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Sensitivity of Turbine Blade Temperatures to Tolerances of Design Variables PUBLIC ACCESS

[+] Author Affiliations
E. S. Hsia

General Electric Co., Evendale, OH

Paper No. 81-GT-90, pp. V003T09A008; 9 pages
doi:10.1115/81-GT-90
From:
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 3: Heat Transfer; Electric Power
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7963-4
  • Copyright © 1981 by ASME

abstract

The General Electric Company in conjunction with the Air Force Aero Propulsion Laboratory is involved in a program to more fully understand air-cooled turbine blade distress mechanisms. As part of this program, the tolerance effects of design parameters on the predicted blade temperature were evaluated. Turbine blade temperature predictions are based on the assumption that all blades conform to the nominal design intent in terms of blade geometry and operating conditions. Since the geometry and operating conditions of each blade may vary from these assumptions, the actual blade life may be significantly different from that calculated, based on the nominal design intent. This study analyzed the blade temperature sensitivity of a single stage high pressure turbine blade to variations in most of the design variables. The effect on blade metal temperature of each variable was assessed individually and the cumulative effect of changing several variables simultaneously was also determined. Finally, an equation was obtained from this study that can be used to predict the cumulative effect on blade temperatures in a given blade by knowing only the single-variable sensitivities.

Copyright © 1981 by ASME
This article is only available in the PDF format.

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