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Research Papers

Turbine Blade Platform Film Cooling With Fan-Shaped Holes Under Simulated Swirl Purge Flow and Slashface Leakage Conditions

[+] Author and Article Information
Andrew F Chen

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: mrandrewchen@outlook.com

Chao-Cheng Shiau

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

Je-Chin Han

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

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 7, 2017; final manuscript received October 5, 2017; published online October 25, 2017. Editor: Kenneth Hall.

J. Turbomach 140(1), 011006 (Oct 25, 2017) (11 pages) Paper No: TURBO-17-1152; doi: 10.1115/1.4038150 History: Received September 07, 2017; Revised October 05, 2017

The combined effects of upstream purge flow, slashface leakage flow, and discrete hole film cooling on turbine blade platform film cooling effectiveness were studied using the pressure sensitive paint (PSP) technique. As a continued study, discrete cylindrical holes were replaced by laidback fan-shaped (10-10-5) holes, which generally provide better film coverages on the endwall. Experiments were done in a five-blade linear cascade. The inlet and exit Mach numbers were 0.26 and 0.43, respectively. The inlet and exit mainstream Reynolds numbers based on the axial chord length of the blade were 475,000 and 720,000, respectively. A wide range of parameters was evaluated in this study. The coolant-to-mainstream mass flow ratio (MFR) was varied from 0.5%, 0.75%, to 1% for the upstream purge flow. For the platform film cooling holes and slashface gap, average blowing ratios (M) of 0.5, 1.0, and 1.5 were examined. Coolant-to-mainstream density ratios (DR) that range from 1 (close to low-temperature experiments) to 1.5 (intermediate DR) and 2 (close to engine conditions) were also examined. Purge flow swirl effect was studied particularly at a typical swirl ratio (SR) of 0.6. Area-averaged film cooling effectiveness results were compared between cylindrical and fan-shaped holes. The results indicate that the fan-shaped holes provide superior film coverage than cylindrical holes for platform film cooling especially at higher blowing ratios and momentum flux ratios.

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References

Chen, A. F. , Shiau, C.-C. , and Han, J.-C. , 2016, “ Turbine Blade Platform Film Cooling With Simulated Swirl Purge Flow and Slashface Leakage Conditions,” ASME J. Turbomach., 139(3), p. 031012. [CrossRef]
Han, J. C. , Dutta, S. , and Ekkad, S. , 2012, Gas Turbine Heat Transfer and Cooling Technology, CRC Press, Boca Raton, FL.
Bogard, D. G. , and Thole, K. A. , 2006, “ Gas Turbine Film Cooling,” J. Propul. Power, 22(2), pp. 249–270. [CrossRef]
Han, J. C. , 2013, “ Fundamental Gas Turbine Heat Transfer,” ASME J. Therm. Sci. Eng. Appl., 5(2), p. 021007. [CrossRef]
Goldstein, R. J. , 1971, “ Film Cooling,” Adv. Heat Transfer, 7, pp. 321–379.
Chen, A. F. , Li, S.-J. , and Han, J.-C. , 2015, “ Film Cooling for Cylindrical and Fan-Shaped Holes Using Pressure-Sensitive Paint Measurement Technique,” J. Thermophys. Heat Transfer, 29(4), pp. 775–784. [CrossRef]
Chen, A. F. , Li, S.-J. , and Han, J.-C. , 2014, “ Film Cooling With Forward and Backward Injection for Cylindrical and Fan-Shaped Holes Using PSP Measurement Technique,” ASME Paper No. GT2014-26232.
Li, S.-J. , Chen, A. F. , Wang, W.-H. , and Han, J.-C. , 2014, “ Experimental and Computational Film Cooling With Backward Injection for Cylindrical and Fan-Shaped Holes,” 15th International Heat Transfer Conference (IHTC), Kyoto, Japan, Aug. 10--15, Paper No. IHTC15-9584.
Langston, L. S. , 1980, “ Crossflows in a Turbine Cascade Passage,” ASME J. Eng. Power, 102(4), pp. 866–874. [CrossRef]
Langston, L. S. , 2001, “ Secondary Flows in Axial Turbines—A Review,” Ann. N. Y. Acad. Sci., 934, pp. 11–26. http://onlinelibrary.wiley.com/doi/10.1111/j.1749-6632.2001.tb05839.x/abstract [PubMed]
Wang, H. P. , Olson, S. J. , Goldstein, R. J. , and Eckert, E. R. G. , 1997, “ Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades,” ASME J. Turbomach., 119(1), pp. 1–8. [CrossRef]
Chyu, M. K. , 2001, “ Heat Transfer Near Turbine Nozzle Endwall,” Ann. N. Y. Acad. Sci., 934, pp. 27–36. http://onlinelibrary.wiley.com/doi/10.1111/j.1749-6632.2001.tb05840.x/abstract [PubMed]
Simon, T. W. , and Piggush, J. D. , 2006, “ Turbine Endwall Aerodynamics and Heat Transfer,” J. Propul. Power, 22(2), pp. 301–312. [CrossRef]
Friedrichs, S. , Hodson, H. P. , and Dawes, W. N. , 1999, “ The Design of an Improved Endwall Film-Cooling Configuration,” ASME J. Turbomach., 121(4), pp. 772–780. [CrossRef]
Jabbari, M. Y. , Marston, K. C. , Eckert, E. R. G. , and Goldstein, R. J. , 1996, “ Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection,” ASME J. Turbomach., 118(2), pp. 278–284. [CrossRef]
Friedrichs, S. , Hodson, H. P. , and Dawes, W. N. , 1996, “ Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique,” ASME J. Turbomach., 118(4), pp. 613–621. [CrossRef]
Burd, S. W. , Satterness, C. , and Simon, T. , 2000, “ Effects of Slot Bleed Injection Over a Contoured End Wall on Nozzle Guide Vane Cooling Performance—Part II: Thermal Measurements,” ASME Paper No. 2000-GT-0200.
Zhang, L. J. , and Jaiswal, R. S. , 2001, “ Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint,” ASME J. Turbomach., 123(4), pp. 730–738. [CrossRef]
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.
Nicklas, M. , 2001, “ Film-Cooled Turbine Endwall in a Transonic Flow Field—Part II: Heat Transfer and Film-Cooling Effectiveness,” ASME J. Turbomach., 123(4), pp. 720–729. [CrossRef]
Knost, D. G. , and Thole, K. A. , 2005, “ Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First-Stage Vane,” ASME J. Turbomach., 127(2), pp. 297–305. [CrossRef]
Thrift, A. A. , Thole, K. A. , and Hada, S. , 2012, “ Effects of Orientation and Position of the Combustor-Turbine Interface on the Cooling of a Vane Endwall,” ASME J. Turbomach., 134(6), p. 061019. [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. Turbomach., 130(3), p. 031015. [CrossRef]
Gao, Z. H. , Narzary, D. , Mhetras, S. , and Han, J. C. , 2012, “ Upstream Vortex Effect on Turbine Platform Film Cooling With Typical Purge Flow,” J. Thermophys. Heat Transfer, 26(1), pp. 75–84. [CrossRef]
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. Turbomach., 131(2), p. 021017. [CrossRef]
Gao, Z. H. , 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. Turbomach., 131(4), p. 041004. [CrossRef]
Liu, K. , Yang, S. F. , and Han, J. C. , 2014, “ Influence of Coolant Density on Turbine Platform Film-Cooling With Stator-Rotor Purge Flow and Compound-Angle Holes,” ASME J. Therm. Sci. Eng. Appl., 6(4), p. 041007. [CrossRef]
Papa, M. , Srinivasan, V. , and Goldstein, R. J. , 2011, “ Film Cooling Effect of Rotor-Stator Purge Flow on Endwall Heat/Mass Transfer,” ASME J. Turbomach., 134(4), p. 041014. [CrossRef]
Takeishi, K. , Oda, Y. , and Kozono, S. , 2015, “ Experimental Study of Leakage Flow on Flow Field and Film Cooling of High Pressure Turbine Blade Platform,” ASME Paper No. GT2015-42898.
Suryanarayanan, A. , Mhetras, S. P. , Schobeiri, M. T. , and Han, J. C. , 2008, “ Film-Cooling Effectiveness on a Rotating Blade Platform,” ASME J. Turbomach., 131(1), p. 011014. [CrossRef]
Suryanarayanan, A. , Ozturk, B. , Schobeiri, M. T. , and Han, J. C. , 2010, “ Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique,” ASME J. Turbomach., 132(4), p. 041001. [CrossRef]
Rezasoltani, M. , Schobeiri, M. T. , and Han, J. C. , 2014, “ Experimental Investigation of the Effect of Purge Flow on Film Cooling Effectiveness on a Rotating Turbine With Nonaxisymmetric End Wall Contouring,” ASME J. Turbomach., 136(9), p. 091009. [CrossRef]
Barigozzi, G. , Franchini, G. , Perdichizzi, A. , Maritano, M. , and Abram, R. , 2013, “ Influence of Purge Flow Injection Angle on the Aerothermal Performance of a Rotor Blade Cascade,” ASME J. Turbomach., 136(4), p. 041012. [CrossRef]
Stinson, M. , Goldstein, R. J. , Simon, T. W. , Shu, F. , and Chiyuki, N. , 2014, “ Effect of Swirled Leakage Flow on Endwall Film-Cooling,” 15th International Heat Transfer Conference (IHTC), Kyoto, Japan, Aug. 10–15, Paper No. IHTC15-9600.
Li, S.-J. , Lee, J. , Han, J.-C. , Zhang, L. , and Moon, H.-K. , 2016, “ Turbine Platform Cooling and Blade Suction Surface Phantom Cooling From Simulated Swirl Purge Flow,” ASME J. Turbomach., 138(8), p. 081004. [CrossRef]
Yu, Y. , and Chyu, M. K. , 1998, “ Influence of Gap Leakage Downstream of the Injection Holes on Film Cooling Performance,” ASME J. Turbomach., 120(3), pp. 541–548. [CrossRef]
Piggush, J. D. , and Simon, T. W. , 2007, “ Heat Transfer Measurements in a First-Stage Nozzle Cascade Having Endwall Contouring: Misalignment and Leakage Studies,” ASME J. Turbomach., 129(4), pp. 782–790. [CrossRef]
Piggush, J. D. , and Simon, T. W. , 2012, “ Flow Measurements in a First Stage Nozzle Cascade Having Endwall Contouring, Leakage, and Assembly Features,” ASME J. Turbomach., 135(1), p. 011002. [CrossRef]
Shiau, C.-C. , Chen, A. F. , Han, J.-C. , Azad, S. , and Lee, C.-P. , 2016, “ Full-Scale Turbine Vane Endwall Film-Cooling Effectiveness Distribution Using Pressure-Sensitive Paint Technique,” ASME J. Turbomach., 138(5), p. 051002. [CrossRef]
Chowdhury, N. H. K. , Shiau, C.-C. , Han, J.-C. , Zhang, L. , and Moon, H. K. , 2017, “ Turbine Vane Endwall Film Cooling With Slashface Leakage and Discrete Hole Configuration,” ASME J. Turbomach., 139(6), p. 061003. [CrossRef]
Cardwell, N. D. , Sundaram, N. , and Thole, K. A. , 2006, “ The Effects of Varying the Combustor-Turbine Gap,” ASME J. Turbomach., 129(4), pp. 756–764. [CrossRef]
Cardwell, N. D. , Sundaram, N. , and Thole, K. A. , 2005, “ Effect of Midpassage Gap, Endwall Misalignment, and Roughness on Endwall Film-Cooling,” ASME J. Turbomach., 128(1), pp. 62–70. [CrossRef]
Ranson, W. W. , Thole, K. A. , and Cunha, F. J. , 2005, “ Adiabatic Effectiveness Measurements and Predictions of Leakage Flows Along a Blade Endwall,” ASME J. Turbomach., 127(3), pp. 609–618. [CrossRef]
Roy, A. , Jain, S. , Ekkad, S. V. , Ng, W. F. , Lohaus, A. S. , and Crawford, M. E. , 2014, “ Heat Transfer Performance of a Transonic Turbine Blade Passage in Presence of Leakage Flow Through Upstream Slot and Mateface Gap With Endwall Contouring,” ASME Paper No. GT2014-26476.
Lynch, S. , and Thole, K. A. , 2017, “ Heat Transfer and Film Cooling on a Contoured Blade Endwall With Platform Gap Leakage,” ASME J. Turbomach., 139(5), p. 051002. [CrossRef]
Wright, L. M. , McClain, S. T. , and Clemenson, M. D. , 2011, “ Effect of Density Ratio on Flat Plate Film Cooling With Shaped Holes Using PSP,” ASME J. Turbomach., 133(4), p. 041011. [CrossRef]
Barigozzi, G. , Benzoni, G. , Franchini, G. , and Perdichizzi, A. , 2005, “ Fan-Shaped Hole Effects on the Aero-Thermal Performance of a Film-Cooled Endwall,” ASME J. Turbomach., 128(1), pp. 43–52. [CrossRef]
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. Turbomach., 130(3), p. 031007. [CrossRef]
Bunker, R. S. , 2005, “ A Review of Shaped Hole Turbine Film-Cooling Technology,” ASME J. Heat Transfer, 127(4), pp. 441–453. [CrossRef]
Ekkad, S. , and Han, J. C. , 2015, “ A Review of Hole Geometry and Coolant Density Effect on Film Cooling,” Front. Heat Mass Transfer, 6(8), p. 013008. http://www.thermalfluidscentral.org/journals/index.php/Heat_Mass_Transfer/article/view/459
Narzary, D. P. , Liu, K. C. , Rallabandi, A. P. , and Han, J. C. , 2012, “ Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique,” ASME J. Turbomach., 134(3), p. 031006. [CrossRef]
Han, J. C. , and Rallabandi, A. P. , 2010, “ Turbine Blade Film Cooling Using PSP Technique,” Front. Heat Mass Transfer, 1, p. 013001. http://www.thermalfluidscentral.org/journals/index.php/Heat_Mass_Transfer/article/view/71
Kline, S. J. , and McClintock, F. A. , 1953, “ Describing Uncertainties in a Single Sample Experiment,” Mech. Eng., 75(1), pp. 3–8.

Figures

Grahic Jump Location
Fig. 1

Schematic diagram of the test facility

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Fig. 2

Five-blade linear cascade

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Fig. 3

Sectional view of the geometry of the inlet purge seal, (swirl) injection plate, and part of the plenum

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Fig. 4

Design of the platform film-cooling, plenum cavities, and hole shape

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Fig. 5

Schematic diagram of PSP measurement

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Fig. 6

Pressure sensitive paint calibration curve obtained using the endwall test plate

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Fig. 7

Static pressure distributions without coolant injection. Pt: inlet total pressure.

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Fig. 8

Film-cooling effectiveness contours showing inlet purge MFR effect at DR = 1, 1.5, and 2. Platform M = 1.

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Fig. 9

Laterally averaged film-cooling effectiveness showing inlet purge MFR effect: (a) DR = 1, (b) DR = 1.5, and (c) DR = 2. Platform M = 1.

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Fig. 10

Laterally averaged film-cooling effectiveness for DR = 1, 1.5 and 2 at (a) M = 0.5, (b) M = 1, and (c) M = 1.5. Inlet purge MFR = 0.75%.

Grahic Jump Location
Fig. 11

Laterally averaged film-cooling effectiveness for M = 0.5, 1, 1.5 at (a) DR = 1, (b) DR = 1.5, and (c) DR = 2. Inlet purge MFR = 0.75%.

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Fig. 12

Film-cooling effectiveness contours for density and blowing ratio effects under inlet purge MFR = 0.75%

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Fig. 13

Inlet purge swirl ratio effects on the platform film cooling effectiveness at MFR = 1%, platform M = 1 and DR = 1: (a) contour plot and (b) laterally averaged plot

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Fig. 14

Area-averaged effectiveness comparison between cylindrical and fan-shaped holes

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Fig. 15

Area-averaged effectiveness comparison between cylindrical and fan-shaped holes versus momentum flux ratio

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