Effect of casing treatment on overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5
Walter M. Osborn, Royce D. Moore, United States. National Aeronautics and Space Administration, Lewis Research Center
National Aeronautics and Space Administration, 1977 - Technology & Engineering - 20 pages
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100 percent Adiabatic speed kg/sec Airflow axial length backing plate centimeter closed slots design speed effect fan performance flow of 29 Flow path flow to lower forward skewed slots front portion kg/sec ratio ratio kilograms per second Lewis Research Center lower flows meters per second midportion moved the stall N/cm NASA TM obtained open slotted configurations opened skewed slot outlet overall performance part-speed peak efficiency percent of design percentage point less Performing Organization plenum tank presented in figure Pressure Temperature Adiabatic ratio ratio efficiency Reading Percent Flow reference solid rotor blade fig rotor tip fig short slots shown in figure skewed slot configuration Skewed slot insert skewed slots Reading slots Reading Percent slotted configurations moved speed kg/sec ratio stage was designed stall flow stall line stall margin static pressure stator teardrop configuration Teardrop Insert Temperature Adiabatic speed test stage thermocouple tip region TIP SOLIDITY tip speed total-temperature TRANSONIC FAN STAGE