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A Computer Model for Gas Turbine Blade Cooling Analysis PUBLIC ACCESS

[+] Author Affiliations
J. C. Han, D. W. Ortman

Texas A&M University, College Station, TX

C. P. Lee

Professional Engineer, Cincinnati, OH

Paper No. 82-JPGC-GT-6, pp. V001T01A006; 7 pages
doi:10.1115/82-JPGC-GT-6
From:
  • 1982 Joint Power Generation Conference: GT Papers
  • 1982 Joint Power Generation Conference: GT Papers
  • Denver, Colorado, USA, October 17–21, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7937-5
  • Copyright © 1982 by ASME

abstract

A computer model for gas turbine blade cooling analysis has been developed. The finite difference technique over the chord and span of the blade is employed. A flow balance and an energy balance program are included in the model. The model is capable of predicting cooling flow characteristics (mass flow rate and internal pressure distribution) and metal temperature profiles of multipass coolant passages in rotating blades with local film cooling. The paper first presents the analytical model of coolant flow and heat transfer, then the computer program is discussed. Finally, the computed results of a sample blade at engine conditions is presented and discussed.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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