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Experimental evaluation of a TF30-P-3 turbofan engine in an altitude facility : Effect of steady-state temperature distortion

Author
Braithwaite, W. M.
Published
Nov 1, 1973.
Physical Description
1 electronic document
Online Version

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Summary
The effects of circumferential distortion of the total temperature entering 25, 50, and 75 percent of the inlet circumferential annulus of a turbofan engine were determined. Complete compressor stall resulted from distortions of from 14 to 20 percent of the face averaged temperature. Increasing the temperature level in one sector resulted in that sector moving toward stall by decreasing the equivalent rotor speeds while the pressure ratio remained approximately constant. Stall originated as a rotating zone in the low-pressure compressor which resulted as a terminal stall in the high-pressure compressor. Decreasing the Reynolds number index to 0.25 from 0.5 reduced the required distortion for stall by 50 percent for the conditions investigated.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19740002609.
Accession ID: 74N10722.
NASA-TM-X-2921.
E-7499.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15746970