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Compressor Stability Enhancement Using Discrete Tip InjectionMass injection upstream of the tip of a high-speed axial compressor rotor is a stability enhancement approach known to be effective in suppressing small in tip-critical rotors. This process is examined in a transonic axial compressor rotor through experiments and time-averaged Navier-Stokes CFD simulations. Measurements and simulations for discrete injection are presented for a range of injection rates and distributions of injectors around the annulus. The simulations indicate that tip injection increases stability by unloading the rotor tip and that increasing injection velocity improves the effectiveness of tip injection. For the tested rotor, experimental results demonstrate that at 70 percent speed the stalling flow coefficient can be reduced by 30 percent using an injected mass- flow equivalent to 1 percent of the annulus flow. At design speed, the stalling flow coefficient was reduced by 6 percent using an injected mass-fiow equivalent to 2 percent of the annulus flow. The experiments show that stability enhancement is related to the mass-averaged axial velocity at the tip. For a given injected mass-flow, the mass-averaged axial velocity at the tip is increased by injecting flow over discrete portions of the circumference as opposed to full-annular injection. The implications of these results on the design of recirculating casing treatments and other methods to enhance stability will be discussed.
Document ID
20010092189
Acquisition Source
Glenn Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Suder, Kenneth L.
(NASA Glenn Research Center Cleveland, OH United States)
Hathaway, Michael D.
(Army Research Lab. Cleveland, OH United States)
Thorp, Scott A.
(NASA Glenn Research Center Cleveland, OH United States)
Strazisar, Anthony J.
(NASA Glenn Research Center Cleveland, OH United States)
Bright, Michelle B.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
January 21, 2001
Publication Information
Publication: Transactions of the ASME
Volume: 123
Subject Category
Aircraft Propulsion And Power
Distribution Limits
Public
Copyright
Other

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