TIME-AVERAGED HEAT-TRANSFER AND PRESSURE MEASUREMENTS AND COMPARISON WITH PREDICTION FOR A 2-STAGE TURBINE

Time-averaged Stanton number and surface-pressure distributions are re ported for the first-stage vane row and the first-stage blade row of t he Rocketdyne Space Shuttle Main Engine two-stage fuel-side turbine. T hese measurements were made at 10, 50, and 90 percent span on both the pressure and suction surfaces of the component. Stanton-number distri butions 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 pressu rized air to which the turbine is subjected. Platinum thin-film gages are used to obtain the heat-flux measurements and miniature silicone-d iaphragm pressure transducers are wed to obtain the surface pressure m easurements. The first-stage vane Stanton number distributions are com pared with predictions obtained using a quasi-three dimensional Navier -Stokes solution and a version of STAN5. This same N-S technique was a lso used to obtain predictions for the first blade and the second vane .