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Experimental Measurement and CFD Prediction of Heat Transfer to a Nozzle Guide Vane FREE

[+] Author Affiliations
Trevor J. Kirsten, Andreas M. Lippert

CSIR, Aerotek, Pretoria, South Africa

Glen C. Snedden, Graham D. J. Smith

University of Natal, Durban, South Africa

Paper No. 96-GT-237, pp. V004T09A034; 6 pages
doi:10.1115/96-GT-237
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7875-0
  • Copyright © 1996 by ASME

abstract

The determination of aerothermal loading plays a vital role in any performance or structural investigation of turbine hot-end components during both the design and in-service phases. This investigation considers the measurement and prediction of heat transfer on a nozzle guide vane in a linear cascade. The experimental method is based on a transient approach and requires that the gas and blade have the correct temperature difference. In this study the transient technique is facilitated by maintaining a constant external gas flow in a closed circuit cascade facility and moving a cooled MACOR blade rapidly into the cascade, displacing an aluminium dummy blade. For a short period of time the correct temperature ratio exists between the gas and blade. It is during this period that the change in the thin-film resistance is measured, which is transformed to represent surface heat transfer. The experimental data is compared to an analytical prediction using an Euler code for the bulk flow solution and a boundary layer code for surface heat transfer. The boundary layer code includes the effects of turbulence in the boundary layer, and the transitional nature of the boundary layer flow is also captured. The accuracy associated with the levels of heat transfer is shown to be good for two exit Mach numbers, although some variation is evident towards the trailing edge of the suction surface. The laminar, transitional and turbulent regions of the boundary layer show good correspondence.

Copyright © 1996 by ASME
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