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

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)

Document Details

Document Type
Technical Report
Publication Date
Mar 12, 1971
Accession Number
AD0726601

Entities

People

  • Yu. M. Matsevityi

Organizations

  • National Air and Space Intelligence Center

Tags

DTIC Thesaurus Topics

  • Energy Generators
  • Energy Systems
  • Gas Turbines
  • Generators
  • Integrators
  • Isotherms
  • Mechanical Equipment
  • Rotor Blades (Turbomachinery)
  • Temperature Gradients
  • Turbine Blades
  • Turbines
  • Turbomachinery

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.
  • Structural Dynamics.