Cold air test data on the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine were recently collected at NASA Marshall Space Flight Center (MSFC). The turbine is a two-stage reaction machine, which was designed in the early 1970s (Fig. 1a). Overall performance data, static pressures on the first- and second-stage nozzles, and static pressures along the gas path at the hub and tip were gathered and are compared in this paper with various (1-D, quasi 3-D, and 3-D viscous) analysis procedures. The results of each level of analysis is compared to test data to demonstrate the range of applicability for each step in the design process of a turbine.

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