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Memorandum reports effects of nozzle shape and blade design on pressure loss in turbine systems, suggesting performance enhancements.
This Memorandum presents the results of pressure loss tests made to date on a cold-air, low-pressure, rig simulating a segment of a tip turbine stator assembly and supply duct, and characterized by flat-plate nozzle blades. A range of pitch/chord ratios has been tested, and the effects on performance of the nozzle shape and blade trailing edge thickness have been briefly investigated.
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R.W. Bassett (1960) studied this question.
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