DESIGN AND EVALUATION OF A HIGH-TEMPERATURE RADIAL TURBINE
Final rept. 18 Jul 1967-30 May 1968 on Phase 1
PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER
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The report describes the work accomplished in the first phase of a two-phase, two-year program that involves the design and testing of a single- stage, high-work radial inflow turbine. This turbine will be typical of one required for advanced gas turbine engines employing high cycle pressure ratios and high turbine inlet temperatures. The objectives of Phase I were to establish a preliminary turbine design, to confirm the preliminary design through cold-flow tests, and to conduct a fabrication study. The Phase I final preliminary turbine design is the result of iterative aerodynamic-structural- heat transfer analyses. The final selections of number of nozzle vanes, number of rotor blades and rotor cooling air ejection method were confirmed and supported by cold-flow tests. The fabrication study showed some material property problems which require additional investigation.
- Jet and Gas Turbine Engines