High-pressure ratio centrifugal compressors are applied to turbochargers and turboshaft engines because of their small dimensions, high efficiency, and wide operating range. Such a high-pressure ratio centrifugal compressor has a transonic inlet condition accompanied with a shock wave in the inducer portion. It is generally said that extra losses are generated by interaction of the shock wave and the boundary layers on the blade surface. To improve the performance of high-pressure ratio centrifugal compressor, it is necessary to understand the flow phenomena. Although some research works on transonic impeller flow have been published, some unknown flow physics are still remaining. The authors designed a transonic impeller, with an inlet Mach number about 1.3, and conducted detailed flow measurements by using laser doppler velocimetry (LDV). In the result, the interaction between the shock wave and tip leakage vortex at the inducer and flow distortion at the downstream of inducer were observed. The interaction of the boundary layer and the shock wave was not observed. Also, computational flow analysis was conducted and compared with experimental results.
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April 2003
Technical Papers
Aerodynamics of a Transonic Centrifugal Compressor Impeller
Seiichi Ibaraki,
Seiichi Ibaraki
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
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Tetsuya Matsuo,
Tetsuya Matsuo
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
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Hiroshi Kuma,
Hiroshi Kuma
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
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Kunio Sumida,
Kunio Sumida
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
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Toru Suita
Toru Suita
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
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Seiichi Ibaraki
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
Tetsuya Matsuo
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
Hiroshi Kuma
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
Kunio Sumida
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
Toru Suita
Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., Nagasaki, 851-0392, Japan
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Amsterdam, The Netherlands, June 3–6, 2002. Manuscript received by the IGTI January 25, 2002. Paper No. 2002-GT-30374. Review Chair: E. Benvenuti.
J. Turbomach. Apr 2003, 125(2): 346-351 (6 pages)
Published Online: April 23, 2003
Article history
Received:
January 25, 2002
Online:
April 23, 2003
Citation
Ibaraki , S., Matsuo , T., Kuma , H., Sumida , K., and Suita, T. (April 23, 2003). "Aerodynamics of a Transonic Centrifugal Compressor Impeller ." ASME. J. Turbomach. April 2003; 125(2): 346–351. https://doi.org/10.1115/1.1540117
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