API-MS Transfer Capillary Flow: Examination of the ...
1
Temperature [°C] Introduction Conclusions Methods API-MS Transfer Capillary Flow: Examination of the Downstream Gas Expansion Sebastian Klopotowski 1 ; Yessica Brachthaeuser 1 ; David Mueller 1 ; Hendrik Kersten 1 ; Walter Wissdorf 1 ; Valerie Derpmann 1 ; Sonja Klee 1 ; Klaus J. Brockmann 1 ; Uwe Janoske 2 ; Hauke Gregor 2 ; Thorsten Benter 1 Experimental Setup Sound Measurements Literature 1) K. J. Brockmann, W. Wissdorf, L. Hyzak, H. Kersten, D. Mueller, Y. Brachthaeuser and T. Benter; Fundamental characterization of ion transfer capillaries used in Atmospheric Pressure Ionization Sources, Salt Lake City, 2010. American Society for Mass Spectrometry, Proceedings of 58th ASMS Conference. 2) D. J. Carrol, I. Dzidic and E. Horning; Atmospheric pressure ionization mass spectrometry. Applied Spectroscopy Reviews, 17(3):337-406, 1981. 3) C. Whitehouse; Electrospray interface for liquid chromato- graphs and mass spectrometers. Analytical Chemistry, 57(3):675, 1985. 4) A. P. Bruins; Mass spectrometry with ion sources operating at atmospheric pressure, Mass Spectrometry Reviews, 10:53-77, 1991. 5) B. Lin and J. Sunner; Ion transport by viscous gas flow through capillaries. Journal of the American Society for Mass Spectrometry, 5(10):873, 1994. 6) E. S. Love, C. E. Grigsby, L. P. Lee and M. J. Woodling; Experimental and numerical investigations of an axis symetric supersonic jet. Technical Report R-6, NASA, 1959. 7) K. Bier and B. Schmidt; Zur Form der Verdichtungsstöße in frei expandierenden Gasstrahlen. Zeitschrift für Angewandte Physik, 13:496-500, 1961 8) R. Campargue; Progress in Overexpanded Supersonic Jets and Skimmed Molecular Beams in Free-jet Zone of Silence, Journal of Physical Chemistry, 88:4466-4474, 1984 9) A. Michalke; Beitrag zur Rohrströmung kompressibler Fluide mit Reibung und Wärmeübergung. Ingenieur-Archiv, 57:377-392, 1987 The application of atmospheric pressure ionization (API) necessitates a pressure reduction in differential pumping stages before mass analysis. One common approach for the first reduction step from atmospheric pressure to the low mbar range is realized by critically operated capillaries. The pressure ratio between capillary entrance and first pumping stage is generally greater than 0.5 leading to choked flow conditions. In fluid dynamical terms the gas flow out of the capillary is a transonic overexpansion. Stationary shock waves (Mach discs), depending on capillary bore and back- ground pressure, are thus expected. The interaction between the gas jet leaving the capillary and downstream ion optical devices (skimmers / ion funnels) could potentially lead to significant ion losses. The capillary is either actively tempered or heated by a hot dry gas stream. We used an automated experimental setup to analyze in detail the flow conditions downstream of the transfer capillary exit at various temperatures and pressures. Computational Fluid Dynamics (CFD) : Basic numerical calculations performed with OpenFOAM Fast-Fourier-Transformation (FFT) : Sound spectrum analysis performed by gnuOCTAVE and plotted with gnuPlot Temperature Distribution behind Capillary Exit Numerical Methods Measurement Chamber: Home built vacuum recipient with mounting for a transfer capillary, evacuated by a flow controlled rotary pump Temperature Probe: Micro thermocouple (Type K: Ni/CrNi) with 0.25 mm diameter, mounted on a positioning stage behind the capillary exit Capillary: Home built glass capillary with internal Pt100 measuring resistor, length 18 cm, inner diameter 0.5 mm. Enveloped with tantalum wire (0.1 mm) for current heating XY-Stage: Moveable platform adjusted by two I²C controlled, motorized thread rods Contact Microfone: Directly attached close to capillary exit, signals recorded by computer audio interface Pressure Control: MKS Type 252E Exhaust Valve Controller between measurement chamber and rough pump with matching butterfly valve. Data Acquisition: Labjack U12 A/D D/A Interface Experimental Methods D Figure 2) Sound emission as function of pressure in the vacuum recipient at 85°C capillary temperature. Pressure in vacuumrecipient [mbar] Frequency [Hz] • A remarkably narrow and stable gas jet leaves the transfer capillary and can still be measured at some centimeters distance from the exit • The jet diameter is inversely dependent on the vacuum recipient pressure • Under typical operating conditions the jet diameter is two to three times wider than the skimmer bore • Stationary shock waves are observed as sudden increases in the jet temperature, as predicted by numerical calculations • The Mach disc appears at the expected location irrespective of the capillary wall temperature • The measured maximum jet core temperature is only marginally lower than the controlled capillary wall temperature • The minimum temperature in the expansion zone is higher than predicted by the calcula- tions even if the effect of radiation heating by the capillary is considered Interference between jet and skimmer have to be expected • With rising temperature and viscosity the gas throughput decreases to values that also result from theoretical calculations • The gas flow is heated effectively even when only the last few cm of the capillary are tempered There is not much doubt that the capillary flow is turbulent. • Transfer capillaries emit characteristic sound spectra, which are dependent on the wall temperature and gas flow • The frequency spectrum varies with wall tem- perature but not with recipient pressure • The highest signal intensities were observed at a recipient pressure of 30 mbar • Preliminary CFD calculations give an adequate, qualitative picture of the overexpanded flow; additional investigations are underway Figure 3c) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 1.0 mm behind the capillary exit, width of the gas jet is roughly 1 mm Figure 3b) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 2.4 mm behind the capillary exit, width of the gas jet is roughly 2.5 mm Figure 3a) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 2.3 mm behind the capillary exit, width the of gas jet is 2.5 mm I 2 C-Bus USB LabJack pressure valve thermo couple Pt100 pressure gauge C A B D E analog OUT analog IN analog IN analog IN A: Computer with Python interpreter B: Stepper Motors C: Thermocouple D: Heated capillary with temp. sensor E: Labjack U12 AD/DA Device • Automated measuring equipment is computer controlled. Software is written in Python programming language (version 3.1) using Qt 4.7 for graphical user interface. • Data are collected with an AD/DA device that additionally generates the control voltage for the pumping stage. Stepper motors, driven via I 2 C- Interface, move xy-stage with mounted thermocouple. • Spatial resolution is 0.1mm per iteration, maximal measured area is two by two centimeters. • The contact microphone, clipped onto the capillary, is not shown here. It is directly connected to the PC sound interface Temperature [°C] Temperature [°C] [°C] [°C] Axial Temperature Profile Figure 5) Position of mach disc as a function of background pressure ( p1) compared to theoretical values[6,7]. x M is the distance from the capillary exit to the mach disc, p 0 = 140 mbar is the pressure at the capillary exit, d is the capillary diameter (capillary temperature = 100°C) a.) T = 26°C / p 1 = 3 mbar b.) T = 85°C / p 1 = 2 mbar c.) T = 100°C / p 1 = 20 mbar x M [mm] background pressure p 1 [mbar] Position of Mach Disc [°C] Choked Flow Figure 4) Temperature distribution along the jet axis for different background pressures. Shock waves are recognizable by the transient temperature increases. Figure 6) Choked flow through the capillary for three different temperatures. Flow rate increases up to a pressure ratio close to 0.5 and becomes constant and independent of the vacuum recipient pressure Distance to capillary exit [mm] Temperature [°C] Flow [L/min] pressure difference [mbar] 1 Physical & Theoretical Chemistry 2 Mechanical Engineering University of Wuppertal, Germany Institute for Pure and Applied Mass Spectrometry Figure 1a) Heatable transfer capillary with built-in thermo resistor and tantalum filament; the gas flow enters from the right. Figure 1b) Schematic representation of the first differential pumping stage, the skimmer diameter is about 1.5 mm, the distance from the capillary exit to the skimmer is 1 to 2 mm Exit Skimmer Multipol 25.5 °C 100.0 °C 65.5 °C a) p 1 = 2 mbar c) p 1 = 20 mbar b) p 1 = 3 mbar Pt100 Electrical connections Tantalum wire Capillary API Source P atm = 1 bar P 1 = 4 mbar P 2 = 0.5 mbar T cap = 84°C T cap = 28°C T cap = 28°C
Transcript of API-MS Transfer Capillary Flow: Examination of the ...
Tem
pera
ture
[°C
]
Introduction Conclusions
Methods
API-MS Transfer Capillary Flow: Examination of the Downstream Gas Expansion
Sebastian Klopotowski1; Yessica Brachthaeuser1; David Mueller1; Hendrik Kersten1; Walter Wissdorf1; Valerie Derpmann1; Sonja Klee1; Klaus J. Brockmann1; Uwe Janoske2; Hauke Gregor2; Thorsten Benter1
Experimental Setup Sound Measurements
Literature1) K. J. Brockmann, W. Wissdorf, L. Hyzak, H. Kersten, D. Mueller, Y.
Brachthaeuser and T. Benter; Fundamental characterization ofion transfer capillaries used in Atmospheric Pressure IonizationSources, Salt Lake City, 2010. American Society for MassSpectrometry, Proceedings of 58th ASMS Conference.
2) D. J. Carrol, I. Dzidic and E. Horning; Atmospheric pressureionization mass spectrometry. Applied Spectroscopy Reviews,17(3):337-406, 1981.
3) C. Whitehouse; Electrospray interface for liquid chromato-graphs and mass spectrometers. Analytical Chemistry,57(3):675, 1985.
4) A. P. Bruins; Mass spectrometry with ion sources operating atatmospheric pressure, Mass Spectrometry Reviews, 10:53-77,1991.
5) B. Lin and J. Sunner; Ion transport by viscous gas flow throughcapillaries. Journal of the American Society for MassSpectrometry, 5(10):873, 1994.
6) E. S. Love, C. E. Grigsby, L. P. Lee and M. J. Woodling;Experimental and numerical investigations of an axis symetricsupersonic jet. Technical Report R-6, NASA, 1959.
7) K. Bier and B. Schmidt; Zur Form der Verdichtungsstöße in freiexpandierenden Gasstrahlen. Zeitschrift für AngewandtePhysik, 13:496-500, 1961
8) R. Campargue; Progress in Overexpanded Supersonic Jets andSkimmed Molecular Beams in Free-jet Zone of Silence, Journalof Physical Chemistry, 88:4466-4474, 1984
9) A. Michalke; Beitrag zur Rohrströmung kompressibler Fluide mitReibung und Wärmeübergung. Ingenieur-Archiv, 57:377-392,1987
The application of atmospheric pressureionization (API) necessitates a pressurereduction in differential pumping stagesbefore mass analysis. One commonapproach for the first reduction step fromatmospheric pressure to the low mbar rangeis realized by critically operated capillaries.The pressure ratio between capillary entranceand first pumping stage is generally greaterthan 0.5 leading to choked flow conditions.In fluid dynamical terms the gas flow out ofthe capillary is a transonic overexpansion.Stationary shock waves (Mach discs),depending on capillary bore and back-ground pressure, are thus expected. Theinteraction between the gas jet leaving thecapillary and downstream ion optical devices(skimmers / ion funnels) could potentially leadto significant ion losses.The capillary is either actively tempered orheated by a hot dry gas stream.We used an automated experimental setupto analyze in detail the flow conditionsdownstream of the transfer capillary exit atvarious temperatures and pressures.
Computational Fluid Dynamics (CFD) :Basic numerical calculations performed withOpenFOAM
Fast-Fourier-Transformation (FFT) :Sound spectrum analysis performed bygnuOCTAVE and plotted with gnuPlot
Temperature Distribution behind Capillary Exit
Numerical Methods
Measurement Chamber:Home built vacuum recipient with mountingfor a transfer capillary, evacuated by aflow controlled rotary pump
Temperature Probe:Micro thermocouple (Type K: Ni/CrNi) with0.25 mm diameter, mounted on a positioningstage behind the capillary exit
Capillary:Home built glass capillary with internal Pt100measuring resistor, length 18 cm, innerdiameter 0.5 mm. Enveloped with tantalumwire (0.1 mm) for current heating
XY-Stage:Moveable platform adjusted by two I²Ccontrolled, motorized thread rods
Contact Microfone:Directly attached close to capillary exit,signals recorded by computer audiointerface
Pressure Control:MKS Type 252E Exhaust Valve Controllerbetween measurement chamber and roughpump with matching butterfly valve.
Data Acquisition:Labjack U12 A/D D/A Interface
Experimental Methods
D
Figure 2) Sound emission as function of pressure in the vacuum recipient at 85°C capillary temperature.
Pres
sure
in v
acuu
mre
cipi
ent [
mba
r]
Frequency [Hz]
• A remarkably narrow and stable gas jet leavesthe transfer capillary and can still be measuredat some centimeters distance from the exit
• The jet diameter is inversely dependent on thevacuum recipient pressure
• Under typical operating conditions the jetdiameter is two to three times wider than theskimmer bore
• Stationary shock waves are observed assudden increases in the jet temperature, aspredicted by numerical calculations
• The Mach disc appears at the expectedlocation irrespective of the capillary walltemperature
• The measured maximum jet core temperature isonly marginally lower than the controlledcapillary wall temperature
• The minimum temperature in the expansionzone is higher than predicted by the calcula-tions even if the effect of radiation heating bythe capillary is considered
Interference between jet and skimmer have tobe expected
• With rising temperature and viscosity the gasthroughput decreases to values that also resultfrom theoretical calculations
• The gas flow is heated effectively even whenonly the last few cm of the capillary aretempered
There is not much doubt that the capillary flowis turbulent.
• Transfer capillaries emit characteristic soundspectra, which are dependent on the walltemperature and gas flow
• The frequency spectrum varies with wall tem-perature but not with recipient pressure
• The highest signal intensities were observed at arecipient pressure of 30 mbar
• Preliminary CFD calculations give an adequate,qualitative picture of the overexpanded flow;additional investigations are underway
Figure 3c) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 1.0 mm behind the capillary exit, width of the gas jet is roughly 1 mm
Figure 3b) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 2.4 mm behind the capillary exit, width of the gas jet is roughly 2.5 mm
Figure 3a) Results of the temperature measurements in a transonic jet. First shock front is identifiable approximately 2.3 mm behind the capillary exit, width the of gas jet is 2.5 mm
I2C-Bus
USB
LabJack
pressure valve
thermo couple
Pt100
pressure gauge
C
AB
D
E
analog OUT
analog IN
analog IN
analog IN
A: Computer with Python interpreter
B: Stepper Motors
C: Thermocouple
D: Heated capillary with temp. sensor
E: Labjack U12 AD/DA Device
• Automated measuring equipment iscomputer controlled. Software iswritten in Python programminglanguage (version 3.1) using Qt 4.7 forgraphical user interface.
• Data are collected with an AD/DAdevice that additionally generates thecontrol voltage for the pumping stage.Stepper motors, driven via I2C-Interface, move xy-stage withmounted thermocouple.
• Spatial resolution is 0.1mm periteration, maximal measured area istwo by two centimeters.
• The contact microphone, clippedonto the capillary, is not shown here. Itis directly connected to the PC soundinterface
Tem
pera
ture
[°C
]
Tem
pera
ture
[°C
]
[°C] [°C]
Axial Temperature Profile
Figure 5) Position of mach disc as a function of background pressure (p1) compared to theoretical values[6,7]. xM is the distance from the capillary exit to the mach disc, p0 = 140 mbar is the pressure at the capillary exit, dis the capillary diameter (capillary temperature = 100°C)
a.) T = 26°C / p1 = 3 mbar b.) T = 85°C / p1 = 2 mbar c.) T = 100°C / p1 = 20 mbar
x M[m
m]
background pressure p1 [mbar]
Position of Mach Disc
[°C]
Choked Flow
Figure 4) Temperature distribution along the jet axis for different background pressures. Shock waves are recognizable by the transient temperature increases.
Figure 6) Choked flow through the capillary for three different temperatures. Flow rate increases up to a pressure ratio close to 0.5 and becomes constant and independent of the vacuum recipient pressure
Distance to capillary exit [mm]
Tem
pera
ture
[°C
]
Flow
[L/
min
]
pressure difference [mbar]
1Physical & Theoretical Chemistry2Mechanical Engineering
University of Wuppertal, GermanyInstitute for Pure and Applied Mass Spectrometry
Figure 1a) Heatable transfer capillary with built-in thermo resistor and tantalum filament; the gas flow enters from the right.
Figure 1b) Schematic representation of the first differential pumping stage, the skimmer diameter is about 1.5 mm, the distance from the capillary exit to the skimmer is 1 to 2 mm
Exit
Skimmer Multipol
25.5 °C
100.0 °C
65.5 °C
a) p1 = 2 mbar c) p1 = 20 mbar b) p1 = 3 mbar
Pt100
Electrical connections
Tantalum wire
Capillary
APISource
Patm= 1 bar P1 = 4 mbar P2 = 0.5 mbar
Tcap = 84°C Tcap = 28°CTcap = 28°C
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