A description is given of an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gages painted on a blade made of machinable glass ceramic. Free stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated.
|Original language||English (US)|
|Journal||[No source information available]|
|Publication status||Published - 1985|
All Science Journal Classification (ASJC) codes
- Mechanical Engineering