This is Part 2 of an examination of the influence of inlet flow conditions on the performance and operating range of centrifugal compressor vaned diffusers. The paper describes tests of a straight-channel type diffuser, sometimes called a wedge-vane diffuser, and compares the results with those from the discrete-passage diffusers described in Part 1. Effects of diffuser inlet Mach number, flow angle, blockage, and axial flow nonuniformity on diffuser pressure recovery and operating range are addressed. The straight-channel diffuser investigated has 30 vanes and was designed for the same aerodynamic duty as the discrete-passage diffuser described in Part 1. The ranges of the overall pressure recovery coefficients were 0.50–0.78 for the straight-channel diffuser and 0.50–0.70 for the discrete-passage diffuser, except when the diffuser was choked. In other words, the maximum pressure recovery of the straight-channel diffuser was found to be roughly 10 percent higher than that of the discrete-passage diffuser investigated. The two types of diffuser showed similar behavior regarding the dependence of pressure recovery on diffuser inlet flow angle and the insensitivity of the performance to inlet flow field axial distortion and Mach number. The operating range of the straight-channel diffuser, as for the discrete-passage diffusers, was limited by the onset of rotating stall at a fixed momentum-averaged flow angle into the diffuser, which was for the straight-channel diffuser, The background, nomenclature, and description of the facility and method are all given in Part 1. [S0889-504X(00)00201-4]
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January 2000
Technical Papers
Effects of Inlet Flow Field Conditions on the Performance of Centrifugal Compressor Diffusers: Part 2—Straight-Channel Diffuser
S. Deniz,
S. Deniz
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139
11
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E. M. Greitzer,
E. M. Greitzer
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139
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N. A. Cumpsty
N. A. Cumpsty
Whittle Laboratory, Department of Engineering, Cambridge University, Cambridge CB3 0DY, United Kingdom
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S. Deniz
11
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139
E. M. Greitzer
Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139
N. A. Cumpsty
Whittle Laboratory, Department of Engineering, Cambridge University, Cambridge CB3 0DY, United Kingdom
Contributed by the International Gas Turbine Institute and presented at the 43rd International Gas Turbine and Aeroengine Congress and Exhibition, Stockholm, Sweden, June 2–5, 1998. Manuscript received by the International Gas Turbine Institute February 1998. Paper No. 98-GT-474. Associate Technical Editor: R. E. Kielb.
J. Turbomach. Jan 2000, 122(1): 11-21 (11 pages)
Published Online: February 1, 1998
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Received:
February 1, 1998
Citation
Deniz , S., Greitzer , E. M., and Cumpsty , N. A. (February 1, 1998). "Effects of Inlet Flow Field Conditions on the Performance of Centrifugal Compressor Diffusers: Part 2—Straight-Channel Diffuser ." ASME. J. Turbomach. January 2000; 122(1): 11–21. https://doi.org/10.1115/1.555424
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