Experimental study on heat transfer of separated impingement jets in short distance
Abstract
In actual cooling construction of turbine blade the relative distance between circular jets c(n)/d(n) is less than 3 and the relative distance of nozzle exit to target surface is also less than 3. But the available empirical formulas were achieved on the basis of a very large range of these geometric parameters. Obviously, these formulas may be inaccurate in the practical narrow range of these parameters, in particular when the temperature of the turbine is very high, and on the surface of the blade exist many rows of film-cooling holes. So an experimental research on the heat transfer of impingement jets has been carried out in the actual range of the geometric parameters, and new empirical formulas which can be applied to the turbine blade of the advanced aeroengine have been derived.
- Publication:
-
Journal of Aerospace Power
- Pub Date:
- April 1993
- Bibcode:
- 1993JAerP...8..165K
- Keywords:
-
- Film Cooling;
- Heat Transfer;
- Jet Impingement;
- Separated Flow;
- Turbine Blades;
- Aircraft Engines;
- Nozzle Geometry;
- Fluid Mechanics and Heat Transfer