Time-averaged heat transfer and pressure measurements and comparison with prediction for a two-stage turbineTime-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 percent, 50 percent, 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-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.
Document ID
19930035422
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dunn, M. G. (NASA Lewis Research Center Cleveland, OH, United States)
Kim, J. (Calspan-UB Research Center Buffalo, NY, United States)
Civinskas, K. C. (U.S. Army, Propulsion Directorate; NASA, Lewis Research Center Cleveland, OH, United States)
Boyle, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 92-GT-194
Meeting Information
Meeting: ASME, International Gas Turbine and Aeroengine Congress and Exposition