Thermal field and flow visualization within the stagnation region of a film-cooled turbine vane

Journal of Turbomachinery

Volumn 124, Issue 2, 2002, Pages 200-206

  Cutbirth, J Michael ^a   Bogard, David G ^a  

^a Carderock Division   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COMPUTATION THEORY; COOLANTS; DOPPLER EFFECT; FLOW VISUALIZATION; JETS; VELOCITY MEASUREMENT;

TURBINE VANE;

TURBINES;

FILM COOLING; FLOW VISUALIZATION; TEMPERATURE DISTRIBUTION; TURBINE; VANE;

EID: 0036541116     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1451086     Document Type: Article

References (16)

1. Performance of a turbine airfoil with multiple film cooling stations Part 1: Heat transfer and film cooling effectiveness
2. Effect of unsteady wake on detailed heat transfer coefficient and film effectiveness distributions for a gas turbine blade
3. Film cooling on a gas turbine rotor blade
4. Mean temperature measurements if jets with a crossflow for gas turbine film cooling applications
5. Measurements in film cooling with lateral injection: Adiabatic effectiveness values and temperature fields
6. Effect of density ratio on the hydrodynamics of film cooling
7. Gas turbine film cooling: Flowfield due to a second row of holes
8. Flow visualization in a linear turbine cascade of high performance turbine blades
9. Flow and heat transfer at the hub endwall of inlet vane passages - Experiments and simulations
10. The influence of curvature on film cooling performance
11. Three component velocity field measurements in the stagnation region of a film cooled turbine vane
12. Film cooling effectiveness in the showerhead region of a gas turbine vane part I: Stagnation region and near-pressure side
13. Film cooling effectiveness in the showerhead region of a gas turbine vane Part II: Stagnation region and near-suction side