Toward improved film cooling prediction

Journal of Turbomachinery

Volumn 124, Issue 2, 2002, Pages 193-199

  Medic, G ^a   Durbin, P A ^a  

^a Stanford University   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

CALCULATIONS; COOLING; GEOMETRY; HEAT TRANSFER; TURBOMACHINE BLADES;

TURBULENCE MODELS;

GAS TURBINES;

BLADE; FILM COOLING; FLOW FIELD; GAS TURBINE; HEAT TRANSFER; PREDICTION; ROTOR; TURBULENCE;

EID: 0036541962     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1458021     Document Type: Article

References (13)

1. Toward improved prediction of heat transfer on turbine blades
2. On the k-ε stagnation point anomaly
3. Discrete-jet film cooling: A comparison of computational results with experiments
4. Short duration measurements and numerical simulation of heat transfer along the suction side of a film-cooled gas turbine blade
5. Experimental heat transfer investigation around the film-cooled leading edge of a high-pressure gas turbine rotor blade
6. An experimental convective heat transfer investigation around a film-cooled gas turbine blade
7. A detailed analysis of film cooling physics: Part 1 - Streamwise injection with cylindrical holes
8. Effect of coolant temperature and mass flow on film cooling of turbine blades
9. The design of an improved endwall film-cooling configuration
10. Film cooling effectiveness for short film cooling holes fed by a narrow plenum