A converging slot-hole film-cooling geometry-Part 1: Low-speed flat-plate heat transfer and loss

Journal of Turbomachinery

Volumn 124, Issue 3, 2002, Pages 453-460

  Sargison, J E ^a   Guo, S M ^a   Oldfield, M L G ^a   Lock, G D ^a   Rawlinson, A J ^a  

^a UNIVERSITY OF TASMANIA   (Australia)

Author keywords

[No Author keywords available]

Indexed keywords

BOUNDARY LAYERS; COOLANTS; COOLING; GEOMETRY; HEAT FLUX; LIQUID CRYSTALS; REMOTE CONSOLES; REYNOLDS NUMBER; ROTORS; TURBOMACHINE BLADES;

ADIABATIC COOLING; FILM-COOLING HOLE GEOMETRY;

HEAT TRANSFER;

FILM COOLING; FLAT PLATE; GEOMETRY; HEAT LOSS; HEAT TRANSFER; TURBINE;

EID: 0036648920     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1459735     Document Type: Article

References (17)

1. A converging slot-hole film-cooling geometry-part 2: Transonic guide vane heat transfer and loss
2. Loss mechanisms in turbomachines
3. The effect of shaping inclined slots on film cooling effectiveness and heat transfer coefficient
4. Heat transfer, adiabatic effectiveness and injectant distributions downstream of a single row and two staggered rows of compound angle film-cooling holes
5. Film cooling with compound angle holes: Heat transfer
6. Film cooling with compound angle holes: Adiabatic effectiveness
7. Heat transfer coefficient measurements of film-cooling holes with expanded exits
8. Adiabatic wall effectiveness measurements of film-cooling holes with expanded exits
9. Flowfield measurements for film-cooling holes with expanded exits
10. Aerodynamic performance of an annular cascade of film cooled nozzle guide vanes under engine representative conditions
11. The variation of heat transfer coefficient, adiabatic effectiveness and aerodynamic loss with film cooling hole shape
12. Definition of heat transfer coefficient in the turbine situation
13. Theory for the use of foreign gas in simulating film cooling
14. Measurement of the temperature field downstream of simulated leading-edge film-cooling holes