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 percent 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.

1.
Dawes, W., 1988, “Development of a 3D Navier–Stokes Solver for Application to All Types of Turbomachinery,” ASME Paper No. 88-GT-70.
2.
Napier, J. C., and Thompson, R. G., 1988, “T-100 Multipurpose Power Unit: Technology for the Next Generation Auxiliary Power Units,” SAE Paper No. 881501.
3.
Napier, J. C., Thompson, R. G., and Rodgers, C., 1989, “Development Test Status T-100 Multipurpose Small Power Unit,” ASME Paper No. 89-GT-117.
4.
Napier, J. C., 1991, “Development of T-100 Multipurpose Small Power Unit,” ASME Paper No. 91-GT-327.
5.
Rodgers, C., 1966, “Efficiency and Performance Characteristics of Radial Turbines,” SAE Paper No. 660754.
6.
Thompson, R. G., and Parker, S. D., 1988, “Technical Approach for a Multipurpose Small Power Unit,” ASME Paper No. 88-GT-262.
7.
USAARTA (AVSCOM), 1986, “T-100 Multipurpose Small Power Unit,” Aviation Applied Technology Directorate, Contract No. DAAJ02-86-C-0007.
This content is only available via PDF.
You do not currently have access to this content.