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

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)

Document Details

Document Type
Technical Report
Publication Date
Oct 17, 1972
Accession Number
AD0752676

Entities

People

  • N. B. Lebed

Organizations

  • National Air and Space Intelligence Center

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Experimental Data
  • Gas Turbine Blades
  • Gas Turbines
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Rotor Blades (Turbomachinery)
  • Thermal Boundary Layer
  • Turbine Blades
  • Turbines
  • Turbomachinery

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.