Accession Number : AD0700582

Title :   THE TEMPERATURE FIELD OF A TURBINE BLADE WITH TRANSVERSE AIR COOLING,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Lyubchenko,I. S.

Report Date : 20 AUG 1969

Pagination or Media Count : 10

Abstract : The cross section of a turbine blade with a deflector in a uniform gas flow is examined. The cooling air, entering near the root section within the deflector, passes through the slits at the leading edge of the deflector. It then breaks into branches and flows through transverse channels over concave and convex surfaces. Air consumption for cooling the back edge and trough is noted along the blade length. The stagnation temperature of the gas in the boundary layer over the profile and the blade temperature over the wall thickness are considered. The balance equations for a blade element and the air flowing past the element are equated.

Descriptors :   (*TURBINE BLADES, COOLING), GAS FLOW, TEMPERATURE CONTROL, WALLS, MATHEMATICAL PREDICTION, EXPERIMENTAL DATA, CORRELATION TECHNIQUES, BOUNDARY LAYER, DIFFERENTIAL EQUATIONS, USSR

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE