Experimental Performance and Analysis of 15.04-Centimeter-Tip-Diameter, Radial-Inflow Turbine with Work Factor of 1.126 and Thick Blading.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER
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The aerodynamic design, the experimental performance, and an internal loss breakdown are presented for a 15.04-cm-tip-diameter, radial-inflow turbine. The design application is to drive a two-stage, 10-to-1 pressure ratio compressor with a mass flow of 0.952 kgsec and a rotative speed of 70,000 rpm. The turbine inlet temperature was 1478 K, and the turbine was designed with blades thick enough for internal cooling passages. The rotor tip diameter was limited to 86 percent of optimum in order to obtain a reduced-tip-speed design. The turbine was fabricated with solid, uncooled blading and tested in air at nominal inlet pressure and temperature of 1.379 x 100,000 Nsq. m and 322.2 K, respectively. Experimental results indicated the turbine total efficiency to be 5.3 points less than design. Analysis of these results has indicated the deficit in performance to be due to stator secondary flow losses, vaneless-space surface friction losses, and trailing-edge wake mixing losses. Author
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