Abstract
In this paper, detailed overall cooling effectiveness and associated flow patterns are presented for two distinct film hole distribution patterns over a turbine endwall: an axial-row pattern and an iso-Mach number line row pattern. Measurements, in combination with numerical simulations, are performed in a scaled-up cascade. Thermal protection for the endwall is achieved by jet-array impingement on the cold side and discrete film cooling on the hot-gas side, combined with purge air from an inclined slot that simulates the upstream seal cavity. Infrared (IR) thermography techniques are used to obtain overall effectiveness in a wide range of coolant flow ratios of 1.5–3.8%. Mach numbers at the exit of the vane cascade are 0.25 and 0.70, representing the variations of engine operating conditions. Overall effectiveness measurements and computational flowfields show that the iso-Mach number line hole pattern outperforms the hole pattern with axial rows of holes in terms of overall effectiveness levels and thermodynamic energy losses, regardless of coolant flow ratios. Increasing Mach number increases overall effectiveness levels on the endwall and higher Mach numbers generate higher effectiveness improvement for the iso-Mach number line arrangement, relative to the axial-row configuration. Additionally, adding purge air to the endwall considerably improves the overall effectiveness levels and purge air performs better for the axial-row pattern due to no direct interactions with downstream discrete coolant injection.
Issue Section:
Research Papers
References
1.
Town
, J.
, Straub
, D.
, Black
, J.
, Thole
, K. A.
, and Shih
, T. I.-P.
, 2018
, “State-of-the-Art Cooling Technology for a Turbine Rotor Blade
,” ASME J. Turbomach.
, 140
(7
), p. 071007
. 10.1115/1.40399422.
Han
, J. C.
, 2013
, “Fundamental Gas Turbine Heat Transfer
,” ASME J. Therm. Sci. Eng. Appl.
, 5
(2
), p. 021007
. 10.1115/1.40238263.
Simon
, T. W.
, and Piggush
, J. D.
, 2006
, “Turbine Endwall Aerodynamics and Heat Transfer
,” AIAA J. Propul. Power
, 22
(2
), pp. 301
–312
. 10.2514/1.163444.
Wright
, L. M.
, Malak
, M. F.
, Crites
, D. C.
, and Morris
, M. C.
, 2014
, “Review of Platform Cooling Technology for High Pressure Turbine Blades
,” ASME Paper No. GT2014-26373.5.
Vogel
, G.
, 2002
, “Experimental Study on a Heavy Film Cooled Nozzle Guide Vane With Contoured Platforms
,” Ph.D. thesis
, École Polytechnique Fédérale de Lausanne
, Lausanne, Switzerland
.6.
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. Turbomach.
, 128
(1
), pp. 43
–52
. 10.1115/1.20987887.
Colban
, W.
, and Thole
, K.
, 2007
, “Influence of Hole Shape on the Performance of a Turbine Vane Endwall Film-Cooling Scheme
,” Int. J. Heat Fluid Flow
, 28
(3
), pp. 341
–356
. 10.1016/j.ijheatfluidflow.2006.05.0028.
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
. 10.1115/1.30683279.
Sato
, T.
, Aoki
, S.
, Takeishi
, K.
, and Matsuura
, M.
, 1987
, “Effect of Three-Dimensional Flow Field on Heat Transfer Problems of a Low Aspect Ratio Turbine Nozzle
,” International Gas Turbine Congress (IGTC) 1987, Paper No. 87-IGTC-59, Tokyo, Japan.10.
Jabbari
, M.
, Marston
, K.
, Eckert
, E.
, and Goldstein
, R.
, 1996
, “Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection
,” ASME J. Turbomach.
, 118
(2
), pp. 278
–284
. 10.1115/1.283663711.
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. Turbomach.
, 112
(3
), pp. 488
–496
. 10.1115/1.292768412.
Harasgama
, S. P.
, and Burton
, C. S.
, 1992
, “Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1—Experimental Technique and Results
,” ASME J. Turbomach.
, 114
(4
), pp. 734
–740
. 10.1115/1.292802613.
Chowdhury
, N. H. K.
, Shiau
, C. C.
, Han
, J. C.
, Zhang
, L.
, and Moon
, H.-K.
, 2017
, “Turbine Vane Endwall Film Cooling Study from Axial-Row Configuration With Simulated Upstream Leakage Flow
,” ASME Paper No. GT2017-63144.14.
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
. 10.1115/1.284091615.
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
. 10.1115/1.283673116.
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
. 10.1115/1.181109917.
Wu
, P. S.
, and Chang
, S. F.
“Vane Endwall Heat Transfer for Smooth and Stepped Inlet Using Streamwise and Cross Stream Film Injection
,” ASME Paper No. GT2007-27850.18.
Shiau
, C. C.
, Sahin
, I.
, Wang
, N.
, Han
, J. C.
, Xu
, H. Z.
, and Fox
, M.
, 2019
, “Turbine Vane Endwall Film Cooling Comparison From Five Film-Hole Design Patterns and Three Upstream Injection Angle
,” ASME J. Therm. Sci. Eng. Appl.
, 11
(3
), p. 031012
. 10.1115/1.404205719.
Mensch
, A.
, and Thole
, K. A.
, 2014
, “Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling
,” ASME J. Eng. Gas Turbines Power
, 136
(3
), p. 031901
. 10.1115/1.402583520.
Li
, X. Y.
, Ren
, J.
, and Jiang
, H. D.
, 2017
, “Experimental Investigation of Endwall Heat Transfer With Film and Impingement Cooling
,” ASME J. Eng. Gas Turbines Power
, 139
(10
), p. 101901
. 10.1115/1.403636121.
Yang
, X.
, Liu
, Z. S.
, Zhao
, Q.
, Liu
, Z.
, Feng
, Z. P.
, Guo
, F. S.
, Ding
, L.
, and Simon
, T. W.
, 2019
, “Experimental and Numerical Investigations of Overall Cooling Effectiveness on a Vane Endwall With Jet Impingement and Film Cooling
,” Appl. Therm. Eng.
, 148
, pp. 1148
–1163
. 10.1016/j.applthermaleng.2018.11.11622.
Albert
, J. E.
, Bogard
, D. G.
, and Cunha
, F.
, 2004
, “Adiabatic and Overall Effectiveness for a Film Cooled Blade
,” ASME Paper No. GT2004-53998.23.
Yang
, X.
, Liu
, Z. S.
, Zhao
, Q.
, Liu
, Z.
, Feng
, Z. P.
, Guo
, F. S.
, and Ding
, L.
, 2019
, “Measurements of Detailed Heat Transfer Characteristics on a High-Pressure Turbine Vane Endwall With Coolant Injection
,” Exp. Therm. Fluid. Sci.
, 109
, p. 109888
. 10.1016/j.expthermflusci.2019.10988824.
Hollworth
, B. R.
, and Dagan
, L.
, 1980
, “Arrays of Impinging Jets With Spent Fluid Removal Through Vent Holes on the Target Surface—Part 1: Average Heat Transfer
,” ASME J. Eng. Power
, 102
(4
), pp. 994
–999
. 10.1115/1.323037225.
Yang
, X.
, Feng
, Z. P.
, and Simon
, T. W.
, 2019
, “Conjugate Heat Transfer Modeling of Turbine Vane Endwall With Thermal Barrier Coatings
,” Aeronaut. J.
, 123
(1270
), pp. 1959
–1981
. 10.1017/aer.2019.5626.
Moffat
, R. J.
, 1988
, “Describing the Uncertainties in Experimental Results
,” Exp. Therm. Fluid. Sci.
, 1
(1
), pp. 3
–17
. 10.1016/0894-1777(88)90043-X27.
Acharya
, S.
, Tyagi
, M.
, and Hoda
, A.
, 2001
, “Flow and Heat Transfer Predictions for Film Cooling
,” Ann. N. Y. Acad. Sci.
, 934
(1
), pp. 110
–125
. 10.1111/j.1749-6632.2001.tb05846.x28.
Celik
, I. B.
, Ghia
, U.
, Roache
, P. J.
, Freitas
, C. J.
, Coleman
, H.
, and Raad
, P. E.
, 2008
, “Procedure for Estimation and Reporting of Uncertainty Due to Discretization in CFD Applications
,” ASME J. Fluids Eng.
, 130
(7
), p. 078001
. 10.1115/1.296095329.
Cho
, H. H.
, and Rhee
, D. H.
, 2003
, “Local Heat/Mass Transfer Measurement on the Effusion Plate in Impingement/Effusion Cooling System
,” ASME J. Turbomach.
, 123
(3
), pp. 601
–608
. 10.1115/1.134490430.
Yang
, X.
, Liu
, Z.
, and Feng
, Z. P.
, 2015
, “Effect of Film Extraction on Impingement Heat Transfer Characteristics of Jet Arrays on Spherical-Dimpled Surfaces
,” ASME Paper No. GT2015-42585.31.
Saumweber
, C.
, and Schulz
, A.
, 2012
, “Effect of Geometry Variations on the Cooling Performance of Fan-Shaped Cooling Holes
,” ASME J. Turbomach.
, 134
(6
), p. 061008
. 10.1115/1.400629032.
Yang
, X.
, Liu
, Z.
, and Feng
, Z. P.
, 2015
, “Numerical Evaluation of Novel Shaped Holes for Enhancing Film Cooling Performance
,” ASME J. Heat Transfer
, 137
(7
), p. 071701
. 10.1115/1.402981733.
Hermanson
, K. S.
, and Thole
, K. A.
, 2002
, “Effects of Nonuniform Inlet Conditions on Endwall Secondary Flows
,” ASME J. Turbomach.
, 124
(4
), pp. 623
–631
. 10.1115/1.150584934.
Wang
, H. P.
, Olson
, S. J.
, Goldstein
, R. J.
, and Eckert
, E. R. G.
, 1995
, “Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades
,” ASME J. Turbomach.
, 119
(1
), pp. 1
–8
. 10.1115/1.284100635.
Hay
, N.
, Lampard
, D.
, and Benmansour
, S.
, 1983
, “Effect of Crossflows on the Discharge Coefficient of Film Cooling Holes
,” ASME J. Eng. Gas Turbines Power
, 105
(2
), pp. 243
–248
. 10.1115/1.322740836.
Lutum
, E.
, von Wolfersdorf
, J.
, Semmler
, K.
, Naik
, S.
, and Weigand
, B.
, 2001
, “Film Cooling on a Convex Surface: Influence of External Pressure Gradient and Mach Number on Film Cooling Performance
,” Heat Mass Transfer
, 38
(1
), pp. 7
–16
. 10.1007/s00231000014937.
Anderson
, J. B.
, Wikes
, E. K.
, McClintic
, J. W.
, and Bogard
, D. G.
“Effects of Freestream Mach Number, Reynolds Number and Boundary Layer Thickness on Film Cooling Effectiveness of Shaped Holes
,” ASME Paper No. GT2016-56152.38.
Saumweber
, C.
, and Schulz
, A.
, 2012
, “Free-Stream Effects on the Cooling Performance of Cylindrical and Fan-Shaped Cooling Holes
,” ASME J. Turbomach.
, 134
(11
), p. 061007
. 10.1115/1.400628739.
Ligrani
, P. M.
, Saumweber
, C.
, Schulz
, A.
, and Wittig
, S.
, 2001
, “Shock Wave-Film Cooling Interactions in Transonic Flows
,” ASME J. Turbomach.
, 123
(4
), pp. 788
–797
. 10.1115/1.139730540.
Barigozzi
, G.
, Abdeh
, H.
, Perdichizzi
, A. G.
, Henze
, M.
, and Krueckels
, J.
, 2017
, “Aero-Thermal Performance of a Nozzle Vane Cascade With a Generic Non-Uniform Inlet Flow Condition—Part II: Influence of Purge and Film Cooling Injection
,” ASME J. Turbomach.
, 139
(10
), p. 101004
. 10.1115/1.403643741.
Kost
, F.
, and Nicklas
, M.
, 2001
, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I—Aerodynamic Measurements
,” ASME Paper No. 2001-GT-0145.Copyright © 2020 by ASME
You do not currently have access to this content.
