Film cooling on a modern HP turbine blade: Part II: Compound-angle round holes

American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI

Volumn 3 B, Issue , 2002, Pages 1095-1101

  Walters, D Keith ^a   Leylek, James H ^a   Buck, Frederick A ^b  

^a AMRL   (United States)

^b GE AVIATION   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COOLANT INJECTION; FILM COOLING; HIGH PRESSURE TURBINE AIRFOIL; NOMINAL DENSITY RATIO; TURBINE BLADE;

AIRFOILS; COMPUTATIONAL METHODS; COOLING; FILMS; HIGH PRESSURE TURBOMACHINERY; MATHEMATICAL MODELS; TRANSONIC FLOW; TURBOMACHINE BLADES; TURBULENCE;

GAS TURBINES;

EID: 0036995188     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.1115/GT2002-30613     Document Type: Conference Paper

References (3)

1. Garg, V.K. and Gaugler, R.E., 1997, "Effect of Velocity and Temperature Distribution at the Hole Exit on Film Cooling of Turbine Blades," Journal of Turbomachinery, Vol. 119, pp. 343-351.
2. Leylek, J., and Zerkle, R., 1994, "Discrete-Jet Film Cooling: A Comparison of computational Results with Experiments," Journal of Turbomachinery, Vol. 116, pp. 358-368.
3. Walters, D., and Leylek, J., 1997, "A Detailed Analysis of Film-Cooling Physics - Part I: Streamwise Injection with Cylindrical Holes," ASME Paper No. 97-GT-269.