Aerodynamic Design and Verification of a Two-Stage Turbine With a Supersonic First Stage

[+] Author and Article Information
R. L. Binsley, J. L. Boynton

Rockwell International/Rocketdyne Division, Canoga Park, Calif.

J. Eng. Power 100(2), 197-202 (Apr 01, 1978) (6 pages) doi:10.1115/1.3446333 History: Received November 10, 1977; Online July 14, 2010


The detailed aerodynamic design and test verification of a 6000-hp (4474-kW) turbine with a supersonic first stage for an airborne application is described. The 12.3-in. (312.4-mm) pitch diameter turbine is driven by products of hydrazine decomposition at 700 psia (4.826 MPa) and 2110 R (1172 K) with an overall pressure ratio of 41.2. The design of the supersonic nozzles and rotor incorporated improved concepts compared to previously reported designs. Test results show that the predicted performance was verified. The supersonic design concepts described are applicable to other high-pressure ratio designs where maximum efficiency is required.

Copyright © 1978 by ASME
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