Effect of blade leading edge thickness on cavitation performance of 80.6 ̊helical inducer in hydrogen
Royce D. Moore, Phillip R. Meng, United States. National Aeronautics and Space Administration, Lewis Research Center
National Aeronautics and Space Administration, 1970 - Technology & Engineering - 21 pages
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11 Flow coefficient blade leading edge booster rotor cavitation parameters cavitation performance consistent trend decreased with increasing ducer Effect of blade effects of cavitation entire flow range equation fluid velocity head function of flow head-rise head-rise-coefficient ratio helical inducer identical in design increasing flow coefficient increasing liquid temperature Inducer C ref inducer in hydrogen Inducer net positive inducer operated inducers were tested inlet line K-factor leading edge thickness Lewis Research Center line inlet liquid hydrogen liquid-volume ratio lowest for inducer Meng NASA TN Nominal hydrogen temperature noncavitating head rise Noncavitating performance Number parameters that qualitatively performance of 80.6 performance of inducers positive suction head psi N/cm2 qualitatively evaluate reference value required NPSH research tank rotative speed Royce shown in figure smallest for inducer speed of 30 suction head NPSH tank pressure thickest blade leading THICKNESS ON CAVITATION thinnest Three different 80 three inducers values of NPSH vapor bulb Venturi