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Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet EngineThe operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material. Compressor air bleed is required to prevent surge of the outboard compressor in the low engine speed region. The maximum altitude at which the engine was operated without the control was about 66,000 feet at 0.8 flight Mach number and at a reduced engine speed to avoid compressor surge; with the engine control in operation, the altitude operating limit is reduced to approximately 59,000 feet. The maximum altitude at which the engine was started was about 40,000 feet.
Document ID
20090026275
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Wallner, Lewis E. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Saari, Martin J. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
March 31, 1954
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-SE54C31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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