Techniques for obtaining detailed heat transfer coefficient measurements within gas turbine blade and vane cooling passages
Abstract
Techniques developed jointly by Rolls-Royce Bristol and Oxford University for determining detailed heat transfer distributions inside turbine blade and vane cooling passages are reviewed. Use is made of a low temperature phase change paint to map the heat flux distributions within models of the cooling passages; the paints change from an opaque coating to a clear liquid at a well-defined melting point. In this way the surface temperature history of a model subjected to transient convective heating is recorded. The heat transfer coefficient distribution is deduced from this history using a transient conduction analysis within the model. Results are presented on detailed heat transfer coefficient distributions within a variety of cooling passages; and data obtained from a comprehensive study of a typical engine multipass cooling geometry are examined.
- Publication:
-
28th International Gas Turbine Conference and Exhibit
- Pub Date:
- March 1983
- Bibcode:
- 1983gatu.confR....C
- Keywords:
-
- Cooling Systems;
- Gas Turbine Engines;
- Heat Transfer Coefficients;
- Turbine Blades;
- Convective Heat Transfer;
- Surface Temperature;
- Test Facilities;
- Vanes;
- Fluid Mechanics and Heat Transfer