Net heat flux reduction and overall effectiveness for a turbine blade leading edge

Proceedings of the ASME Turbo Expo

Volumn 3 PART A, Issue , 2005, Pages 825-832

  Mouzon, Brian D ^a   Albert, Jason E ^a,c   Terrell, Elon J ^a,b   Bogard, David G ^a  

^a UNIVERSITY OF TEXAS AT AUSTIN   (United States)

^b CARNEGIE MELLON UNIVERSITY   (United States)

^c PRATT AND WHITNEY   (United States)

Author keywords

Film cooling; Heat transfer coefficient; Matched Biot number; Net heat flux reduction; Overall effectiveness

Indexed keywords

BIOT NUMBER; COOLING HOLES; FILM COOLING; SURFACE TEMPERATURES;

AIRFOILS; COOLING; HEAT TRANSFER COEFFICIENTS; TURBOMACHINE BLADES;

HEAT FLUX;

EID: 27744587723     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.1115/GT2005-69002     Document Type: Conference Paper

References (13)

1. Sen, B., Schmidt, D.L., and Bogard, D.G., 1996, "Film Cooling with Compound Angle Holes: Heat Transfer," ASME J. of Turbomachinery, Vol 118, pp. 800-806.
2. Mick, W. J. and Mayle, R. E., 1988, "Stagnation Film Cooling and Heat Transfer, Including it effects Within the Hole Pattern," ASME J. of Turbomachinery, Vol 110, pp. 66-72.
3. Albert, J.E., Bogard, D.G., and Cunha, F., 2004, "Adiabatic and Overall Effectiveness for a Film Cooled Blade," ASME paper 04-GT-53998.
4. Sweeney, P.C., and Rhodes, J.F., 2000, "An Infrared Technique for Evaluating Turbine Airfoil Cooling Designs," Journal of Turbomachinery, Vol 122, pp.170-177.
5. Bohn, D., Ren, J., and Kusterer, K., 2003, "Conjugate Heat Transfer Analysis for Film Cooling Configurations with Different Hole Geometries," ASME 03-GT-38369.
6. Kusterer, K., Bohn, D., Sugimoto, T., and Tanaka, R., 2004, "Conjugate Calculations for a Film-Cooled Blade Under Different Operating Conditions," ASME 04-GT-53719.
7. Cruse, M.W., Yuki, U.M., and Bogard, D.G., 1997, "Investigation of Various Parametric Influences on Leading Edge Film Cooling," ASME 97-GT-296.
8. Yuki, U.M., Bogard, D.G., and Cutbirth, J.M., 1998, "Effect of Coolant Injection on Heat Transfer for a Simulated Turbine Airfoil Leading Edge," ASME Paper 98-GT-431.
9. Johnston, C.A., Bogard, D.G., and McWaters, M.A., 1999, "Highly Turbulent Mainstream Effects on Film Cooling of a Simulated Airfoil Leading Edge," ASME Paper 99-GT-261.
10. Albert, J.E., 2003, "Adiabatic and Overall Effectiveness Measurements of a Forward-Diffused Film Cooling Configuration for a Turbine Blade Leading Edge," M.S. Thesis, The University of Texas at Austin.
11. Giedt, W.H., 1949, "Investigation of Variation of Point Unit Heat Transfer Coefficient Around a Cylinder Normal to an Air Stream," Trans. ASME, Vol 71, pp. 375-381.
12. Terrell, E.J., Mouzon, B.D., and Bogard, D.G., 2005, "Convective Heat Transfer Through Film Cooling Holes of a Gas Turbine Blade Leading Edge," ASME paper 05-GT-69003.
13. Mouzon, B. D., 2005, "Evaluation of performance for leading edge cooling of turbine blades," M.S Thesis, University of Texas.