A Twisted Turbine Blade Analysis for a Gas Turbine Engine

Abstract

An analysis of a twisted turbine blade was performed to determine the regions of maximum stress and moment which occur on a typical gas turbine engine under variable revolutions per second. An extension of the Holzer and Myklestad methods was developed to simulate shear and moment effects occurring from the root of the blade to its outermost extremity. Under numerical simulations, shear force and moments of inertia were realized at changing revolutions per minute by solving the Den Hartog twisted blade equations.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1997
Accession Number
ADA329581

Entities

People

  • T. A. Korjack

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • C4I

DTIC Thesaurus Topics

  • Bending Moments
  • Books
  • Engines
  • Equations
  • Frequency
  • Gas Turbines
  • Inertia
  • Military Research
  • Moment Of Inertia
  • New York
  • Resonant Frequency
  • Revolutions
  • Shear Stresses
  • Simulations
  • Turbine Blades
  • Turbines
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Structural Dynamics.