Document ID: 19930035422 A (93A19419) File Series: Open Literature

Report Number: ASME PAPER 92-GT-194

Sales Agency & Price: Issuing Activity

Authors:

Dunn, M. G. (NASA Lewis Research Center), Kim, J. (Calspan-UB Research Center), Civinskas, K. C. (U.S. Army, Propulsion Directorate), Boyle, R. J. ( NASA, Lewis Research Center)

Published: Jun 01, 1992

Corporate Source: NASA Lewis Research Center (Cleveland, OH, United States)

Pages: 13

Contract Number: None

NASA Subject Category: FLUID MECHANICS AND HEAT TRANSFER

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 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.

Major Subject Terms:

HEAT TRANSFER PERFORMANCE

PREDICTION PRESSURE MEASUREMENT

STANTON NUMBER TWO STAGE TURBINES

Minor Subject Terms:

METAL FILMS PLATINUM PRESSURE

DISTRIBUTION SPACE SHUTTLE MAIN

ENGINE THIN FILMS

Language Note: English

Notes: ASME, International Gas Turbine and Aeroengine Congress and Exposition, 37th, Cologne, Germany, June 1-4, 1992 ASME, International Gas Turbine and Aeroengine Congress and Exposition Cologne June 1-4, 1992

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