Thermo-Mechanical Stress Analysis of Advanced Turbine Blade Cooling Configuration.

Abstract

A thermo-mechanical stress analysis capability, based on the Boundary Integral Equation Method (BIE) is developed and described. The capability is used to provide a thermoelastic analysis of stress in the vicinity of cooling holes in turbojet blades with transpiration or film cooling. Details involved in the formulation, numerical procedures, mathematical modelling, and data from solved problems are presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1979
Accession Number
ADA074098

Entities

People

  • D. J. Shippy
  • F. J. Rizzo

Organizations

  • University of Kentucky

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Cartesian Coordinates
  • Centrifugal Fields
  • Computer Programs
  • Cooling
  • Engineering
  • Equations
  • Heat Transfer
  • Integral Equations
  • Materials
  • Mechanics
  • Stress Analysis
  • Stresses
  • Three Dimensional
  • Turbines
  • Turbojet Engines

Readers

  • Combustion and Flow Dynamics.
  • Structural Health Monitoring of Composite Structures.
  • Wave Propagation and Nonlinear Chaotic Dynamics.