Accession Number : ADA329581

Title :   A Twisted Turbine Blade Analysis for a Gas Turbine Engine

Descriptive Note : Final rept. Sep 96-Feb 97

Corporate Author : ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s) : Korjack, T. A.

PDF Url : ADA329581

Report Date : AUG 1997

Pagination or Media Count : 27

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.

Descriptors :   *GAS TURBINES, *SHEAR STRESSES, *GAS TURBINE BLADES, VIBRATION, STRESS ANALYSIS, STIFFNESS, FLEXURAL STRENGTH, AXIAL LOADS, MOMENT OF INERTIA, BENDING MOMENTS.

Subject Categories : Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE