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Models for the Representation of Turbomachine Blades During Temperature Transients FREE

[+] Author Affiliations
N. R. L. Maccallum

University of Glasgow, Glasgow, Scotland

Paper No. 76-GT-23, pp. V01AT01A023; 8 pages
doi:10.1115/76-GT-23
From:
  • ASME 1976 International Gas Turbine and Fluids Engineering Conference
  • Volume 1A: General
  • New Orleans, Louisiana, USA, March 21–25, 1976
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7974-0
  • Copyright © 1976 by ASME

abstract

When the operating conditions of turbomachinery are changed, as when a gas turbine is accelerated, heat is transferred from or to the various components of the machine. One of the significant heat transfers is with the blading. Several simple models for the blade and platform arrangement are compared. Satisfactory representation is obtained from a simple eight-element Finite Difference Model and from a Revised Fin Model. Computer running times are similar, but the latter allows more convenient hand calculations and is more suitable when predicting the thermal response of casings or disks to which the blades are attached.

Copyright © 1976 by ASME
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