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Research Papers

Shower Head and Trailing Edge Cooling Influence on Transonic Vane Aero Performance

[+] Author and Article Information
Ranjan Saha

Heat and Power Technology,
KTH Royal Institute of Technology,
Stockholm SE-100 44, Sweden
e-mail: ranjan.saha@energy.kth.se

Jens Fridh, Torsten H. Fransson

Heat and Power Technology,
KTH Royal Institute of Technology,
Stockholm SE-100 44, Sweden

Boris I. Mamaev

Energy Oil & Gas Design Department,
Siemens LLC,
B. Tatarskaya str., 9,
Moscow 115184, Russia

Mats Annerfeldt, Esa Utriainen

Siemens Industrial Turbomachinery AB,
Finspong SE-612 83, Sweden

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received June 29, 2014; final manuscript received July 8, 2014; published online August 5, 2014. Editor: Ronald Bunker.

J. Turbomach 136(11), 111001 (Aug 05, 2014) (11 pages) Paper No: TURBO-14-1098; doi: 10.1115/1.4028024 History: Received June 29, 2014; Revised July 08, 2014

An experimental investigation on a cooled nozzle guide vane (NGV) has been conducted in an annular sector to quantify aerodynamic influences of shower head (SH) and trailing edge (TE) cooling. The investigated vane is a typical high pressure gas turbine vane, geometrically similar to a real engine component, operated at a reference exit Mach number of 0.89. The investigations have been performed for various coolant-to-mainstream mass–flux ratios. New loss equations are derived and implemented regarding coolant aerodynamic losses. Results lead to a conclusion that both TE cooling and SH film cooling increase the aerodynamic loss compared to an uncooled case. In addition, the TE cooling has higher aerodynamic loss compared to the SH cooling. Secondary losses decrease with inserting SH film cooling compared to the uncooled case. The TE cooling appears to have less impact on the secondary loss compared to the SH cooling. Area-averaged exit flow angles around midspan increase for the TE cooling.

Copyright © 2014 by ASME
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References

Deckers, M., and Denton, J., 1997, “The Aerodynamics of Trailing-Edge-Cooled Transonic Turbine Blades: Part 1—Experimental Approach,” ASME Turbo Expo, Orlando, FL, June 2–5, ASME Paper No. 97-GT–518.
Sieverding, C. H., Arts, T., Denos, R., and Martelli, F., 1996, “Investigation of the Flow Field Downstream of a Turbine Trailing Edge Cooled Nozzle Guide Vane,” ASME J. Turbomach., 118(2), pp. 291–300. [CrossRef]
Kapteijn, C., Amecke, J., and Michelassi, V., 1996, “Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part I—Experimental Approach,” ASME J. Turbomach., 118(3), pp. 519–528. [CrossRef]
Kollen, O., and Koschel, W., 1985, “Effect of Film Cooling on the Aerodynamic Performance of a Turbine Cascade,” AGARD Heat Transfer and Cooling in Gas Turbines Conference (AGARD CP-390), Bergen, Norway, May 6–10.
Rehder, H. J., 2009, “Investigation of Trailing Edge Cooling Concepts in a High Pressure Turbine Cascade—Aerodynamic Experiments and Loss Analysis,” ASME Paper No. GT2009-59303. [CrossRef]
Uzol, O., and Camsi, C., 2001, “Aerodynamic Loss Characteristics of a Turbine Blade With Trailing Edge Coolant Ejection: Part 2—External Aerodynamics, Total Pressure Losses, and Predictions,” ASME J. Turbomach., 123(2), pp. 118–125. [CrossRef]
Aminossadati, S. M., and Mee, D. J., 2013, “An Experimental Study on Aerodynamic Performance of Turbine Nozzle Guide Vanes With Trailing-Edge Spanwise Ejection,” ASME J. Turbomach., 135(3), pp. 1–12. [CrossRef]
Fiala, N. J., Johnson, J. D., and Ames, F. E., 2010, “Aerodynamics of a Letter-Box Trailing Edge: Effect of Blowing Rate, Raynolds Number, and External Turbulence on Aerodynamic Losses and Pressure Distribution,” ASME J. Turbomach., 132(4), pp. 1–11. [CrossRef]
Day, C. R. B., Oldfield, M. L. G., and Lock, G. D., 2000, “Aerodynamic Performance of an Annular Cascade of Film Cooled Nozzle Guide Vanes Under Engine Representative Conditions,” Exp. Fluids, 29(2), pp. 117–129. [CrossRef]
Reiss, H., and Bölcs, A., 2000, “Aerodynamic Loss Measurements in a Linear Cascade With Film Cooling Injection,” 15th Bi-Annual Symposium on Measurement Techniques in Transonic and Supersonic Flow in Cascades and Turbomachines, Florence, Italy, September 21–22.
Bunker, R. S., 2005, “A Review of Shaped Hole Turbine Film-Cooling Technology,” ASME J. Heat Transfer, 127(4), pp. 441–453. [CrossRef]
Hambidge, C., and Povey, T., 2012, “Numerical and Analytical Study of the Effect of Film Cooling on HP NGV Capacity,” ASME Paper No. GT2012-69066. [CrossRef]
Friedrichs, S., Hodson, H. P., and Dawes, W. N., 1997, “Aerodynamic Aspects of Endwall Film-Cooling,” ASME J. Turbomach., 119(4), pp. 786–793. [CrossRef]
Drost, U., and Bölcs, A., 1999, “Performance of a Turbine Airfoil With Multiple Film Cooling Stations, Part II: Aerodynamic Losses,” ASME Turbo Expo, Indianapolis, IN, June 7–10, ASME Paper No. 99-GT-42.
Saha, R., Mamaev, B. I., Fridh, J., Annerfeldt, M., and Fransson, T., 2013, “Suction and Pressure Side Film Cooling Influence on Vane Aero Performance in a Transonic Annular Cascade,” ASME Paper No. GT2013–94319. [CrossRef]
Saha, R., 2012, “Aerodynamic Investigations of a High Pressure Turbine Vane With Leading Edge Contouring at Endwall in a Transonic Annular Sector Cascade,” Licentiate thesis, Department of Energy Technology, KTH Royal Institute of Technology, Stockholm, Sweden.
Mitrus, A., 2012, “Numerical Investigation of Blade Leading Edge Contouring by Fillet and Baseline Case of a Turbine Vane: A Comparative Study of the Effect on Secondary Flow,” M.Sc. thesis, EGI-2012-045 MSC, EKV 894, KTH Royal Institute of Technology, Stockholm, Sweden.
Goldstein, R. J., and Spores, R. A., 1988, “Turbulent Transport on the Endwall in the Region Between Adjacent Turbine Blades,” ASME J. Heat Transfer, 110(4a), pp. 862–869. [CrossRef]
Roux, J., 2004, “Experimental Investigation of Nozzle Guide Vanes in a Sector of an Annular Cascade,” Licentiate thesis, TRITA KRV 2004-3, Department of Energy Technology, KTH Royal Institute of Technology, Stockholm, Sweden.

Figures

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Fig. 1

Test sector with three NGVs

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Fig. 2

Axial section view of test sector

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Fig. 3

Cooling hole location (distorted view)

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Fig. 4

View of five-hole probe

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Fig. 5

Mach number distribution at 50% span

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Fig. 6

Vane profile loading distribution

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Fig. 7

Spanwise exit flow angle distributions at nominal conditions

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Fig. 8

Spanwise exit flow angle distributions for various SH cases

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Fig. 9

Spanwise exit flow angle distributions for various TE cases

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Fig. 10

(a)–(c) Vorticity distributions

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Fig. 11

(a)–(c) Total pressure ratio

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Fig. 12

Mass-averaged kinetic energy loss distribution at nominal conditions

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Fig. 13

Mass-averaged primary loss distribution at nominal conditions

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Fig. 14

Mass-averaged kinetic energy loss distribution for various SH film cooling cases

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Fig. 15

Mass-averaged primary loss distribution for various SH film cooling cases

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Fig. 16

Mass-averaged kinetic energy loss distribution for various TE cooling cases

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Fig. 17

Mass-averaged primary loss distribution for various TE cooling cases

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Fig. 18

Integrated kinetic energy loss for various Y values

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Fig. 19

Circumferential loss distribution around midspan zone

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Fig. 20

Circumferential primary loss distribution around midspan zone

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Fig. 22

Comparison of loss equations in spanwise direction

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Fig. 21

Comparison of loss equations in pitchwise direction

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