable upon an aircraft crashing the arresting gear. In order to provide an aircraft arresting gear that is uniform for any width runway, we have found it is necessary that the actuator strap be supported at substantially the same height above the runway We provide internmediate supports for installation approximately every fifty feet of transverse distance so that the actuator strap will not sag more than approximately two inches between stanchions These intermediate stanchions are so constructed that 70 they do not endanger the aircraft when relieved of their supporting function, even if hit by the aircraft. As set forth above the problem encountered in using arresting cables of the kind herein 75 described is that the nose wheel of the aircraft must pass over the arresting cable which must then be flung into a wave or loop sufficiently high at the point where the nose wheel travelled over it to engage one of the two main points 80 which are braced to hold such a cable without damage to the aircraft These points are the main landing gear struts or the bomb hangers which may also be employed to hold fuel tanks or rocket launchers The loop has to be ap 85 proximately three to four feet high to pass over these fuel tanks or bombs and engage the hangers, while the aircraft has travelled only a distance of approximately six feet If the main landing gear struts are to be engaged, then the 90 loop must be higher than two and one-half feet but less than five feet after the aircraft has travelled about fifteen to nineteen and one-half feet from the point where the nose wheel passed over the arresting cable, depend 95 ing upon the type of aircraft Accordingly, it is easy to understand why an uncontrolled wave engendered into the arresting cable produces erratic results. In practice we prefer to employ a 1 ' wire 100 rope as an arresting

cable Of course this cable size may be increased for greater loads The arresting cable is snapped into the air by the lifter straps beingstretchedwhenthe nose wheel strut of the aircraft engages the actuator strap 105 and carries it forward The manner of accomplishing this snapping is very important to the performance of the arresting cable The lifter straps, which are attached to both the actuator strap and the runway, are folded over the cable 110 intermediate their ends and secured by sewing or by snap fasteners and formed into a loop enfolding the cable Upon the actuator strap being stretched by the nose wheel strut, the arresting cable is freed and snapped into the 115 air in the form of a loop or wave just before the lifter strap becomes unfastened from the runway The loop is formed in the arresting cable at the point of engagement and it is this loop which engages the aircraft To form this 120 loop we provide excess cable that is lying on the runway In other words, if the runway is one hundred fifty feet wide, we provide that the cable will be approximately one hundred fifty-three feet long This excess cable forms 125 the loop which engages the aircraft and then the cable is carried along, picking up the drag as the aircraft travels down the runway Obviously, the actuator strap must be permitted to break at a predetermined point This is 130 785,-144 satisfactorily and is less expensive; Our: means of accomplishing -the reflection as above set forth is to provide that the arresting cable is connected to the side stanchions in such a manner that just after the 70 arresting cable: is raised by the lifter straps and before the arresting cable picks up the drag; it is jerked sharply This jerk causes substantially all of the tension wave to be reflected along: the cable toward the point of 75 impact Thus, if the point of impact is roughly at the center of:the actuator -strap, the reflected tension wave acts to increase the arc or loop in the arresting cable Even if the point of impact is off center, we have found the re 80 flected tension wave does not adversely affect the size or performance of the arc or loop in the arresting cable. The principal object of the invention is to provide an aircraft arresting gear for use on 85 runways of any width, that will absorb the kinetic energy, or speed, of a jet propelled aircraft. Another object of the invention is to provide that the arresting cable of an aircraft arresting 90 gear will uniformly engage either the bomb or rocket launcher racks, the fuel tank supports; or the main landing gear struts, of a jet propelled aircraft without doing substantial damage 95 Another object of the invention is to provide an aircraft arresting gear which will absorb the speed of jet propelled aircraft from thirty to one hundred ninety miles per hour without adjustment, 100 Another object of the invention is to provide an aircraft arresting gear actuator strap stanchion or support that will

disassemble upon the actuator strap being engaged by a moving aircraft by the stanchion being triggered to 105 release engagement. Another object of the invention is to control the reflected tension wave created in the arresting cable of an aircraft arresting gear when it is snapped into position to engage a 110 moving aircraft, thereby permitting a loop to develop in the arresting cable which will rise the correct distance to uniformly engage the proper portions of an aircraft Our means of accomplishing the foregoing 115 objects may be more readily apprehended by having reference to the drawings which are appended hereto and are made a part hereof in which:Figure 1 is a perspective view somewhat 120 diagrammatic, showing an arresting gear made in accordance with our invention about to be engaged by an aircraft. Fig 2 is a perspective view similar to Fig 1 after engagement of the arresting gear by an 125 aircraft showing the beginning' of the loop formed in arresting cable. Fig 3 is a perspective view of the actuator: strap and arresting cable with the arresting gear in erected position with two intermediate 1-30 usually accomplished by means of a shear pin arrangement which parts the actuator strap upon a predetermined certain pressure being exerted on it We have found in practice that __ a shear pin in each end of the actuator strap adapted to shear when 3,000 pounds pressure is applied to it gives sufficient snap to the lifter straps at the point of engagement to form the desired loop in the arresting cable. ID We have also found that a drag formed by anchor chains six hundred feet long attached to each end of the arresting cable performs very satisfactorily As stated above, by long experimentation, we have found that unless some method to control the size and performance of the loop of the arresting cable is developed, the uncontrolled loop performs so erratically that no dependence can be placed upon the results When it is realized each aircraft saved by the use of an aircraft arresting gear represents the saving of the life of the pilot as well as the saving of an aircraft valued at many hundreds of thousands of dollars, the desirability of developing an arresting cable which will uniformly engage the proper parts of an aircraft regardless of the speed of the aircraft (within certain limits) is evident After considerable study of the problem, we discovered that a transverse wave travelling at approximately two hundred feet per second and a partially reflected tension wave travelling approximately ten thousand feet per second were combining to act on the loop of the arresting cable after it was snapped into the air to engage the aircraft These uncontrolled waves prevented any uniformity of action in the arc or loop of the arresting cable being achieved The loop,

after it was released, into the air, frequently became catenary in shape, softening to a circle and then running back into an ellipse, all in the short space of time We then endeavored to separate the partially reflected tension wave in its effect from the transverse wave We discovered that the tension wave would tend to bring the ends of the arresting cable, if free to move, directly inwardly toward the point of impact However, when the arresting cable was attached to the drag and the stanchion, the tension wave was reflected into several directions in varying strengths We discovered that since the proportion of reflection of the tension wave back toward the point of impact along the arresting cable depended upon the degree of dissipation of the tension wave by the drag and the stanchion, we could control the reflection of the tension wave, and hence control the action of the arc or loop in the arresting cable, if we could direct substantially all of the tension wave back toward the point of impact Of course, if we could completely absorb all the tension wave, we could also control the performance of the arc or loop in the arresting cable However; we have found that reflecting substantially all of the tension wave works: i 85,144 stanchions in place Fig 4 is a detailed view of a shear pin arrangement attached to one end of the actuator strap. Fig 5 is a detailed view of one end of the arresting cable with the tension wave control in position. Fig 6 is a detailed view of the lifter strap engagement of the arresting cable: Fig 7 is a detail view of our intermediate stanchion. Fig 8 is a schematic drawing of the progress of the unsnapping of a lifter strap as an aircraft engages the actuator strap. Fig 9 is a detail view, partly in section of a portion of our intermediate stanchion. Fig 10 is a detail view of Figure 2. Fig 11 is a schematic view of our intermediate stanchion in a "down" position. Similar numerals refer to similar parts throughout the specification. As shown in the drawings, we provide an actuator strap 2 for the aircraft arresting gear indicated generally as 1, which is preferably made of woven nylon approximately one and three-quarters inches wide and three-sixteenths of an inch thick with a 10,000 pound test strength For safety, we provide dual straps 2 but we shall refer to one only One end of this -strap 2 is attached through a shear pin assembly 4 to a cable 6 which is held by the end stanchion 8 Since each end is a duplicate, we have described only one The stanchion 8 is adapted to be raised into a vertical position when the arresting gear is required by means of bungee cord 9 or in any suitable manner As

shown in Fig 4, the shear pin assembly 4 is comprised of a yoke 10 riveted to a finger 11 and pivotedly attached by means of a bolt 12 to a bifurcated tongue 14 which is swedged to the cable 6, which is attached to the stanchion 8 While we have described one shear pin assembly 4 for the actuator strap 2, it is understood there are two of these, one at each end A shear pin 16 -which will shear at 3,000 pounds pull on the actuator strap 2 is inserted in the hole 18 in the pin 17 which is attached by means of a bolt 20 to the bottom 13 of the yoke 10 as shown. We provide a plurality of lifter straps 22 which also may be made of woven nylon, each of which may be attached to the actuator strap. 2 by loops 24 around the actuator strap 2 The length of the lifter strap 22 must be as nearly exact in its measurements as possible. For safety, we provide two straps 22 for each lifter, but for convenience we shall describe only one The straps 22 are formed into restraining loops 24 provided when the snap fasteners 26 are snapped together and are folded over an arresting cable 30 as shown in Fig 6. When the fasteners 26 are snapped together the strap 22 is firmly but detachably fastened to the arresting cable 30 Of course, the straps -65 22 may be lightly sewed together instead of employing the snap fasteners -26 if desired. We provide inertia straps 27 with snap fasteners 29 to insure the restraining loops 24 against premature release We provide that the snap fasteners 26 will open on a pull of 90 to 100 70 pounds It will be noted that the lower end 31 of the lifter strap 22 is firmly buttoned to an anchor plate 32 set in the runway by means of a grommet 34 However, this grommet 34 will resist separation far beyond the release 75 load of the actuator strap fasteners 26 because the direction of pull on the grommet 34 effects a shearing action rather than a pulling force. We have provided that the grommet 34 will separate upon a pull of approximately 250 80 pounds. It will thus be clear that when the actuator strap 2 is engaged by the nose wheel strut of an aircraft as shown in Figs 2 and 10 and pulled forwardly with enormous force, first the lifter 85 strap 22 nearest the nose wheel will unfasten at the loop 24 surrounding the arresting cable and then upon further stretching of the actuator strap 2, the lifter straps 22 straighten out and snap the cable into the air upon the 90 runway grommet 34 being pulled out This is schematically shown in Fig 8 Referring to Fig 10, it will be clear that the lifter straps A, B, C, D, E and F, have separated but that the lifter straps X and Y have not yet been 95 forced open. As set forth above, the actuator strap 2 should not be permitted to sag more than approximately two inches because the function of the

actuator strap 2, as its name implies, is to 100 actuate the cable 30 In order to accomplish this purpose, the straps 22 should be in a position to uniformly affect the cable 30 wherever the actuator strap 2 is engaged. Consequently, we provide that an intermediate 105 stanchion indicated generally as 40 is positioned approximately every fify feet of transverse runway In this manner, a runway of any width may be covered by our arresting gear without adjustment by merely inserting the 110 stanchion 40 as set forth above The stanchion comprises a lower bar 42 which is hinged to a base plate 44 set into the runway As shown in Fig 9 the lower bar 42 is hollow at its upper end 46 to receive a tube 48 The lower 115 end 62 of the tube 48 rests in the end 46 of the lower bar 42 and is inserted at its upper end into a cap 50 attached to the actuator strap 2 as shown in Figs 1 and 7. A key 52 is mounted by a pivot 53 on a 120 flange 54 extending outwardly from the extension 43 of the lower bar 42 substantially as shown in Figure 9 The key 52 has an ear 56 extending upwardly and a bifurcated finger 58 The tube 48 has a slot 60 adjacent its 125 lower end 62 into which the finger 58 of the key 52 falls when the tube 48 is inserted into the bar 42 As shown in Figs 3, 7, 9 and 11, a bungee cord 64 is attached to a base plate 66 in the runway and is slipped around the ear 56 130 -4 785,144 785,144 5 of the key 52 It will be noted that the bungee cord 64 rests just below the plane of the pivot 53 and will normally tend to keep the key 52 into a locked position A trigger wire 68 is attached to the cap 50 and runs somewhat parallel to the tube 48 and around the bifurcation in the finger 58 just behind the bungee cord 64 The bungee cord 64 keeps the lower bar 42 in an upright position until the actuator strap 2 is engaged by an aircraft At this point, the cap 50 which is attached to the actuator strap 2 is lifted from its position and causes the trigger wire 68 attached to it to pull upwardly on the finger 58 of the key 52 As soon as the finger 58 is raised sufficiently that the bungee cord 64 is above the plane of the pivot 53 due to the raising of the finger 58 caused by the trigger wire 68 pulling thereon, the bungee cord 64 pulls the key 52 completely up and releases the tube 48 which falls along the runway Thus the intermediate stanchion 40 disassembles and cannot injure the aircraft even if the aircraft hits it during its forward movement A recess may be formed in the runway for the intermediate stanchion 40 when it is in a downward position as shown in Fig 3. The bungee cord 64 will be forced to stretch further when the arresting gear is in a "down" position as shown in Fig 11 but it-will be in substantially the same plane as the lower bar 42 and hence will not cause it to raise until the entire arresting gear is raised approximately 30 The lower bar 42 is curved as shown to hold the

arresting cable under it when in a downward position as shown in Fig 11. As shown in the drawings we provide an arresting cable 30 which is positioned substantially parallel to the actuator strap 2 but is laid upon the runway In practice we have found a '," wire rope very satisfactory As shown in Figs 2 and 10, the arresting cable 30 is snapped into the air by the lifter straps 22 when they become "sprung" i e unsevered or -45 unsnapped at the point of engagement Obviously, not all of the lifter straps will be C"sprung" at the same time nor with the same degree of force Hence, as shown in Fig 10, a curve or loop 71 is developed into the arresting cable 30 This loop 71 will have its greatest arc directly behind the nose wheel strut. Thus the dimensional geometry of the lifter straps is very important in timing the lifting of the arresting cable 30 For this reason near -55 uniformity is highly desirable When the arresting cable 30 is snapped into the air, the tension wave created in it tends to draw the ends 70 and 72 of the cable directly towards each other at the center of the point of engagement If the ends 70 and 72 of the arresting cable were unattached, the result would be a loose V formed by the arresting cable behind the main landing gear struts or other point of engagement as the aircraft travelled down the runway with the ends 70 and 72 approaching each other If the ends of the arresting cable are attached to the drag only (in this case, anchor chains) the ends of the cable would jerk the loose chain links in a perpendicular direction to the path of travel of the aircraft 70 thereby increasing the amount of the cable in the loop 71 and distorting it We have seen this happen and have found that if the reflected tension wave can be controlled, the transverse wave unites into forming a uniform loop of the 75 desired characteristics Accordingly, we provide a pair of tension control cables 74 and 78 attached to each end 70 and 72 of the cable 30. One set of these is shown in Fig 5 Since they are identical, we shall describe only one A 80 small cable 74 is attached firmly to the stanchion 8 near the base, approximately one foot above the runway, and extends to a shear pin device 76 which is similar to the shear pin 4 except that it will shear at 4,000 pounds Another 85 cable 78 of the same dimensions as the cable 74 extends from the shear pin device 76 to the arresting cable 30 and may be attached by member 78 ' as shown The end of the arresting cable 30 may be attached to the drag 33 by 90 means of a loop 30 ' passing through a shackle held by a screw pin 82 and attached to the cable by clamp 61 Since the success of our invention resides in the cables 74 and 78 controlling the reflected tension wave created 95 when the lifter straps 22 snap the cable 30 into the air, we carefully measure the cables 74 and 78 to assure that

as soon as the arresting cable is first lifted above the runway the cables 74 and 78 become taut When the further 100 travel of the aircraft against the actuator strap 2 forces the lifter straps nearest the point engaged by the nose wheel strut to snap the arresting cable 30 into the shape of a loop as shown in Fig 10, the cables 74 and 78 have 105 been tightened to the shearing point of the shear pin device 76 At this instant, just before the shear is effected and the cables 74 and 78 are separated, the reflected tension wave is controlled by directing the reflection through 1-10 the cables 74 and 78 back thfouagh cable 30. From the drawings it will be clear that when the shear pin device 76 separates, the arresting cable 30 is free to begin to pick up the first links of the drag 33 in a turn of approximately 115 1800 and gradually pick up more and more links which sweep into a drag forming a rough cuneiform figure behind the aircraft as it progresses down the runway Since the reflected tension wave is controlled, the loop 71 formed 1,20 in the arresting cable 30 can be regulated with almost mathematical certainty by changing the length of the lifter straps 22 If it is desired to delay the time of forming the loop 71, the lifter straps 22 may be lengthened In practice we 125 have found the actuator strap 2 should be supported approximately 38 to 40 inches above the runway From a great many tests, we have found this control of the performance of the loop 71 is impossible without our tension wave 130 785,144 control means as set forth above.

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* GB785145 (A)

Description: GB785145 (A) ? 1957-10-23

Improvements in or relating to a flexible casing for use with the core of apush-pull cable assembly

Description of GB785145 (A)

PATENT SPECIFICATION Date of Application and filing Complete Specification: Aug 15, 1955. \ No 23480/55. Complete Specification Published: Oct 23, 1957. Index at Acceptance:-Class 80 ( 3) D( 1 B: 313), D 5 (A: B: C: D: E). International Classification -FO Sc. COMPLETE SPECIFICATION Improvements in or relating to a Flexible Casing for use with the core of a Push-pull Cable Assembly I, Jo HN FRANKLIN MORSE, a citizen of the United States of America, of 21 Clinton Street, Hudson, Summit County, Ohio, United States of America, do hereby declare the invention, for which I pray that a patent may be granted to me, and the method by which it is to be performed, to be particularly described in and by the following statement:- The present invention relates to what ateknown in the art as "push-pull" cables, in which a flexible core member, usually in the form of a cable, is employed to transmit mechanical motion in either direction This type of mechanism is well known in the art and it is the purpose of the present invention to improve upon the construction and design of the outer casing member through which the core member slides. The usual existing forms of casing have a number of objections which are overcome by the present invention The type of casing shown and described herein is of a design which is adaptable for installation at the point of use. This enables the user to purchase the casing in long lengths, which are cut on the job to fit the requirements thereof The new form of casing also adapts itself to the attachment of end fittings either of the permanently swaged on type or of the detachable type. One of the advantages of the new form of casing is its ability to withstand high compression or tension loads without buckling or stretching In the operation of the core member of the push-pull cable assembly the force which is applied to the end of the core member to shift it in the casing is transmitted to the casing, but in the opposite direction. The casing of the present invention is constructed so that 'it will resist much heavier forces than is possible with ordinary types of casings, hence much greater loads may -be applied to the core member. The casing is also designed so that it will withstand high compressive loads which would crush casings made in accordance with prior art practices Should heavy tools or machinery bump against or be placed on

the casing, it will not crush The casing is also designed to resist kinking or excessive bending at localized points, but it has sufficient flexibility so that it 50 may be bent around corners or over beams, or other obstacles when installed. The -casing is also water and oil tight and will remain so under severe conditions of wear and rough usage, and will resist abrasion or 55 other forces which would injure older forms of casings. One of the main advantages of the invention resides in the fact that the construction of the casing permits a substantial reduction in the 60 clearance between the inner wall of the casing and the outer surface of the slidable core member Reduction in clearance between the casing and the core member reduces the opportunity for bending or buckling of the core 65 member In older forms of casings it has been necessary to provide an excessive amount of clearance between the core and the interior of the casing because of the possibility of the casing becoming deformed, for various reasons 70 The present form of casing also provides -a yielding layer between the inner and outer walls of the casing, which will absorb compression loads placed upon the casing and thus the clearance between the core and the interior 75 of the casing may -be substantially reduced. The casing shown and described herein has a degree of inherent springiness which causes it to lie in a straight line when free to do so,rather than tending to curl or bend, as is the 80 case with older types of casings This feature is especially valuable when the core member has a like tendency to lie in a straight line: because it reduces the frictional drag between the core and the casing The form of casing -85 shown herein has the further advantage that it will not tend to unravel when cut, thus eliminating any necessity for holding the wires which constitute the casing at the points, -of cutting to prevent untwisting of the casing 90 785; 145According to the invention there is provided a flexible casing for use with the core of a pushpull-cable-assembly having an inner reinforcing member to withstand high compressive loads without deformation and an outer reinforcing member to withstand high tensile-loads without elongating, said inner reinforcing member consisting of a flattened wire ribbon tightly wrapped in a helix with the edges of the turns of the ribbon in contact, the contacting edges being rounded with the common tangent at each contact perpendicular to the axis of the casing to permit the casing to be bent without-relative transverse displacement of the turns and the inner surface of the helix forming a constant diameter sliding bearing for the core, said outer reinforcing member consisting of'a plurality of wires spirally wrapped about the O casing 1 N relatively long spirals and havingi a permanent set in the spiral form, and a sheath of rubber or rubber-like material interposed

between said two reinforcing meimbers. In, order that the invention may be understood, it-will now be described with reference to the accompanying drawings in which:Fig 1 is a side elevation of one end of a push-pull cable-assembly: comprising the improved casing of the present invention In this embodiment of the invention, a pivoted operating lever-is attached to the core and the casing-is extended beyond the clamping means thlrefor-so as to aillow for the rocking mover ment of the lever by the bending of the casing. Fig 2 is a side elevation of an alternative type of mounting in which the rocking, movement of the operating lever, is permitted -by a ball and socket connection between the operating lever and the fitting on the end of : the casing. Fig 3-is a lqngiotiinal section through-the. casing and the-end fitting shown in Fig 2. Fig 4 is an enlarged= section through one sid&e of-the casing on,the-line 4-4 of Fig 3. Figi 5 is an enlarged section through one side of the casing at the point of attachment of tlhe end fittingsi the location of this view being indicated by the line-5-5 of Fig 3. In the draw-ings, the movable core member is indicated generally by the numeral 1 This core member may be any of the standard forms of cores but it is preferred to employ that type of core member which consists of a central cables usually; co Ranpsed of nineteen strands-of wre spirally wrapped to form an inner cable 2 and an outer covering consisting of a flat metal ribbon 3-spirally-wrapped about the inner cable and compressed thereon, the core assemblyconstijtuting:an armored strand which is common in the art This type of core member is preferrpd because of its high efficiency and also because ithas a smooth outer surface and tends to lie, in a straight line. Hen ce it-does not create as much friction with the interior of the,-casing as other types of core members. The outer casing is indicated as a whole by the numeral 5, the details of which will be described later In making the installation the user cuts off a length of the casing sufficient for the requirements and secures it in location 70 by any suitable means, an ordinary clip for this purpose being shown at 6 in Fig 1 The user then cuts off a length of the inner core member sufficient so that a substantial portion of the core member will project from either 75 end of the casing for attachment of the end fittings for the core. While many types of core end-fitting may be used, the preferred form is that shown in the drawings The core member 1 is extended 80 into an end fitting 10 which is a bar of metal having a bore 11 to receive the

core member, which is securely clamped to the fitting by screws 12 threadedinto-the fitting and holding the core by deforming it as shown in Fig 2 85 This preferred means of securing the core to its end fitting is covered in U S Patent Specification 2,643,146. The end fitting 10 is pivotally connected at 14 -to the operating member here shown as a 90 pivoted lever or crank arm 15 Secured in a socket, in the outer end of the fitting 10 is a guiding member in the form of a tube 16 which surrounds the core member and is telescopically received, in a sleeve 18 attached 95 to the end-of the casing by an end fitting By this means any movement of the operating lever imparts a direct thrust to the core member. The end fitting for the casing is indicated, 100 as a whole in both Figs 1 and 2 by the-numeral The means by which this end fitting is secured to the casing is the same, in both embodiments of the invention and will be later described The means by which the sleeve 18 105 is attached-to this end fitting in the form shown in Fig 1 consists in providing a socket 22 in the member 21 of the end fitting The end of the sleeve 18 is force fitted-and brazed in the socket so that the sleeve is rigid with the end 110 fitting In this embodiment of the invention the necessary flexibility for operating, the lever and providing for free sliding movement of the tube 16 in the sleeve 18 is provided for by the end of the flexible casing 5 which is ex 115 tended for a sufficient distance beyond the nearest clip or holder 6 to allow for the movemesit of the operating lever. This method of assembling is usually emiployed on light duty cable assemblies where 120 the loads exerted by the operation of the-lever are not excessive However, it is not well suited for assemblies in-which the loads transmitted by the core member are extreme and for this reason the modification shown inm Fig,2 12-5 has been devised. In the form of the invention shown in Figs 2 and 3, the member of the casing end fitting corresponding to the part 21 in Fig 1 is given the reference-numeral 25 This mem 130 wire wrapping which is given the reference numeral 40 This is composed of a plurality of steel wires wrapped in long spirals, with the turns thereof closely spaced but not in actual contact, as shown in Fig 4, and with 70 the spiral on the opposite hand from the spiral. of the inner wire 36 The wires 40 are preformed before being wrapped about the outside of the casing, by which is meant that the wires are formed, in substantially the condition in 75 = which they will lie -in the finished product before wrapping them about the sheath By preforming the wires 40 in the manner described, the casing does not exhibit any tendency to twist or writhe, and hence it will: 80 i remain in a straight line when no bending. force is applied to the, casing, but the casing may be flexed when it

is installed The preforming of the wires also eliminates any tendency of the wires to untwist or ravel when the 85 casing is cut When the wires 40 are applied over the intermediate rubber sheath, the wireswill embed themselves to a limited, extent in, the rubber, as shown in Fig 4. The casing which has been described is, 90ideally suited for attachment of the casing end fittings as will be understood from a further description of this element of the assembly. The outer spiral wire gives an exceedingly durable and abrasive and wear resisting outer 95. covering for the casing and also, provides a high tensile strength when the push-pullcable is working under heavy compression. loads The heavy inner coil of wire 36 provides the desirable compressive strength when the 100 Q push-pull cable is working under heavy tensile loads Both inner and outer coils, together with the intermediate cushion 38 prevent the: casing from crushing under heavy external loads, and the combination of the inner-, and 105 outer coils all tends to resist excessive local bends and to maintain-an even and fairly large radius where bends occur, all of which contributes to the -smooth operation of the inner cable in its movement to and fro in the casing 110. Referring now to the casing end fitting: In the forms of the invention shown in both Figs 1 and 2, the member 21 or-25 is the malemember of a threaded coupling by which the operating elements for the core are securely 115 attached,to the end of the casing The female member in each case is indicated by the numeral and-both elements of the coupling are provided with flattened areas by which they may be rotated relatively to one another in making 120 or detaching the coupling. The male member is provided with a threaded extension 46, which is received within the internally threaded extension 47 on the female member, and the inner end of the male 125 member is formed with the cone shaped socket 48 At the base of the threads on the female member of the coupling or joint is a shoulder and in the space between the two elements of the coupling is the clamping ring 52, one 130 her is provided with a threaded extension 26 in which is formed a spherical socket 27. The guiding sleeve 18 a in this case is provided with a mating spherical head 28 which fits in the socket 27 and is apertured at 29 providing for the angular movement between the core end fitting and the casing, on the rocking of the lever 15; The end of the extension 26 is peened or spun over the head, 28 to hold the elements together. In the form shown in Fig 2, the casing end fitting is held in position by a bracket 32, one arm of which is apertured to fit over the

threaded outer end of the member 25 and is held-in position against a flange 33 by the nut 34 on the extension The other, arm of the brack-et-is adapted to be fastened in location-by bolts or-screws 37, which give a rigid support for the end of -the casing The method of securing the end of the casing in position has advantages where the loads exerted on the core are extremely heavy and also where there is little room to mount the operating:member. Referring now to the details of the casing design: This is composed of an inner member made of a substantially rectangular wire 36 which-is wrapped in a tight coil-or helix, the inner diameter of which is slightly greater than the outer diameter of the core member 1 As explained above, one of the advantages of the invention is that it enables the clearance between the core and the casing to b e reduced substantially over old forms of cable assemblies, thus reducing any tendency of the core to buckle or bend-in the casing under heavy loads and giving much smoother operation In-the present invention the clearance need be only sufficient to provide a free sliding bearing between core and casing, with a small amount of lubricant. It will be noted that the inner and outer surfaces of the wire 36 are flat but that the edges thereof are formed on an arc, which permits a certain amount of flexing in the casing necessary to permit its installation It will also be noted that the common tangent of the curved edges at each contact point is perpendicular-to the axis of the casing to permit the casing to bend without relative transverse displacement of the turns As a result the inner surface of the casing is maintained at constant diameter during-bending. Placed about the inner lining formed by the spiral wire 36 is a sheath of an oil resistant rubber or rubber-like material 38 which is ordinarily extruded and cured over the coil 36. While rubber is normally used, rubber substitutes, plastics, or other resilient materials having waterproofing and yielding properties comparable to rubber may be employed This sheath is of substantial thickness and not only gives the oil and waterproof protection to the interior of the casing but also serves as a cushion to protect the inner wire helix from crushing. Over the sheath 38 is applied the outer spiral 785,1,45 4 785,145 side of which bears against the shoulder The other side of the ring is formed with a reduced skirt or extension 54, which fits into the conical socket on the male member of the coupling and is preferably split so that as the two coupling members are brought together the skirt will be contracted by the cone-shaped socket and will bite into the outer surfaces of the wires 40 The edge of the skirt should be sharpened so as to dig into the several wires as shown in Fig 3 In this view one of the lowermost wires 40 a is shown in extension so as

to illustrate this operation; a true section at this point will show the wires as elongated ovals as they appear in the upper portion of the view. The action of the coupling is illustrated by comparing Figs 4 and 5 Tightening of the two elements of the coupling causes the edge of the skirt to dig into the wires It also crowds the wires 40 together and causes the rubber of the sheath 38 to flow into the interstices between the wires This makes an extremely secure anchorage for the casing end fitting. It will be noted, however, that the tightening of the coupling cannot reduce the innermost diameter of the casing due to the fact that the wires 36 are in a tight coil and also due to the fact that the rubber cushion between the inner and outer coils will permit a contraction of the inner diameter of the outer coil without crushing of the inner coil. It will be seen that the assembly shown and 357 described herein is one which may be easily cut and assembled on location, which reduces the cost of push-pull cable installation The casing is ideally adapted for the attachment of Xa casing end fitting and particularly for that shown herein There is no reduction in the inner diameter of the casing so that it is possible to make a push-pull cable installation in which there is the mi Tnmum amount of clearance between the cable and the casing, resulting in the minimum amount of bacldash The casing assembly is unusually rugged and adapted to withstand all loads placed upon it It is practically indestructible and protects the interior of the casing from oil and water. Where the term "rubber" or "rubber-like" 50 is used in the claims, it is intended to cover all types of rubber or rubber-like or composite material which gives the desired yielding and waterproofing characteristics to the assembly. While the "high efficiency" type of core mem 55 ber is preferred, other core elements may be employed and while zother types of couplings may be susbstituted for that shown, the form shown is best adapted for use with the casing which has been described 60

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* GB785146 (A)

Description: GB785146 (A) ? 1957-10-23

Yarn treatment

Description of GB785146 (A)

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Oil 1 PATENT SPECIFICATION 785,146 Date of Application and filing Complete Specification: Aug 30, 1955. Application made in United States of America on Aug 31, 1954. Complete Specification Published: Oct 23, 1957. Index at Acceptance:-Class 2 ( 3), B 1 (E: J). International Classification:-D Olf. COMPLETE SPECIFICATION Yarn Treatment We, CELANESE CORPORATION OF AMERICA, of 180 Madison Avenue, New York 16, New York, United States of America, a company incorporated in accordance with the laws of the State of Delaware, United States of America, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:- This invention relates to apparatus suitable for the treatment of yarns with liquids.

Apparatus in accordance with the invention comprises a plurality of rotatable rolls, adapted to support yarn to be treated, means for applying liquid to one or more of the rolls, and a wiper element or elements having an upper surface resiliently engaging one of the rolls and a lower surface engaging another of the rolls, the said element or elements preferably extending along at least the greater part of the length of the said rolls, whereby liquid can be wiped off the first of the said rolls and transferred to the second It will be understood that when the apparatus comprises more than two rolls, more than one of them may be provided with a wiper element whereby liquid can be removed from it and transferred to another roll. In an important embodiment of the invention at least one of the rolls has its axis skew with respect to that of the other roll or rolls, so that a yarn can be caused to travel simultaneously round the system of rolls in a number of convolutions, and along the length of the rolls, in the well known manner Rolls so arranged are commonly termed "advancing rolls", and are usually arranged in pairs. Apparatus according to the invention and comprising a system of advancing rolls may be constructed in such a way as to allow the yarn to be treated either with a single liquid or with two or more different liquids In the latter case each roll may be divided into sections separated by barrier means whereby the flow lPrice 3 s 6 d l of treating liquid from one section to another is prevented or hindered, separate means being provided for applying the different -liquids to the several sections It is moreover advantageous to provide an auxiliary wiping means 50 adapted to remove liquid from each section after the first, preferably only over a short length adjacent to the preceding section, in combination with means for transferring liquid so removed to the preceding section of 55 a lower roll, for example an inclined trough. By this means contamination of a particular treating liquid by liquid carried over with the yarn from the preceding section can be largely eliminated 60 The invention will be described in more detail by reference to the accompanying draw ing, in which: Figure 1 is a fragmentary view of a preferred form of apparatus in side elevation, 65 Figure 2 is a cross-sectional view taken along the line 2-2 of Figure 1, and Figure 3 is a cross-sectional view taken along the line 3-3 of Figure 1 Like reference numerals indicate like parts 70throughout the several views of the drawing. Referring now to the drawing, the apparatus comprises a pair of advancing rolls 11 and 12 mounted one above the other and having their axes skew with respect to each other, and both 75 driven in the same direction as shown by the arrows in Figure 2 Owing to the mutual orientation of the rolls a yarn 13 supplied continuously to the upper

roll 11 and carried in a number of spaced convolutions round the rolls 80 will travel from the left or input side to the right or discharge side of the apparatus (as shown in the drawing) in the manner well known in the art Sprinkler means 14 and'16 are positioned above the upper roll 11 for sup 85 plying different treating liquids t 6 it (For the l sake of clarity only two separate treatment zones 17 and 18 are shown in the drawing, but it will be understood that any particular apparatus may comprise any desired number 90 No 24842/55. of treatment zones, in accordance with the number of different treatments it is desired to perform on it) In order to prevent uncontrolled mixing of the different liquids on-the rolls 11 and 12, the rolls are divided into axially spaced sections by means of barrier means 19 and 21 The barrier means may each comprise two rows of grooves 22 inclined to the generating elements of the surface of the rolls The grooves 22 may be evenly spaced round the rolls and may be inclined at an angle of about 300 to about 600, preferably about 450, to the generating elements of the surfaces of the rolls The bottom surface of each groove 22 may be either arcuate or straight in the direction of the -length of the groove, and the grooves of adjacent rows may be staggered as shown in the drawing or in line Other barrier means may however be employed; for example when the treating liquids are aqueous in nature the appropriate parts of the rolls 11 and 12 may be treated to make them water-repellent, for instance by coating them with polytetrafluoroethylene, polyethylene or polytrifluoromonochloroethylene, the uncoated parts of the rolls being of course easily wetted by aqueous liquids For example a film of the desired coating material may be applied to the appropriate parts -of the smooth surfaces of the rolls, preferably over a suitable undercoating, and fused to the rolls by means of heat. The apparatus comprises also wiper blades 23 and 24 mounted on a blade support 26 between the rolls 11 and 12 and substantially parallel to the lower roll 12 The blade support 26 is adjustably mounted on a fixed bar 27 as by means of screws 28 (Figure 1) The wiper -blades 23 and 24 are preferably made of natural or synthetic rubber or of some other flexible and chemically inert material, and are secured in any suitable manner, as by clamping with a metal strip, to the blade support 26 -Each blade 23 and 24 extends for almost the entire length of the corresponding treating zone of the apparatus, and is arranged so that the whole length of the upper edge of the blade rests against and wipes the lower surface of the upper roll 11, thus removing liquid from the roll as. it rotates Under the influence of gravity the liquids so removed flow along the upper surfaces of the blades 23 and 24 and onto the upper surface of the lower roll 12 The lower surfaces of the blades 23 and

24 are serrated evenly along their lower edges 29 and 31 so as to distribute the liquid uniformly over the lower roll 12, and so into contact with the yarn 13 passing over the lower roll, with the mini-mum of disturbance to the yarn. The wiper blades 23 and 24 are uniform in cross-section and in the relaxed position are flat and rectangular, but as installed they are bent owing to their engagement with both the blade support 26 and the lower part of the upper roll-11 The top of the blade support 26 is formed in a smooth curve at 32 to aid in maintaining the blades in even contact with the upper roll 11 Since the blade support 26 extends substantially parallel to the lower roll 12, the serrated edges 29 and 31 of the blades 70 23 and 24 engage the lower roll 12 along a line parallel to its axis Since the axes of the upper and lower rolls are skew with respect to each other, the line along which the upper edges of the blades 23 and 24 engage the upper roll 75 will not be parallel to the axis of the roll. However the spans of the blades 23 and 24 between the top of the blade support 26 and the upper edges of the blades are made sufficiently great to ensure that the flexible blades 80 will maintain close contact with the upper roll 11 along the whole length of their upper edges. The wiper blades 23 and 24 are so mounted that they do not make contact with the grooves 85 22 making up the barriers 19 and 21 (or other barrier means if such are employed), and that part of the blade support 26 which is opposite the barriers has notches in at least one edge, and preferably both, as shown by the reference 90 numerals 33 and 34 These notches serve to prevent or hinder liquid from flowing along the blade support 26 from one zone to another. In the second zone 18 there is provided an auxiliary wiper blade 36, which, like the blades 95 23 and 24, is preferably made of rubber. This auxiliary blade 36 is mounted on any suitable support (not shown) and is situated further back than the blade 24, as viewed in Figure 1, with its upper edge in close contact 100 with the lower part of the upper roll 11 (See Figures 2 and 3) At least part of the auxiliary blade 36 extends closer to the barrier 19 than the edge 37 of the blade 24, so that that part of the upper roll 11 which is between the 105 barrier and the edge 37 is engaged solely by the auxiliary blade The auxiliary blade 36 serves to remove liquid which has been carried over by the yarn 13 from the first to the second section of the upper roll, and which may have 110 been partly diluted by the liquid supplied by the sprinkler 16 A tilted trough 38 is fixed to the lower edge of the auxiliary blade 36 and serves to transfer liquid which has been removed by the auxiliary blade from the upper 115 roll 11 to the upper part of the lower roll 12 in the preceding zone A trough 39 is

provided below the lower roll 12 to receive liquid falling from it, and this liquid can be recycled to the sprinkler head 14 by a pipe 41, fresh make-up 120 liquid being added through an inlet 42. The effective width of the auxiliary blade 36, and therefore the amount of liquid which it transfers from the second zone 18 to the first zone 17, may be varied by adjusting the position 125 of the wiper blade 24 on the support 26 so as to vary the extent to which the blade 24 and the auxiliary blade 36 overlap In the area = where-the blade 24 and the auxiliary blade 36 overlap, the blade 24 will remove most or all 130 t 785,146 system for circulating the saponification liquid may be kept in balance That is to say, when the rate of supply of concentrated sodium hydroxide or other alkaline saponification liquor through the inlet 42 and the rate of supply of 70 wash water through the sprinkler head 16 are kept constant, the position of the blade 24 may be so adjusted that the net amount of liquid withdrawn from the saponification zone 17 by the wet yarn 13 is exactly equalled by 75 the sum of the amount of liquid -returned to the zone by the action of the auxiliary blade 36 and the amount added at the inlet 42 In addition the provision of the auxiliary blade 36 reduces the amount of sodium acetate lost from 80 the system with the wash water.

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* GB785147 (A)

Description: GB785147 (A) ? 1957-10-23

Glyceride molecular rearrangement process

Description of GB785147 (A) Translate this text into Tooltip

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The EPO does not accept any responsibility for the accuracy of data and information originating from other authorities than the EPO; in particular, the EPO does not guarantee that they are complete, up-to-date or fit for specific purposes.

PATENT SPECITI CA-TION - Date of Application and filing Complete Specification: Sept 2, 1955. 785,147 No 25339/55. t W i x t to Application made in United States of America on Sept 2, 1954. Complete Spocification Published: Oct 23, 1957. Index at Acceptance:-Classes 82 ( 1), A 8 G, A 9 B( 1 F: 2 A: 3 E), AX; and 91, C 3 A 7. International Classification:-Cllc C 22 c. COMPLETE SPECIFICATION Glyceride Molecular Rearrangement Process We, THOMAS HIEDLEY & Co LIMITED, a company organised under the laws of Great Britain, of Phoenix Buildings, Collingwood Street, Newcastle upon Tyne, 1, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:- The present invention relates to catalysis of glyceride molecular rearrangement processes, and more particularly to the catalysis of interesterification reactions as applied to glycerides. The use of alkali metals, such as sodium and potassium, to catalyse molecular rearrangement reactions in glycerides is well known, but it is believed that the manner of such priof use, at least in part necessitated by the physical properties of the alkali metal, has not led to ' realization of the maximum effectiveness in catalyst activity The processes of the prior art have either involved dispersion of the sodium orpotassium in the glyceride at substantially elevated temperatures, or have involved the addition to the glyceride of preformed dispersions of the solid alkali metal in an inert, non-aqueous solvent such as xylene, toluene, or kerosene fractions. In the-first instance, those temperatures which ' are required to melt sodium-and potassium are in a range of temperatures conducive to undesirable side reactions with the glyceride, thusresulting in a marked reduction of the catalytic activity of the alkali metal, and in a darkening and even charring of the glyc'eride beingtreated Potassium and sodium melt -at about TF and 2080 F, respectively, and according to experience, the exposure-of the glyceride-to such highly active alkali metals at temperatures substantially above 120 'F, even for

short periods of time, results in appreciable reduction in catalyst activity and quality of the glyceride derived from the treatment. If, for example, the molecular rearrangement reaction is conducted at the tempetature -of lP dispersion or perhaps at some lower temperature which, however, is above the melting point of the sodium or potassium, the aforementioned undesirable side reactions proceed to an objectionable degree Even exposure of 50 the glyceride to the sodium or potassium at such temperatures for short periods of time, as are normally required for dispersion and activation of the catalyst, has adverse effect on the catalytic activity in subsequent opera 55 tions at temperatures below 120 'F Thus, a dispersion of sodium in lard at 250 OF, at a conventional concentration of about O; 2 %, has resulted in complete inactivation of the sodium for catalysis of subsequent directed rearrange 6 ment of the lard at temperatures in the range of -900 F Such inactivation is not observed in practising the present invention, and pre sumably at the higher temperatures of prior practice, the sodium or the active catalyst 65 formed thereform is consumed or poisoned in side reactions In the second instance, the use of preformed dispersions of solid alkali metal in a suitable solvent obviously embodies the addition of the 70 ' solvent as a foreign substance whichi,: -in the case of edible pfoduicts, must later be removedat some stage of processing to enable intended use The step of deodorization, of course, can be conducted in such manner as to accomplish solve'it"remnoval, but'it is difficult to recover the solvefit 'economically' in a form which permnits reuse, and therefore employment of the solvent as a dispersion, vehicle usually represents a net loss Moreover, in 80 cominetcial installations, the handling of combustible solvents-presents undesirable'fire and explosion hazards. Iii additionr, when temperatures of molecular rearrafigeifient are below the melting point' of 8 the sodiuii or potassium, the alkali metal exists as a solid phase, Which even though of a. malleable nafttre and fin-ely dispersed throughout the glyceride, shows not only some resistance' to' prelifinary activation but also a 90susceptibility to poisoning. It is an object of the present invention to provide an improved catalytic material of the alkali metal class for glyceride molecular rearrangement reactions The above object is achieved and the disadvantages of prior teachings are obviated by the use according to the invention, at temperatures not substantially higher than 1200 F, of a metallic sodium and potassium alloy which is liquid at such temperatures While sodium and -potassium each have melting points above 1200 F', certain mixtures or alloys of the two metals have melting points which are much lower than the melting point of either constituent The present invention is therefore directed to the process

of conducting glyceride rearrangement reactions with the aid of liquid sodium-potassium alloys which have melting points not substantially higher than 120 'F. Alloys meeting this specification are those having by weight about 75 % to about 3 % sodium and ab 6 ut 25 % to about 97 % potassium. The lowesitmelting alloy within this composition range, having a -melting point bf about -100 F S contains about 77 % potassium and about 23 % sodium. Those compositions containing from about % to about 15 % sodium and about 50 % to about 85 % potassium are particularly suitable for low temperatures directed rearrangement reactions since their melting points are below 'F, and, in general, rearrangement in accordance with the invention is carried out at a temperature not substantially lower than 500 F For general use, serving demand for economy and liquidity, the 50-50 alloy is preferred The sodium-potassium alloys are obtainable by passing sodium vapour through fused potassium chloride whereby a mixture of potassium and sodium vapours is formed, and second, appropriately fractionating the vapour mixture. In the use of the sodium potassium alloy in accordance with the present invention, the same precautions are observed as in the customary use of sodium or potassium alone Thus for example, any free fatty acids, peroxides, and moisture present in the glycerides tend to consume the catalytic material and sufficient alkali metal must be used to insure an excess over that which might be inactivated by the presence of such materials In general, an excess of 0 02 %,-calculated as percent sodium, has been found to give a reasonable reaction rate, and greater amounts may of course be used, but for economic reasons such amounts do not normally exceed 1 % If the acid and moisture in the glyceride is such as to require such larger usage, then it is usually more economical to purify the glyceride as by preliminary alkali refining and/or drying steps In the treatment of glyceride fats such as dry lard, for example, having a fatty acid content of 0 25 % to 0 5 %, an amount of 50-50 alloy equal to 0 2 % to 0 5 % by weight (calculated as sodium) of the glyceride will usually be found adequate. The liquid sodium potassium alloy can be 70 dispersed directly in the glyceride by means of conventional mechanically agitated dispersing equipment adapted for use with liquids, an example being the Premier Dispersator manufactured by the Premier Mill Corporation of 75 Geneva, New York This is an enclosed mixing device having a relatively small barrel-shaped rotor cage mounted on a vertical axis, this cage being driven at very high speed (from about 15,000 RPM in smaller models to about 80 3,600 RPM in larger units) and being adapted to suck the heavier liquid into its open lower end and to sling, by centrifugal

force, subdivided portions of this heavier liquid into the surrounding lighter liquid through vertical 85 slits in its outer wall Other dispersing devices of well known design, preferably employing a centrifugally induced shearing action, will serve the purpose Expensive special equipment, such as a homogenizer or a colloid mill, 90 although suitable for the purpose, is not necessary However, it should be pointed out that the efficiency of the alloy in catalysis has been found to be in part dependent on its droplet size in the dispersion, higher efficiencies being 95 observed with smaller droplets It is preferable, therefore, that the intensity of agitation during dispersion be such as to give an average droplet diameter not substantially exceeding 50 microns 100 It is believed that the sodium potassium alloy does not immediately possess catalytic activity on introduction into the glyceride, but rather requires a briefperiod for activation, after which catalytic activity is noted This may possibly 105 be due to the reaction of the alloy with glyceride or fatty material in some way to produce the actual catalyst. The use of the present alloys has not only resulted in shorter activation periods but also 110 in appreciably higher activity in bringing the rearrangement reaction to equilibrium This is particularly advantageous in the production of directedly rearranged glycerides wherein sufficiently low reaction temperatures are employed 115 to permit crystallization of higher melting triglycerides formed during the course of interesterification In many instances of such treatment, the temperature will be below 1200 F, such as 40 'F to 950 F, depending on 120 the glyceride being processed. The ability of the alloy to become activated in a relatively short time and to maintain an outstanding high degree of activity throughout the rearrangement reaction is perhaps directly 125 due to the existence of the alloy as droplets, rather than malleable or plastic solid particles, in the presence-of the glyceride during reaction. A liquid is more readily dispersed in finely divided form than a semi-solid, and it would 130 785,147 785,147 appear that complete poisoning of the catalyst as by formation of coatings on the particles, would be delayed in the case of a liquid droplet, which, compared to a semi-solid particle, is relatively easy to deform or subdivide, thereby presenting a fresh surface for catalysts during the reaction. The manner in which the sodium potassium alloys are employed will be readily evident from the following Examples. In these Examples a standardized procedure for determining the "cloud point" was employed to obtain a rough measure of the extent of rearrangement In the cloud point procedure a portion of the material to be examined is heated to about 60 TC and is placed in a tall form

electrolytic type beaker (No 1140 Corning Glass Works, Corning, New York). Means for agitating the sample and for reading its temperature are provided A flowing stream of cold water at a temperature of less than about 70 C is passed around the outside of the beaker at such a rate that the temperature of the glyceride mixture in the beaker drops from 60 to 40 'C in about 1 minute A beam of white light is passed through the beaker and the sample, the transmitted beam intensity being such that a photo cell registers 2 microamperes while the sample is wholly liquid. The temperature at which the transmitted beam intensity is reduced to 31 4 % of its initial intensity as a result of crystal formation throughout the sample is taken as the cloud point temperature The parts and proportions mentioned in the Examples are by weight. EXAMPLE 1 Vacuum dried prime steam lard having a cloud point of 17 40 C was used in this Example. To 2,000 parts of this lard under a nitrogen blanket at a temperature of 970 F were added 5.4 parts of a sodium potassium alloy constituted of equal parts by weight of sodium and potassium The mixture of liquid lard and alloy was then mechanically agitated vigorously to achieve dispersion of the alloy throughout the lard in very finely divided form At the end of about 2 i minutes mixing time, the colour of the mixture changed from light gray to brown, indicating that the catalyst had become activated and that interesterification was taking place At the end of 5 minutes total mixing time, the agitation was stopped, the temperature having risen to about 1151 F. About ' of the reacted mixture was removed and treated with an excess of water to inactivate the catalyst and hydrate the soaps formed by reaction of fatty material with the alkali metal alloy Thereafter the mixture was settled and -the treated oil was filtered to remove suspended sodium and potassium soaps The cloud point of the thus treated lard was 22 60 C, an increase of 5 20 C over the cloud point of the original lard This change in cloud point was sufficient to indicate that substantial interesterification had been effected The five minute reaction period required to obtain this result was much shorter than that required with metallic sodium even at substantially higher temperature. EXAMPLE 2 70 The remaining 5 of the mixture of Example 1 was transferred to a heavy duty mixing device especially adapted to effect the mixing of thick viscous substances or slurries The mixture of glyceride and catalyst was agitated and cooled 75 in the mixer to about 720 F in about 10 minutes.

This cooling brought about crystallization of a substantial portion of higher melting glycerides. Agitation of the slurry was continued and the stock temperature was allowed to rise to 80 Sa 850 F as a result of liberation of the heat of crystallization, and was then held between these temperature limits for a period of one hour At the end of this time, the catalyst was first inactivated with an excess of water while 85: the temperature was held within the 80 'F range, and the resulting mixture was then heated to 120 'F to melt the solidified portion -of the fat The soaps formed by reaction of the alkali metal with the fat were allowed to 90 settle and the decanted oil was filtered to remove suspended sodium and potassium soaps The cloud point on the filtered oil was found to be 29 40 C, a 6 80 C rise over the rearranged product of Example 1 and 12 'C 95 rise over the original lard, indicating that a substantial portion of the combined saturated fatty acids in the lard had been converted to trisaturated glycerides which did not exist in the original or in the Example 1 compositions 00 An equal amount by weight of a 60-40 potassium sodium alloy can be employed in the practice of Examples 1 and 2 with substantially equal results. The improvement in the speed of catalyst 105 activation and of catalysis resulting from the use of the liquid sodium potassium alloy in accordance with the invention, is of outstanding advantage in continuous glyceride rearrangement processes, both of the random and of the 110 directed type Such improvements have made possible the simplification in design of equipment and have resulted in economies due to the permissible use of smaller "holding" or reacting tanks, coils, etc The following 115 Example is exemplary of a continuous process for producing a directly rearranged lard shortening product. EXAMPLE 3 Prime steam lard having a cloud point of 120 18.60 C was continuously heated to about 330 'F and pumped at a rate of 100 pounds per hour through a two-stage vacuum drying unit which reduced the moisture content of the lard to about 0 01 % The stream of lard 125 leaving the vacuum drier was continuously cooled to a temperature of 104 -108 'F and was continuously pumped without exposure to air to a high speed mixing and dispersing device, Premier Dispersator, having sufficient 130 volumetric capacity to provide a "hold" or "dwell" time of about 3 minutes At the point of introduction of the dried lard into this mixer there was also continuously introduced a stream of a 50-50 sodium potassium alloy at a rate of 0 23 pounds per hour The dispersion of finely divided alloy in lard leaving themixet was then continuously passed through a coil of sufficient volume to provide a "hold" EC time of about 15 minutes The mixture leaving this coil had a temperature of 108 1100 F, and a sample taken at this point, after treatment to

inactivate catalyst and remove soap stock, had a cloud point of 23 90 C, indicating substantial interesterification of the lard. The mixture of liquid lard and catalyst leaving the reaction coil was -discharged into a small surge tank -from which it-was pumped continuously through a standard scraped-wall heat exchanger in which the "hold" time was about 05 minutes The stock leaving the heat -exchanger had a temperature of 68 -710 F and contained a heavy cloud of fine crystallized fat solids This partially crystallized mixture was next passed continuously through a small "picker" tube in which th& mixture wasagitated for an average times of about 21 minutes Interesterification with simultaneous precipitation of insoluble glycerides proceeded 3 D rapidly in the picker box as shown by the fact that the temperature of the mixture leaving the picker box had risen to 81 -830 F without the addition of -external heat Such directed interesterification was confirmed by a cloud point 331 analysis of 29 7 "C on the interesterified lard at this point The rate of directed interesterification thus far noted in the process of thisExample was substantially -greater than that which had been experienced with the use of -40 other catalytic materials. For some purposes, the degree of directed rearrangement thus far effected in this Example is sufficient, and the catalyst can be immediately inactivated without substantial change in 4 temperature to preserve the reactants formed For other purposes, however, the reaction can be -carried -to a greater degree of completion, but it should be understood that the rate of the directional reaction is somewhat 507 lower, and this is demonstrated by further processing as follows. Without inactivating the catalyst, the mixture resulting from the above treatment was f passed through a second scraped-wall heat exchanger having a "hold" time of about five minutes The-mixture leaving this second heat exchanger had a temperature of 69 -720 F. This mixture was thence passed continuously through a large reactor equipped with means = for gently agitating the slurry of liquid and solid fat undergoing directed interesterification. This reactor had a "hold" time of about 1-Hv hours, the stock leaving the reactor -being at a temperature of 86 -900 F While the temperature of -the stock leaving the reactor was still within the range of 86 900 F, sufficient water was added to neutralize the catalyst and to hydrate soaps formed during the reaction Subsequently the melted interesterified lard, which now had a cloud 70 point of the order of 31 7 C was separated from soap stock and processed into an acceptable finished shortening in a conventional manner. EXAMPLE 4- To 3 parts by weight of refined, bleached 75 and deodorized cottonseed

oil having a cloud point of 330 C were added 015 parts by weight ( 0 5 %) of a sodium potassium alloy constituted of equal parts by weight of sodiumand potassium The temperature of the oil 80 at the time of the addition of catalyst was 790 F The mixture was mechanically and vigorously agitated with a Premier Dispersator under an atmosphere of nitrogen, effecting dispersion of the-alloy throughout the oil in 85 finely divided form At the end of four minutes agitation, the colour of the mixture became brown, indicating that the catalyst had become activated At the end of a total mixing time of 13 minutes, the agitation was stopped, the 9 Otemperature having risen to 118 'F The catalyst was then inactivated by incorporating about 15 parts by weight of water The potassium and sodium soaps were allowed to settle and the decanted oil was filtered to remove 95 suspended soap particles The cloud point on the filtered -oil was determined as 11 90 C, an 8.60 C rise over the cloud point of the originaloil, indicating that a substantial rearrangement in fatty acid radicals, or interesterification, had 100 been effected X Ex AMPLE 5 -Example 4 was repeated using a sodium potassium alloy catalyst constituted of 10 % by weight of sodium and 90 % by weight of 105 potassium The initial temperature was 820 F, the total time of reaction was 20 minutes (agita tion being discontinued after 13 minutes), and the final temperature was 116 'F The cloud point of the oil was increased from 330 C to 110 13.8 MC indicating substantial interesterification. The above Examples deal with the molecular rearrangement of lard and cottonseed oil as catalysed by the addition of the sodium potassium alloy, but it is to be understood that, 115 as is well known in the art, all animal, vegetable, and marine glyceride fats and oils can be modified in molecular structures by application of the rearrangement reaction Therefore the process is equally applicable with corresponding 120 advantages in the treatment of other glycerides, especially those which are constituted of combined fatty acids whose molecular structures differ in respects affecting solubility of glycerides thereof in the glyceride system, in 125 cluding tallow, palm oil, cottonseed oil, soybean oil, linseed oil, coconut oil, and the like, as well as mixtures thereof Also the invention can be employed with advantages in other glyceride molecular rearrangement reactions 130 785,147 4 droplets averaging not substantially more than microns in diameter. 7 Process according to any of claims 1-6 in which the sodium potassium alloy is introduced as a flowing stream of liquid and the combined streams are subjected to a mixing and dispersing action whereby activation of catalyst is effected and the molecular rearrangement is permitted to take place at a temperature not substantially higher than 120 TF.

8 Process according to any of claims 1-7 in which the molecular rearrangement is effected at a temperature not substantially lower than 50 TF. 9 Process according to any of claims 1-8 in which the rearrangement reaction is accompanied by the precipitation of solid glycerides formed during the course of rearrangement. Process according to any of claims 1-9 performed on lard. 11 Process according to any of claims 1-10, in which the catalytic amount of sodium potassium alloy, based on the glyceride mixture, is within the range of 0 2 % to 1 % by weight, calculated as sodium. 12 Process of catalytically effecting molecular rearrangement of glycerides substantially as described in-any of the foregoing Examples. CARPMAELS & RANSFORD, Agents for Applicants, 24 Southampton Buildings, Chancery Lane, London, W C 2.

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