Accession Number : AD0670096

Title :   AN ASYMPTOTIC METHOD FOR COMPUTING THE TEMPERATURE FIELD OF GAS TURBINE MOVING BLADES (K ASIMPTOTICHESKOMU METODU RASCHETA TEMPERATURNOGO POLYA RABOCHIKH LOPATOK GAZOVYKH TURBIN),

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

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

Report Date : 18 AUG 1967

Pagination or Media Count : 17

Abstract : An approximate solution was obtained for the boundary problem of unidimensional stationary heat conductivity. This solution enables computations to be carried out with a high degree of accuracy. The working blade of a turbine in a non-uniform temperature gas field is considered, on the assumption that the blade temperature through the section and along the profile contour (at any radius) is held constant, and that the heat emission factor along the contour of each cylindrical section is also constant. The heat balance equation is converted into a differential equation and boundary conditions are assigned. Formulae are derived for the solution of the boundary problem and, in the second section of the article, an effort is made to represent this solution in an asymptotic form. A final asymptotic expression is thus obtained and estimated, with an example given illustrating how it can be employed in a practical calculation of blade temperature fields. (Author)

Descriptors :   (*GAS TURBINE BLADES, TEMPERATURE), THERMAL CONDUCTIVITY, ASYMPTOTIC SERIES, APPROXIMATION(MATHEMATICS), HEAT TRANSFER, EQUATIONS OF STATE, BOUNDARY VALUE PROBLEMS, USSR

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE