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Turbofan compressor dynamics during afterburner transientsThe effects of afterburner light-off and shut-down transients on the compressor stability are investigated. The reported experimental results are based on detailed high response pressure and temperature measurements on the TF30-P-3 turbofan engine. The tests were performed in an altitude test chamber simulating high altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shutdown transient the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
Document ID
19760018095
Document Type
Conference Paper
Authors
Kurkov, A. P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 8, 2013
Publication Date
April 1, 1976
Publication Information
Publication: AGARD Unsteady Phenomena in Turbomachinery
Subject Category
AIRCRAFT PROPULSION AND POWER
Distribution Limits
Public
Copyright
Other

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