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Experimental performance and analysis of 15.04-centimeter-tip-diameter, radial-inflow turbine with work factor of 1.126 and thick bladingThe aerodynamic design, the performance, and an internal loss breakdown were examined for a 15.04 cm tip diameter, radial-inflow turbine. The design application was to drive a two stage, 10 to 1 pressure ratio compressor with a mass flow of 0.952 kg/sec and a rotative speed of 70,000 rmp. 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 10000 N/sq m and 322.2 K, respectively. 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.
Document ID
19800024902
Document Type
Technical Publication (TP)
Authors
Mclallin, K. L. (NASA Lewis Research Center Cleveland, OH, United States)
Haas, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
NASA-TP-1730
AVRADCOM-TR-80-09
E-391
Funding Number(s)
PROJECT: RTOP 505-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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