Accession Number : AD0726601

Title :   Investigation of the Stressed State of Cooled Turbine Blades of the Shell Type,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Matsevityi,Yu. M.

Report Date : 12 MAR 1971

Pagination or Media Count : 11

Abstract : A description is given of a technique for determining the temperature field of internally cooled blades of gas turbines. The technique uses an integrator in combination with a coordinating device which measures the temperature gradient in the blade body during cooling. Approximate values of the normal stresses developing in the turbine blades during cooling can be obtained by this technique. (Author)

Descriptors :   (*TURBINE BLADES, THERMAL STRESSES), (*GAS TURBINES, TURBINE BLADES), COOLING, REFRACTORY COATINGS, TEMPERATURE, THERMAL ANALYSIS, TEST METHODS, USSR

Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE