Mass injection upstream of the tip of a high-speed axial compressor rotor is a stability enhancement approach known to be effective in suppressing stall 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 massflow equivalent to 1 percent of the annulus flow. At design speed, the stalling flow coefficient was reduced by 6 percent using an injected massflow 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 massflow, 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.
Skip Nav Destination
Article navigation
January 2001
Technical Papers
Compressor Stability Enhancement Using Discrete Tip Injection
Kenneth L. Suder,
Kenneth L. Suder
NASA Glenn Research Center, Cleveland, OH 44135
Search for other works by this author on:
Michael D. Hathaway,
Michael D. Hathaway
US Army Vehicle Technology Directorate, Cleveland, OH 44135
Search for other works by this author on:
Scott A. Thorp,
Scott A. Thorp
NASA Glenn Research Center, Cleveland, OH 44135
Search for other works by this author on:
Anthony J. Strazisar,
Anthony J. Strazisar
NASA Glenn Research Center, Cleveland, OH 44135
Search for other works by this author on:
Michelle B. Bright
Michelle B. Bright
NASA Glenn Research Center, Cleveland, OH 44135
Search for other works by this author on:
Kenneth L. Suder
NASA Glenn Research Center, Cleveland, OH 44135
Michael D. Hathaway
US Army Vehicle Technology Directorate, Cleveland, OH 44135
Scott A. Thorp
NASA Glenn Research Center, Cleveland, OH 44135
Anthony J. Strazisar
NASA Glenn Research Center, Cleveland, OH 44135
Michelle B. Bright
NASA Glenn Research Center, Cleveland, OH 44135
Contributed by the International Gas Turbine Institute and presented at the 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000. Manuscript received by the International Gas Turbine Institute February 2000. Paper No. 2000-GT-650. Review Chair: D. Ballal.
J. Turbomach. Jan 2001, 123(1): 14-23 (10 pages)
Published Online: February 1, 2000
Article history
Received:
February 1, 2000
Citation
Suder, K. L., Hathaway, M. D., Thorp , S. A., Strazisar , A. J., and Bright, M. B. (February 1, 2000). "Compressor Stability Enhancement Using Discrete Tip Injection ." ASME. J. Turbomach. January 2001; 123(1): 14–23. https://doi.org/10.1115/1.1330272
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
The Influence of Dump Gap on External Combustor Aerodynamics at High Fuel Injector Flow Rates
J. Eng. Gas Turbines Power (May,2009)
Rotor-Stator Interactions in a Four-Stage Low-Speed Axial Compressor—Part II: Unsteady Aerodynamic Forces of Rotor and Stator Blades
J. Turbomach (October,2004)
Backward Traveling Rotating Stall Waves in Centrifugal Compressors
J. Turbomach (January,2004)
Stability Enhancement by Casing Grooves: The Importance of Stall Inception Mechanism and Solidity
J. Turbomach (March,2012)
Related Proceedings Papers
Related Chapters
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Stability and Range
Design and Analysis of Centrifugal Compressors
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential