Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment
Royce D. Moore, Walter Martin Osborn, United States. National Aeronautics and Space Administration, Lewis Research Center
National Aeronautics and Space Administration, 1977 - Technology & Engineering - 24 pages
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0.140 centimeter Reading 061 centimeter Reading 8-8 at design Adiabatic efficiency kg/sec assumed operating line blade tip clearance centimeter Reading Rotative CLEARANCE ON OVERALL clearance was increased clearances from 0.061 closed skewed slots closed-skewed-slot cm Figure decreased with increasing design speed Airflow Effects of rotor-blade EFFECTS OF TIP efficiency decreased Figure 11 Four nominal nonrotating increasing clearance increasing tip clearance kilograms per second Lewis Research Center margin was obtained N/cm nominal nonrotating rotor Nominal nonrotating tip nominal tip clearances nonrotating rotor blade nonrotating tip clearance open skewed slots overall performance peak efficiency percent of design PERFORMANCE OF FAN Performing Organization plenum chamber Pressure ratio Temperature rake ratio Adiabatic efficiency ratio and efficiency ratio Temperature ratio Reading Rotative speed Rotor blade tip rotor tip rotor-blade tip clearance shown in figure stage was tested stall condition stall line stall point stator TABLE Temperature ratio Adiabatic test stage thermocouple total-temperature transonic fan stage