Accession Number : AD0683285

Title :   EFFECT OF GAS TEMPERATURE DURING THE ACCELERATION OF GAS TURBINE ENGINES ON THE THERMAL STATE OF TURBINE BLADES,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Barskii,I. A.

Report Date : 21 FEB 1968

Pagination or Media Count : 11

Abstract : The acceleration time of a turbocompressor in a twin-shaft gas-turbine engine can be reduced by raising the gas inlet temperature. However, the increase in the inlet temperature may result in compressor surge or overheating of the turbine blades. These effects of the inlet temperature were investigated analytically. The obtained results indicate that during acceleration, the gas inlet temperature has a very small effect on the temperature of the mean cross section of the blade. On the other hand, a 10% rise in the inlet temperature reduces the acceleration time by 25-35%. It is therefore concluded that, in general, the possibility of compressor surge should be the only factor limiting the maximum inlet temperature. (Author)

Descriptors :   (*GAS TURBINES, THERMAL ANALYSIS), (*GAS TURBINE BLADES, ACCELERATION), HEAT TRANSFER, DUCT INLETS, THERMAL CONDUCTIVITY, TEMPERATURE, AXIAL FLOW COMPRESSOR BLADES, HEAT OF COMBUSTION, USSR

Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE