Mainstream aerodynamic effects due to wheelspace coolant injection in a high-pressure turbine stage: Part II - Aerodynamic measurements in the rotational frame

Journal of Turbomachinery

Volumn 123, Issue 4, 2001, Pages 697-703

  McLean, C ^a   Camci, C ^a   Glezer, B ^a  

^a Techkor Instrumentation   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; BOUNDARY LAYER FLOW; COOLANTS; HIGH PRESSURE EFFECTS; NOZZLES; ROTORS;

COOLANT INJECTIONS;

TURBINES;

AERODYNAMICS; COOLANT; GAS TURBINE; HIGH PRESSURE; MEASUREMENT METHOD;

EID: 0035483362     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1397303     Document Type: Article

References (14)

1. Analysis of film cooling and full coverage film cooling of gas turbine blades
2. Aerodynamic aspects of endwall filmc-cooling
3. Film cooling, mass transfer, and flow at the base of a turbine blade
4. Film cooling of the gas turbine endwall by discrete-hole injection
5. Film cooling on a gas turbine blade near the end wall
6. Comparison of visualized turbine secondary flows and measured heat transfer patterns
7. An experimental study of endwall and airfoil surface heat transfer in a large scale turbine blade cascade
8. Impact or rotor-stator interaction on turbine blade film cooling
9. Investigation of three dimensional flow field in a turbine including rotor/ stator interaction
10. Design and development of a turbine research facility to study rotor-stator interaction
11. Distribution of film-cooling effectiveness on a turbine endwall measured using the ammonia and diazo technique