Rotating Turbine Rig, Heat Transfer, Film Cooling

TPFL: The Turbomachinery Performance and Flow Research LaboratoryTexas A&M University

M. T. Schobeiri

Rotating Turbine Rig, Heat Transfer, Film Cooling

Facility: A new two-loop turbine specially designed for Film cooling/heat tarassfer measurement under rotating

condition.

Instrumentation used: Pressure Sensitive paints (PSP) for film cooling effectiveness

measurement

Temperature sensitive paints (TSP) for heat transfer measurement


M. T. Schobeiri

Rotating Turbine Rig, Aero-Performance Research Capability

Following figures give you an idea about the rotating turbine Aero-performance research capability

The turbine facility is designed to address aerodynamics, heat transfer and performance issues under rotating condition. The facility with its components is shown below schematically.

1 2 3 4c

5

7

1

2 4b

4a

6

5

7

Electric drive

Compressor

Honeycomb

Flow straightener

Research turbine

Turbine inlet with heater

Torque meter

9

7a Flex. couplings

8

8

4b4a

Calibrated Venturi3 Exit diffuser4c 9

107a

Traversing system

Silence chamber10

Dynamometer

6

7a

Turbine Rotor Specially Designed for Heat Transfer and Film Cooling

Rotor has two loops: an Internal cooling loop for purge flow through an inclined circumferential slot and an external loop for platform film cooling/heat transfer Experiments.

.

Mainstream Flow

Rotor-Seal Ejection Cooling

Platform Film Cooling

Mainstream Flow

Rotor-Seal Ejection Cooling

Platform Film Cooling


M. T. Schobeiri

Coolant Injection Through Gap

Cross sectional view of the slot ahead of the 1st stage rotor

Coolant enters the plenum through the hollow shaft and exits the slot at 25º to the horizontal.


M. T. Schobeiri

Coolant Injection Film Cooling Holes on Hub Platform

Turbine 1st Stage Rotor platform and Flow Schematics Downstream Film Cooling Holes Injection

Coolant injection from discrete Holes

STATOR

ROTOR

Sta

tor

Rotor

u

Passage Vortex

GAP


M. T. Schobeiri

Using Pressure Sensitive Paints (PSP) for Film Cooling Effectiveness Measurement

Block diagram of the experimental facility


M. T. Schobeiri

PSP - Calibration

0.0 0.2 0.4 0.6 0.8 1.0

0.0

0.2

0.4

0.6

0.8

1.0

P/P

ref

Iref

/I

Fig. 6 Calibration Curve for PSP

Calibration for Temp. range =

22.2oC to 60.1oC

Thermocouple

Vacuum Chamber

Vacuum Pump

Red light emitted from PSP

Green light to excite

PSP

PC

PSP coated test sample

Strobe light

Camera

Heater for Temperature

Control


M. T. Schobeiri

Boundary Condition and Sample Results

1st Rotor Inlet Velocity = 35.8 m/s

Inlet Mach Number = 0.1

Inlet Temperature = 46°C

Turbine Stage Operating Conditions

Exit Velocity = 107 m/s

Exit Mach Number = 0.3

Exit Temperature = 43°C

Re = 2.0*105 (axial chord length and exit velocity)

Inlet Total – to – Exit Pressure Ratio = 1.4

Angular Velocity = 2400 rpm , 2550 rpm, 3000 rpm

Stator-Rotor Ejection: Cooling Flow ~ 0.5% to 2% of Mainstream

Platform Film Cooling: Blowing Ratio (M=cVc/∞V∞) ~ 0.5 to 2

Density Ratio (DR=c/∞) = 1 (N2 Injection)


M. T. Schobeiri

Results

Measured Film Cooling Effectiveness on the Rotating Platform using PSP – Downstream Discrete Hole Injection

10.90.80.70.60.50.40.30.20.10

M = 0.752400 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.02400 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.252400 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.752400 rpm

10.90.80.70.60.50.40.30.20.10

M = 2.02400 rpm

2400 rpmPitchwise Averaged Film Cooling Effectiveness

at 2400rpm – Effect of Blowing ratio

10.90.80.70.60.50.40.30.20.10

M = 2.02400 rpm

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

M=0.75 M=1.00 M=1.25

M=1.50 M=1.75 M=2.00

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00

Slot Flowm = 1.5% of mainstream

1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

0 0.2 0.4 0.6 0.8 10

0.1

0.2

0.3

M=0.50M=0.75M=1.00M=1.25M=1.50M=1.75M=2.00

10.90.80.70.60.50.40.30.20.10

M = 1.502400 rpm

M=ρcVc/ ρ∞V∞ ; MFR=(msc/ ms)


M. T. Schobeiri

Results

Measured Film Cooling Effectiveness on the Rotating (Reference Point) Platform using PSP – Downstream Discrete Hole Injection

2550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.002550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.502550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.252550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.752550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.002550 rpm

10.90.80.70.60.50.40.30.20.10

M = 2.002550 rpm

Pitchwise Averaged Film Cooling Effectiveness at 2550rpm – Effect of Blowing ratio

10.90.80.70.60.50.40.30.20.10

M = 2.02400 rpm

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

M=0.75 M=1.00 M=1.25

M=1.50 M=1.75 M=2.00

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

0 0.2 0.4 0.6 0.8 10

0.1

0.2

0.3

M=0.50M=0.75M=1.00M=1.25M=1.50M=1.75M=2.00



M. T. Schobeiri

Results

Measured Film Cooling Effectiveness on the Rotating Platform using PSP – Downstream Discrete Hole Injection

3000 rpm

10.90.80.70.60.50.40.30.20.10

M = 2.02400 rpm

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

SS

PS

M=0.75 M=1.00 M=1.25

M=1.50 M=1.75 M=2.00

10.90.80.70.60.50.40.30.20.10

M = 0.752550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.002550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.252550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.502550 rpm

10.90.80.70.60.50.40.30.20.10

M = 1.752550 rpm

10.90.80.70.60.50.40.30.20.10

M = 2.002550 rpm


0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |

Axial Chord, x/CxA

vera

ge

Eff

ect

ive

ne

ss0 0.2 0.4 0.6 0.8 1

0

0.1

0.2

0.3

M=0.50M=0.75M=1.00M=1.25M=1.50M=1.75M=2.00


Results

Pitchwise Averaged Film Cooling Effectiveness on the Rotating Platform using PSP – Downstream Film Cooling Hole Injection

Pitchwise Averaged Film Cooling Effectiveness– Effect of Rotor Speed


Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=0.75

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,0 0.2 0.4 0.6 0.8 1

0

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=1.00

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=1.25

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=1.50

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=2.00

Axial Chord, x/Cx

Ave

rag

eE

ffect

iven

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=1.75

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

,

0 0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

2400 rpm2550 rpm3000 rpm

Mholes=1.50

Results

Measured Film Cooling Effectiveness on the Rotating Platform using PSP – Upstream Stator- Rotor Injection Through Circumferential Slot Only

2400 rpm 2550 rpm 3000 rpm


M. T. Schobeiri

Combination of Slot and Hole InjectionsTurbine 1st Stage Rotor platform and Flow Schematics for Combined Upstream Stator- Rotor

Gap Injection and Downstream Film Cooling Holes Injection

Coolant injection through Stator-Rotor Seal

Coolant injection from discrete holes

STATOR

ROTOR

Sta

tor

Rotor

u

Passage Vortex

GAP


M. T. Schobeiri

Results

Measured Film Cooling Effectiveness on the Rotating Platform using PSP – Combined Upstream Stator- Rotor Gap Injection and Downstream Film Cooling Hole Injection

2400 rpm

0.600.550.500.450.400.350.300.250.200.150.100.05

2400 rpmGap MFR=1.00%Holes M=0.75

SS

PS

MFR=1.00%

M=0.75

0.600.550.500.450.400.350.300.250.200.150.100.05


SS

PS

MFR=1.00%

M=1.00

0.600.550.500.450.400.350.300.250.200.150.100.05


0.600.550.500.450.400.350.300.250.200.150.100.05


SS

PS

MFR=1.00%

M=1.25

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

MFR=1.00%, M=0.75MFR=1.00%, M=1.00MFR=1.00%, M=1.25

2400rpm

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |




M. T. Schobeiri

Results

Measured Film Cooling Effectiveness on the Rotating Platform using PSP – Combined Upstream Stator- Rotor Gap Injection and Downstream Film Cooling Hole Injection

0.600.550.500.450.400.350.300.250.200.150.100.05


0.600.550.500.450.400.350.300.250.200.150.100.05


0.600.550.500.450.400.350.300.250.200.150.100.05


3000 rpm

SS

PS

MFR=1.00%

M=0.75

SS

PS

MFR=1.00%

M=1.00

0.600.550.500.450.400.350.300.250.200.150.100.05


SS

PS

MFR=1.00%

M=1.25

Axial Chord, x/Cx

Ave

rag

eE

ffe

ctiv

en

ess

0.2 0.4 0.6 0.8 10

0.05

0.1

0.15

0.2

0.25

0.3

0.35

MFR=1.00%, M=0.75MFR=1.00%, M=1.00MFR=1.00%, M=1.25

3000rpm

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


1.5% 20 Sep 2005 | | |

0.00 0.14 0.29 0.43 0.57 0.71 0.86 1.00


0.5% 20 Sep 2005 | | |




M. T. Schobeiri

Rotating Turbine Rig, Heat Transfer, Film Cooling

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