THE STRESSED STATE OF GAS-TURBINE DISKS,

Abstract

A 200 mm profiled turbine disk was studied to determine the effect of heat transfer parameters on stresses. The disk was designed to instanteneously increase the rpm and gas temperature to rated values. The heat transfer coefficient in the flow section was varied, the coolant temperature was 100, 300, and 600 degrees C, and the heat transfer coefficient of the end plane was doubled. Depending on the coolant temperatures at the end planes, the temperature distribution with radius can vary for the same temperature gradient. Stress distribution in the disk depends on the shape of the temperature field. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 21, 1969
Accession Number
AD0694758

Entities

People

  • E. I. Molchanov
  • V. P. Trushechkin

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Coefficients
  • Gas Turbine Rotors
  • Gas Turbines
  • Heat Transfer
  • Heat Transfer Coefficients
  • Isotherms
  • Temperature Gradients
  • Turbines

Readers

  • Combustion and Flow Dynamics.
  • Mechanical Engineering/Mechanics of Materials.