0
Research Papers

Influence of Coolant Density on Turbine Platform Film-Cooling With Stator–Rotor Purge Flow and Compound-Angle Holes

[+] Author and Article Information
Kevin Liu, Shang-Feng Yang

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123

Je-Chin Han

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received October 28, 2013; final manuscript received February 24, 2014; published online May 9, 2014. Assoc. Editor: Srinath V. Ekkad.

J. Thermal Sci. Eng. Appl 6(4), 041007 (May 09, 2014) (9 pages) Paper No: TSEA-13-1182; doi: 10.1115/1.4026964 History: Received October 28, 2013; Revised February 24, 2014

A detailed parametric study of film-cooling effectiveness was carried out on a turbine blade platform. The platform was cooled by purge flow from a simulated stator–rotor seal combined with discrete hole film-cooling. The cylindrical holes and laidback fan-shaped holes were accessed in terms of film-cooling effectiveness. This paper focuses on the effect of coolant-to-mainstream density ratio on platform film-cooling (DR = 1 to 2). Other fundamental parameters were also examined in this study—a fixed purge flow of 0.5%, three discrete-hole film-cooling blowing ratios between 1.0 and 2.0, and two freestream turbulence intensities of 4.2% and 10.5%. Experiments were done in a five-blade linear cascade with inlet and exit Mach number of 0.27 and 0.44, respectively. Reynolds number of the mainstream flow was 750,000 and was based on the exit velocity and chord length of the blade. The measurement technique adopted was the conduction-free pressure sensitive paint (PSP) technique. Results indicated that with the same density ratio, shaped holes present higher film-cooling effectiveness and wider film coverage than the cylindrical holes, particularly at higher blowing ratios. The optimum blowing ratio of 1.5 exists for the cylindrical holes, whereas the effectiveness for the shaped holes increases with an increase of blowing ratio. Results also indicate that the platform film-cooling effectiveness increases with density ratio but decreases with turbulence intensity.

FIGURES IN THIS ARTICLE
<>
Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Han, J. C., Dutta, S., and Ekkad, S., 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor & Francis Group, New York.
Chyu, M. K., 2001, “Heat Transfer Near Turbine Nozzle Endwall,” Ann. N. Y. Acad. Sci., 934(1), pp. 27–36. [CrossRef] [PubMed]
Simon, T., and Piggush, J., 2006, “Turbine Endwall Aerodynamics and Heat Transfer,” J. Propul. Power, 22(2), pp. 301–312. [CrossRef]
Langston, L., 1980, “Cross Flow in Turbine Cascade Passage,” J. Eng. Power, 102(1), pp. 866–874. [CrossRef]
Langston, L., 2001, “Secondary Flows in Axial Turbines—A Review,” Ann. N. Y. Acad. Sci., 934(1), pp. 11–26. [CrossRef] [PubMed]
Wang, H., Olson, S., Goldstein, R., and Eckert, E., 1997, “Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades,” ASME J. Turbomachinery, 119(1), pp. 1–8. [CrossRef]
Takeishi, K., Matsuura, M., Aoki, S., and Sato, T., 1990, “An Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbine Nozzles,” ASME J. Turbomachinery, 112(3), pp. 488–496. [CrossRef]
Jabbari, M., Marston, K., Eckert, E., and Goldstein, R., 1996, “Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection,” ASME J. Turbomachinery, 118(2), pp. 278–284. [CrossRef]
Friedrichs, S., Hodson, H., and Dawes, W., 1996, “Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique,” ASME J. Turbomachinery, 118(4), pp. 613–621. [CrossRef]
Friedrichs, S., Hodson, H., and Dawes, W., 1998, “Design of an Improved Endwall Film-cooling Configuration,” ASME Paper No. 98-GT-483.
Vogel, G., Wagner, G., and Bölcs, A., 2002, “Transient Liquid Crystal Technique Combined With PSP for Improved Film Cooling Measurements,” Proceedings 10th International Symposium on Flow Performance, Kyoto, Japan.
Barigozzi, G., Benzoni, G., Franchini, G., and Perdichizzi, A., 2006, “Fan-Shaped Hole Effects on the Aero-Thermal Performance of a Film-Cooled Endwall,” ASME J. Turbomachinery, 128(1), pp. 43–52. [CrossRef]
Granser, D., and Schulenberg, T., 1990, “Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud,” ASME Paper No. 90-GT-95.
Roy, R., Squires, K., Gerendas, M., Song, S., Howe, W., and Ansari, A., 2000, “Flow and Heat Transfer at the Hub Endwall of Inlet Vane Passages—Experiments and Simulations,” ASME Paper No. 2000-GT-198.
Burd, S. W., Satterness, C., and Simon, T., 2000, “Effects of Slot Bleed Injection Over a Contoured Endwall On Nozzle Guide Vane Cooling Performance: Part II—Thermal Measurements,” ASME Paper No. 2000-GT-200.
Oke, R., Simon, T., Shih, T., Zhu, B., Lin, Y. L., and Chyu, M., 2001, “Measurements Over a Film-Cooled, Contoured Endwall with Various Coolant Injection Rates,” ASME Paper No. 2001-GT-0140, p. 0140.
Oke, R. A., and Simon, T. W., 2002, “Film Cooling Experiments with Flow Introduced Upstream of a First Stage Nozzle Guide Vane through Slots of Various Geometries,” ASME Paper No. GT-2002-30169.
Zhang, L. J., and Jaiswal, R. S., 2001, “Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint,” ASME J. Turbomachinery, 123(4), pp. 730–738. [CrossRef]
Zhang, L., and Moon, H. K., 2003, “Turbine Nozzle Endwall Inlet Film Cooling: The Effect of a Back-Facing Step,” ASME Paper No. GT2003-38319.
Wright, L. M., Blake, S. A., Rhee, D. H., and Han, J. C., 2009, “Effect of Upstream Wake With Vortex on Turbine Blade Platform Film Cooling With Simulated Stator–Rotor Purge Flow,” ASME J. Turbomachinery, 131(2), p. 021017. [CrossRef]
Suryanarayanan, A., Ozturk, B., Schobeiri, M., and Han, J., 2010, “Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique,” ASME J. Turbomachinery, 132(4), p. 041001. [CrossRef]
Nicklas, M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II—Heat Transfer and Film-Cooling Effectiveness,” ASME J. Turbomachinery, 123(4), pp. 720-729. [CrossRef]
Wright, L. M., Blake, S. A., and Han, J. C., 2008, “Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator–Rotor Purge and Discrete Film Hole Flows,” ASME J. Turbomachinery, 130(3), p. 031015. [CrossRef]
Suryanarayanan, A., Mhetras, S., Schobeiri, M., and Han, J., 2009, “Film-Cooling Effectiveness on a Rotating Blade Platform,” ASME J. Turbomachinery, 131(1), p. 011014. [CrossRef]
Kadotani, K., and Goldstein, R., 1979, “On the Nature of Jets Entering a Turbulent Flow Part A: Jet-Mainstream Interaction,” J. Eng. Power, 101, pp. 459–465. [CrossRef]
Jumper, G., Elrod, W., and Rivir, R., 1991, “Film Cooling Effectiveness in High-Turbulence Flow,” ASME J. Turbomachinery, 113(3), pp. 479–483. [CrossRef]
Bons, J. P., MacArthur, C. D., and River, R. B., 1996, “The Effect of High Free-Stream Turbulence on Film Cooling Effectiveness,” ASME J. Turbomachinery, 118(4), pp. 814–825. [CrossRef]
Schmidt, D., and Bogard, D., 1996, “Effects of Free-Stream Turbulence and Surface Roughness on Film Cooling,” ASME Paper No. 96-GT-462.
Colban, W., Thole, K. A., and Haendler, M., 2008, “A Comparison of Cylindrical and Fan-Shaped Film-Cooling Holes on a Vane Endwall at Low and High Freestream Turbulence Levels,” ASME J. Turbomachinery, 130(3), p. 031007. [CrossRef]
Salvadori, S., Ottanelli, L., Jonsson, M., Ott, P., and Martelli, F., 2012, “Investigation of High-Pressure Turbine Endwall Film-Cooling Performance Under Realistic Inlet Conditions,” J. Propul. Power, 28(4), pp. 799–810. [CrossRef]
Lynch, S. P., Thole, K. A., Kohli, A., and Lehane, C., 2011, “Computational Predictions of Heat Transfer and Film-Cooling for a Turbine Blade With Nonaxisymmetric Endwall Contouring,” ASME J. Turbomachinery, 133(4), p. 041003. [CrossRef]
Gao, Z., Narzary, D., and Han, J. C., 2009, “Turbine Blade Platform Film Cooling With Typical Stator–Rotor Purge Flow and Discrete-Hole Film Cooling,” ASME J. Turbomachinery, 131(4), p. 041004. [CrossRef]
Gao, Z., Narzary, D., Mhetras, S., and Han, J. C., 2007, “Upstream Vortex Effects on Turbine Blade Platform Film Cooling With Typical Stator–Rotor Purge Flow,” ASME Paper No. IMECE2007-41717.
Narzary, D. P., Liu, K. C., and Han, J. C., 2009, “Influence of Coolant Density on Turbine Blade Platform Film-Cooling,” ASME Paper No. GT-2009-59342.
McLachlan, B., and Bell, J., 1995, “Pressure-Sensitive Paint in Aerodynamic Testing,” Exp. Therm. Fluid Sci., 10(4), pp. 470–485. [CrossRef]
Rallabandi, A. P., Grizzle, J., and Han, J. C., 2011, “Effect of Upstream Step on Flat Plate Film Cooling Effectiveness Using PSP,” ASME J. Turbomachinery, 133(4), p. 041024. [CrossRef]
Jones, T., 1999, “Theory for the Use of Foreign Gas in Simulating Film Cooling,” Int. J. Heat Fluid Flow, 20(3), pp. 349–354. [CrossRef]
Charbonnier, D., Ott, P., Jonsson, M., Cottier, F., and Köbke, T., 2009, “Experimental and Numerical Study of the Thermal Performance of a Film Cooled Turbine Platform,” ASME Paper No. GT2009-60306.
Kline, S. J., and McClintock, F., 1953, “Describing Uncertainties in Single-Sample Experiments,” Mech. Eng., 75(1), pp. 3–8.
Coleman, H. W., and Steele, W. G., 1999, Experimentation and Uncertainty Analysis for Engineers, Wiley-Interscience, New York.

Figures

Grahic Jump Location
Fig. 1

Schematic of (a) experimental facility (b) linear cascade

Grahic Jump Location
Fig. 2

Configuration of upstream stator rotor seal

Grahic Jump Location
Fig. 3

Discrete hole configuration on platform

Grahic Jump Location
Fig. 4

PSP working principle and calibration

Grahic Jump Location
Fig. 5

Velocity profile and freestream turbulence intensity measured at the cascade inlet

Grahic Jump Location
Fig. 6

Pressure and Mach number distribution without coolant injection

Grahic Jump Location
Fig. 7

Density ratio effect on adiabatic film-cooling effectiveness for configuration A (M = 1.5, Tu = 10.5%, MFR = 0.5%)

Grahic Jump Location
Fig. 8

Density ratio effect on adiabatic film-cooling effectiveness for configuration B (M = 1.5, Tu = 10.5%, MFR = 0.5%)

Grahic Jump Location
Fig. 9

Blowing ratio effect on adiabatic film-cooling effectiveness for configuration A (DR = 1.5, Tu = 10.5%, MFR = 0.5%)

Grahic Jump Location
Fig. 10

Blowing ratio effect on adiabatic film-cooling effectiveness for configuration B (DR = 1.5, Tu = 10.5%, MFR = 0.5%)

Grahic Jump Location
Fig. 11

Adiabatic effectiveness distribution at two different turbulence intensities for configuration A (DR = 1.5, M = 1.5, MFR = 0.5%)

Grahic Jump Location
Fig. 12

Adiabatic effectiveness distributions at two different turbulence intensities for configuration B (DR = 1.5, M = 1.5, MFR = 0.5%)

Grahic Jump Location
Fig. 13

Laterally averaged film-cooling effectiveness

Grahic Jump Location
Fig. 14

Area averaged film-cooling effectiveness

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In