Accession Number : AD0694758

Title :   THE STRESSED STATE OF GAS-TURBINE DISKS,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Molchanov,E. I. ; Trushechkin,V. P.

Report Date : 21 APR 1969

Pagination or Media Count : 9

Abstract : A 200 mm profiled turbine disk was studied to determine the effect of heat transfer parameters on stresses. The disk was designed to instanteneously increase the rpm and gas temperature to rated values. The heat transfer coefficient in the flow section was varied, the coolant temperature was 100, 300, and 600 degrees C, and the heat transfer coefficient of the end plane was doubled. Depending on the coolant temperatures at the end planes, the temperature distribution with radius can vary for the same temperature gradient. Stress distribution in the disk depends on the shape of the temperature field. (Author)

Descriptors :   (*GAS TURBINES, GAS TURBINE ROTORS), (*GAS TURBINE ROTORS, THERMAL STRESSES), HEAT TRANSFER, STRESSES, DEFORMATION, COOLING, THERMAL PROPERTIES, USSR

Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE