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Effect of steady-state temperature distortion and combined distortion on inlet flow to a turbofan engineFlow angle, static pressure, total temperature and total pressure were measured in the inlet duct upstream of a turbofan engine operating with temperature distortion or combined pressure-temperature distortion. Such measurements are useful in the evaluation of analytical models of inlet distortion. A rotating gaseous-hydrogen burner and a circumferential 180 degrees-extent screen configuration mounted on a rotatable assembly generated the distortions. Reynolds number index was maintained at 0.5 and engine corrected low-rotor speeds were held at 6000 and 8600 rpm. The measurements showed that at the entrance to the engine, flow angle was largest in the hub region. As flow approached the engine, yaw angle (circumferential variation) increased and pitch angle (radial variation) decreased. The magnitude of static-pressure distortion measured along the inlet-duct and extended bullet nose walls increased exponentially as flow approached the engine.
Document ID
19790022016
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Soeder, R. H. (NASA Lewis Research Center Cleveland, OH, United States)
Bobula, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-143
NASA-TM-79237
Accession Number
79N30187
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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