Reverse thrust performance of the QCSEE variable pitch turbofan engineResults of steady-state reverse and forward-to-reverse thrust transient performance tests are presented. The original QCSEE 4-segment variable fan nozzle was retested in reverse and compared with a continuous, 30-deg half-angle conical exlet. Data indicated that the significantly more stable, higher pressure recovery flow with the fixed 30-deg exlet resulted in lower engine vibrations, lower fan blade stress and approximately a 20% improvement in reverse thrust. Objective reverse thrust of 35% of takeoff thrust was reached. Thrust response of less than 1.5 sec was achieved for the approach and the takeoff-to-reverse thrust transients.
Document ID
19810049802
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Samanich, N. E. (NASA Lewis Research Center Cleveland, OH, United States)
Reemsnyder, D. C. (NASA Lewis Research Center Cleveland, OH, United States)
Bloomer, H. E. (NASA Lewis Research Center Cleveland, Ohio, United States)