Results from a series of experiments to investigate whether centrifugal compressor stability could be improved by injecting air through the diffuser hub surface are reported. The research was conducted in a 4:1 pressure ratio centrifugal compressor configured with a vane-island diffuser. Injector nozzles were located just upstream of the leading edge of the diffuser vanes. Nozzle orientations were set to produce injected streams angled at 0, and degrees relative to the vane mean camber line. Several injection flow rates were tested using both an external air supply and recirculation from the diffuser exit. Compressor flow range did not improve at any injection flow rate that was tested, and generally diminished as injection rate increased. Compressor flow range did improve slightly at zero injection due to the flow resistance created by injector openings on the hub surface. Resistance and flow range both increased as the injector orientation was turned toward radial. Leading edge loading and semivaneless space diffusion showed trends that are similar to those reported earlier from shroud surface experiments that did improve compressor range. Opposite trends are seen for hub injection cases where compressor flow range decreased. The hub injection data further explain the range improvement provided by shroud-side injection and suggest that stability factors cited in the discussion of shroud surface techniques are valid. The results also suggest that a different application of hub-side techniques may produce a range improvement in centrifugal compressors.
Skip Nav Destination
Article navigation
January 2005
Technical Papers
Experimental Investigation of Diffuser Hub Injection to Improve Centrifugal Compressor Stability
Gary J. Skoch
Gary J. Skoch
U. S. Army Research Laboratory, Glenn Research Center, Cleveland, OH 44135
Search for other works by this author on:
Gary J. Skoch
U. S. Army Research Laboratory, Glenn Research Center, Cleveland, OH 44135
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF TURBOMACHINERY. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Vienna, Austria, June 13–17, 2004, Paper No. 2004-GT-53618. Manuscript received by IGTI, October 1, 2003; final revision, March 1, 2004. IGTI Review Chair: A. J. Strazisar.
J. Turbomach. Jan 2005, 127(1): 107-117 (11 pages)
Published Online: February 9, 2005
Article history
Received:
October 1, 2003
Revised:
March 1, 2004
Online:
February 9, 2005
Citation
Skoch, G. J. (February 9, 2005). "Experimental Investigation of Diffuser Hub Injection to Improve Centrifugal Compressor Stability ." ASME. J. Turbomach. January 2005; 127(1): 107–117. https://doi.org/10.1115/1.1812779
Download citation file:
Get Email Alerts
Related Articles
Flow Control of Rotating Stall in a Radial Vaneless Diffuser
J. Fluids Eng (June,2001)
Experimental Investigation of Centrifugal Compressor Stabilization Techniques
J. Turbomach (October,2003)
Backward Traveling Rotating Stall Waves in Centrifugal Compressors
J. Turbomach (January,2004)
Related Proceedings Papers
Related Chapters
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression Systems: A Practical Approach, Second Edition
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression System: A Practical Approach, Third Edition
Stability and Range
Design and Analysis of Centrifugal Compressors