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

[+] Author and Article Information
M. G. Dunn, J. Kim

Calspan-UB Research Center, Buffalo, NY 14225

K. C. Civinskas

U.S. Army Propulsion, Directorate—AVSCOM

R. J. Boyle

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 116(1), 14-22 (Jan 01, 1994) (9 pages) doi:10.1115/1.2928270 History: Received February 17, 1992; Online June 09, 2008


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 percent span on both the pressure and suction surfaces of the component. Stanton-number distributions are also reported for the second-stage vane at 50 percent 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 gages 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-three dimensional 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 © 1994 by The American Society of Mechanical Engineers
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