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Effects of fan inlet temperature disturbances on the stability of a turbofan engineThe effects of steady-state and time-dependent fan inlet total temperature disturbances on the stability of a TF30-P-3 turbofan engine were determined. Disturbances were induced by a gaseous-hydrogen-fueled burner system installed upstream of the fan inlet. Data were obtained at a fan inlet Reynolds number index of 0.50 and at a low-pressure-rotor corrected speed of 90 percent of military speed. All tests were conducted with a 90 deg extent of the fan inlet circumference exposed to above-average temperatures.
Document ID
19820010348
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Abdelwahab, M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-82699
E-982
Accession Number
82N18222
Funding Number(s)
PROJECT: RTOP 505-32-6A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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