Gas Turbine Film Cooling
Tóm tắt
Từ khóa
Tài liệu tham khảo
Han J. C., 2000, Gas Turbine Heat Transfer and Cooling Technology
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
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
Cutbirth J., 2003, Effects of Coolant Density Ratio on Film Cooling
Kelly G. B., 2003, An Investigation of the Heat Transfer for Full Coverage Film Cooling, 10.1115/GT2003-38716
Schmidt D. L., 1997, Proceedings of the 32nd National Heat Transfer Conference, HTD-Vol. 350, 12, 233
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
Schwarz S., 1990, Journal of Turbomacherinery, 112, 472
Bons J., 1995, AIAA Paper, 95
Rigby M. J., 1990, Gas Turbine Rotor Blade Film Cooling With and Without Simulated NGV Shock Waves and Wakes, 10.1115/90-GT-078
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
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
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
Acharya S., 2002, Numerical Simulation of Film Cooling Holes on the Tip of a Gas Turbine Blade
Granser D., 1990, Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud, 10.1115/90-GT-095
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
Zhang L., 2003, Turbine Nozzle Endwall Inlet Film Cooling-The Effect of a Back-Facing Step, 10.1115/GT2003-38319
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
Kohli A., 1997, 32nd National Heat Transfer Conference, 12, 223
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