Gas Turbine Film Cooling

Journal of Propulsion and Power - Tập 22 Số 2 - Trang 249-270 - 2006
David G. Bogard1, Karen A. Thole2
1University of Texas, Austin, Texas 78712-0292
2Virginia Polytechnic Institute and State University, Blacksburg, Virginia 24060

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10.1115/1.2927678

Han J. C., 2000, Gas Turbine Heat Transfer and Cooling Technology

10.1016/S0065-2717(08)70020-0

10.1115/1.3262237

5Papell, S. S. "Effect on Gaseous Film Cooling of Coolant Injection Through Angled Slots and Normal Holes," NASA Rept. NASA-TN-D-299, Oct.1960.

Hartnett J. P., 1961, Journal of Heat Transfer, 83, 283

10.1115/1.3450752

10.1115/1.1504443

10.1115/1.1371778

Thole K. A., 1992, Hemisphere, 69

Mouzon B. D., 2005, Net Heat Flux Reduction and Overall Effectiveness for a Turbine Blade Leading Edge, 10.1115/GT2005-69002

10.1115/1.2927894

Cutbirth J., 2003, Effects of Coolant Density Ratio on Film Cooling

10.1115/1.1343457

10.1115/1.1505848

10.1115/1.2840938

10.1115/1.3230306

10.1115/1.3262013

10.1115/1.2835681

10.1115/1.3450424

10.1115/1.3446430

10.1115/1.1400111

Kelly G. B., 2003, An Investigation of the Heat Transfer for Full Coverage Film Cooling, 10.1115/GT2003-38716

10.1115/1.2841118

10.1115/1.2840937

Schmidt D. L., 1997, Proceedings of the 32nd National Heat Transfer Conference, HTD-Vol. 350, 12, 233

10.1115/1.1515336

10.1115/1.1515337

Kadotani K., 1979, Transaction of the American Society of Mechanical Engineers, 101, 298

Goldstein R., 1970, Israel Journal of Technology, 8, 145

Goldstein R., 1968, NASA CR-54604

10.1115/1.3450171

10.1115/1.3445904

10.1115/1.3446382

Schwarz S., 1990, Journal of Turbomacherinery, 112, 472

10.1115/1.2927900

10.1016/0017-9310(79)90056-5

Schmidt D. L., 1995, Pressure Gradient Effects on Film Cooling, 10.1115/95-GT-018

10.1016/0017-9310(74)90141-0

10.1115/1.3446602

10.1115/1.3446602

10.1115/1.2927899

10.1115/96-GT-462

10.1115/1.2841752

10.2514/3.501

Bons J., 1995, AIAA Paper, 95

10.1016/S0017-9310(98)00042-8

10.1115/1.3230238

10.1115/1.2928279

10.1115/1.2927684

Rigby M. J., 1990, Gas Turbine Rotor Blade Film Cooling With and Without Simulated NGV Shock Waves and Wakes, 10.1115/90-GT-078

10.1115/1.1400115

10.1115/1.2841411

10.1115/1.3239669

Schmidt D. L., 1996, Effects of Surface Roughness on Film Cooling, 10.1115/96-GT-299

Bogard D. G., 2003, ASME Paper EMECE2003-42061

Rutledge J. L., 2005, Degradation of Film Cooling Performance on a Turbine Vane Suction Side Due to Surface Roughness, 10.1115/GT2005-69045

Polanka M. D., 1999, Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part I: Stagnation Region and Near Pressure Side

Witteveld V. C., 1999, Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part II: Stagnation Region and Near Suction Side

10.1115/1.1451086

10.1115/1.1504441

10.1115/1.2841788

10.1115/1.2928023

10.1115/1.555420

Albert J. E., 2004, Adiabatic and Overall Effectiveness for a Film Cooled Blade, 10.1115/GT2004-53998

Bunker R. S., 2001, Annals of the New York Academy of Sciences, 934, 64

10.1115/1.2835630

10.1115/1.2835638

Kwak J. S., 2002, Heat Transfer Coefficient and Film-Cooling Effectiveness on a Gas Turbine Blade Tip

Kwak J. S., 2002, Heat Transfer Coefficient and Film-Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade

Ahn J., 2004, Film-Cooling Effectiveness on a Gas Turbine Blade Tip Using Pressure Sensitive Paint, 10.1115/GT2004-53249

10.1115/1.1812320

Acharya S., 2002, Numerical Simulation of Film Cooling Holes on the Tip of a Gas Turbine Blade

10.1115/GT2003-38251

10.1115/1.2840916

10.1115/1.2841189

10.1115/1.2836731

10.1115/1.3450239

Granser D., 1990, Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud, 10.1115/90-GT-095

10.1115/1.1561811

10.1115/1.1561812

Burd S. W., 2000, Effects of Slot Bleed Injection over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I: Flow Field Measurements, 10.1115/2000-GT-0199

Burd S. W., 2000, Effects of Slot Bleed Injection over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II: Thermal Measurements

Oke R., 2000, Measurements in a Turbine Cascade Over a Contoured Endwall: Discrete Hole Injection of Bleed Flow

10.1115/2001-GT-0140

Zhang L., 2003, Turbine Nozzle Endwall Inlet Film Cooling-The Effect of a Back-Facing Step, 10.1115/GT2003-38319

10.1115/1.1400112

10.1115/1.1397308

Knost D. K., 2003, Computational Predictions of Endwall Film-Cooling for a First Stage Vane, 10.1115/GT2003-38252

Knost D. G., 2004, Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First Stage Vane, 127

10.1115/1.2929422

10.1115/1.2841188

Kohli A., 1997, 32nd National Heat Transfer Conference, 12, 223

10.1115/98-GT-438

10.1115/1.555433

Buck F. A., 2002, Film Cooling on a Modern HP Turbine Blade Part I: Experimental and Computational Methodology and Validation

Walters D. K., 2002, Film Cooling on a Modern HP Turbine Blade Part II: Compound Angle Round Holes

Ferguson J. D., 2002, Film Cooling on a Modern HP Turbine Blade Part III: Axial Shaped Holes

McGrath E. L., 2002, Film Cooling on a Modern HP Turbine Blade Part IV: Compound Angle Shaped Holes