Abstract
This paper describes 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 gauges 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. Heat transfer modifications due to incidence angle variations were interpreted with the aid of inviscidflow calculation methods.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1016-1021 |
| Number of pages | 6 |
| Journal | Journal of Engineering for Gas Turbines and Power |
| Volume | 107 |
| Issue number | 4 |
| DOIs | |
| State | Published - Jan 1 1985 |
All Science Journal Classification (ASJC) codes
- Nuclear Energy and Engineering
- Fuel Technology
- Aerospace Engineering
- Energy Engineering and Power Technology
- Mechanical Engineering