Effects of temperature transients at fan inlet of a turbofan engine
Mahmood Abdelwahab, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1977 - Technology & Engineering - 38 pages
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180°-circumferential-extent transient 74 percent 90-percent low-pressure-rotor speed Angular location circumferential and radial circumferential extent compressor distortion limits compressor pressure disturbance compressor stall effects of fan engine response extent of distortion extent transients fan inlet Reynolds fan inlet sector fan inlet temperature flow control valve heated fan inlet high-speed valve history of engine HPC exit HPC stall hydrogen burner system inlet Reynolds number inlet temperature change inlet temperature rise inlet temperature transients instantaneous temperature left side Lewis Research Center low-pressure magnitude and rate magnitude of fan milliseconds momentary compressor pressure msec NASA parameters during 180°-circumferential-extent perature performance and stability pressure ratio Pressures at stations prior to compressor probe quadrants Rate of fan rate of temperature Reynolds number index rotating stall rotor speed side of compressor stall occurred station 2a temperature rise rate TF30-P-3 turbofan engine thermocouples time-dependent temperature distortion total pressure total temperature distortion transients at 90-percent Turbojet