Design and Test of a Small, High Pressure Ratio Radial Turbine PUBLIC ACCESS

[+] Author Affiliations
Anthony C. Jones

Sundstrand Power Systems, San Diego, CA

Paper No. 94-GT-135, pp. V001T01A045; 12 pages
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7883-5
  • Copyright © 1994 by ASME


This paper describes the aerodynamic design and rig test of a radial inflow turbine having a rotor tip diameter of 4.58 inches. The single stage turbine was designed for use in the Sundstrand Power Systems (SPS) T-100 Multipurpose Small Power Unit (MPSPU). The T-100 is a small, single-shaft, simple-cycle gas turbine engine intended for airborne, vehicular, and ground based auxiliary power application. Nominal power output of the engine is 50 hp, with growth capability to 100 hp with minimal modification.

Aggressive specific fuel consumption goals for the engine led to a demanding turbine efficiency target of 87% total to static, referred to exhaust diffuser exit, at an expansion ratio of 5.7:1 and a flow rate of 0.73 lb/s.

Details of the design approach are given, together with test results from the turbodrive rig. The results include overall stage mapping and rotor exit surveys.

Copyright © 1994 by ASME
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