EXPERIMENTAL STUDY OF ENDWALL AND AIRFOIL SURFACE HEAT TRANSFER IN A LARGE SCALE TURBINE BLADE CASCADE
Local rates of heat transfer on the endwall, suction, and pressure surfaces of a large scale turbine blade cascade were measured for two inlet boundary layer thicknesses and for a Reynolds number typical of gas turbine engine operation. The accuracy and spatial resolution of the measurements were sufficient to reveal local variations of heat transfer associated with distinct flow regimes and with regions of strong three-dimensional flow. Pertinent results of surface flow visualization and pressure measurements are included. The dominant role of the passage vortex, which develops from the singular separation of the inlet boundary layer, in determining heat transfer at the endwall and at certain regions of the airfoil surface is illustrated. Heat transfer on the passage surfaces is discussed and measurements at airfoil midspan are compared with current finite difference prediction methods.
- Paper for the 12-15 March 1979 Meeting.
American Society of Mechanical EngineersTwo Park Avenue
New York, NY United States 10016-5990
- Graziani, R A
- Blair, M F
- TAYLOR, J R
- Mayle, R E
- Publication Date: 1979
- Features: References;
- Pagination: 11 p.
- TRT Terms: Airfoils; Boundary layer; Gas turbines; Heat transfer; Turbine engines
- Subject Areas: Aviation; Vehicles and Equipment;
- Accession Number: 00301366
- Record Type: Publication
- Source Agency: Engineering Index
- Report/Paper Numbers: 79-GT-99 Conf Paper
- Files: TRIS
- Created Date: Feb 11 1980 12:00AM