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Time-Averaged Heat Transfer and Pressure Measurements and Comparison With Prediction for a Two-Stage Turbine PUBLIC ACCESS

[+] Author Affiliations
M. G. Dunn, J. Kim

Calspan-UB Research Center, Buffalo, NY

K. C. Civinskas

Lewis Research Center, Cleveland, OH

R. J. Boyle

NASA Lewis Research Center, Cleveland, OH

Paper No. 92-GT-194, pp. V004T09A011; 13 pages
doi:10.1115/92-GT-194
From:
  • ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Cologne, Germany, June 1–4, 1992
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7896-5
  • Copyright © 1992 by ASME

abstract

Time-averaged Stanton number and surface-pressure distributions are reported for the first-stage vane row and the first-stage blade row of the Rocketdyne Space Shuttle Main Engine two-stage fuel-side turbine. These measurements were made at 10%, 50%, and 90% span on both the pressure and suction surfaces of the component. Stanton-number distributions are also reported for the second-stage vane at 50% span. A shock tube is used as a short-duration source of heated and pressurized air to which the turbine is subjected. Platinum thin-film pages are used to obtain the heat-flux measurements and miniature silicone-diaphragm pressure transducers are used to obtain the surface pressure measurements. The first-stage vane Stanton number distributions are compared with predictions obtained using a quasi-3D Navier-Stokes solution and a version of STAN5. This same N-S technique was also used to obtain predictions for the first blade and the second vane.

Copyright © 1992 by ASME
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