Accession Number : AD0629227

Title :   AN ASYMPTOTE SOLUTION TO THE PROBLEM OF DETERMINING THE TEMPERATURE OF GAS TURBINE BLADES,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Lyubchenko,I. S. ; Tupchiev,V. A.

Report Date : 20 JAN 1966

Pagination or Media Count : 17

Abstract : Problem in current gas turbine construction is that of increasing the working temperature of the gas. As is known, this leads to increased efficiency, and a reduction in the size and weight of gas turbines. However, the design of high temperature gas turbines encounters serious difficulties in connection with the limited capabilities of the metal of elements in the flow-through portion to stand up under increased temperature potentials. The most heavily worked turbine elements are the work blades which operate under conditions of elevated mechanical and temperature stresses. Naturally, when designing a gas turbine it is very important to know how to calculate the temperature field in the blade body taking into account variation along the radius of heat transfer, and of the perimeters and areas of cylindrical cross sections. (Author)

Descriptors :   (*GAS TURBINE BLADES, TEMPERATURE), DETERMINATION, HEAT TRANSFER, USSR

Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE