Effects of Temperature Transients at Fan Inlet of a Turbofan EngineNational Aeronautics and Space Administration, Scientific and Technical Information Office, 1977 - Fans (Machinery) - 38 pages |
Common terms and phrases
74 percent 90-percent low-pressure-rotor speed 90-percent N₁ Angular location circumferential and radial circumferential extent compressor distortion limits compressor pressure disturbance compressor stall effects of fan engine inlet exit pres extent of distortion extent transients Fan hub exit Fan inlet pressure fan inlet sector fan inlet temperature Fan tip exit flow control valve Heated sector high-speed valve HPC exit temperature HPC stall Hub radius inlet temperature change inlet temperature rise K per second K/sec left side low-pressure LPC pressure ratio magnitude and rate magnitude of fan milliseconds momentary compressor pressure msec N/cm2 LPC NASA performance and stability Pressure at stations pressure ratio HPC quadrant Radius Tip Mean Rate of fan ratio LPC Reynolds number index rotating stall rotor speed side of compressor stall occurred station 2a steady-state sure ratio temperature rise rate TF30-P-3 turbofan engine thermocouples Tip and mean tip exit temperature total pressure transients at 90-percent Turbojet