Accession Number : AD0752676

Title :   Local Heat Transfer of Gas-Turbine Blades on Sections with a Laminar Boundary Layer,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Lebed,N. B.

Report Date : 17 OCT 1972

Pagination or Media Count : 11

Abstract : An approximate relation describing the local intensity of heat transfer in sections of profiles with laminar boundary flow was obtained on the basis of analysis of the integral relation for the thermal boundary layer considering the G. S. Ambrok expression regarding independence of the heat transfer law with respect to the velocity and temperature head gradients. The theoretical solution obtained agrees satisfactorily with the experimental data and is convenient for engineering calculations. (Author)

Descriptors :   (*GAS TURBINE BLADES, HEAT TRANSFER), LAMINAR BOUNDARY LAYER, TURBULENCE, SPECIFIC HEAT, ENTHALPY, LAMINAR FLOW, USSR

Subject Categories : Thermodynamics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE