Effect of a reduction in blade thickness on performance of a single-stage 20.32-centimeter mean-diameter turbine

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National Aeronautics and Space Administration, 1973 - Technology & Engineering - 24 pages
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As part of a program to reduce the manufacturing costs of a small gas-turbine engine, the turbine blading was reduced in thickness to facilitate coining. Tests were made to determine the effect of this modification on turbine performance. The working fluid was air at nominal inlet total conditions of 535 deg F and 20.0 psia. Performance results are presented and compared for four stator-rotor combinations in terms of equivalent torque, mass flow, and efficiency at equivalent design speed and at inlet-total to exit-static pressure ratios of 1.8 to 3.8

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