Requirements for aeronautical gas turbine engines for helicopters include small size, low weight, high output, and low fuel consumption. In order to achieve these requirements, development work has been carried out on high efficiency and high pressure ratio compressors. As a result, we have developed a single stage centrifugal compressor with a pressure ratio of 11 for a 1000 shp class gas turbine. The centrifugal compressor is a high transonic compressor with an inlet Mach number of about 1.6. In high inlet Mach number compressors, the flow distortion due to the shock wave and the shock boundary layer interaction must have a large effect on the flow in the inducer. In order to ensure the reliability of aerodynamic design technology, the actual supersonic flow phenomena with a shock wave must be ascertained using measurement and Computational Fluid Dynamics (CFD). This report presents the measured results of the high transonic flow at the impeller inlet using Laser Doppler Velocimeter (LDV) and verification of CFD, with respect to the high transonic flow velocity distribution, pressure distribution, and shock boundary layer interaction at the inducer. The impeller inlet tangential velocity is about 460 m/s and the relative Mach number reaches about 1.6. Using a LDV, about 500 m/s relative velocity was measured preceding a steep deceleration of velocity. The following steep deceleration of velocity at the middle of blade pitch clarified the cause as being the pressure rise of a shock wave, through comparison with CFD as well as comparison with the pressure distribution measured using a high frequency pressure transducer. Furthermore, a reverse flow is measured in the vicinity of casing surface. It was clarified by comparison with CFD that the reverse flow is caused by the shock-boundary layer interaction. Generally CFD shows good agreement with the measured velocity distribution at the inducer and splitter inlet, except in the vicinity of the casing surface.
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October 2004
Technical Papers
Detailed Flow Study of Mach Number 1.6 High Transonic Flow With a Shock Wave in a Pressure Ratio 11 Centrifugal Compressor Impeller
Hirotaka Higashimori,
Hirotaka Higashimori
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
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Kiyoshi Hasagawa,
Kiyoshi Hasagawa
Mitsubishi Heavy Industries, Ltd., Nagoya Guidance & Propulsion Systems Works, 1200 Higashi-Tanaka, Komaki, Aichi 485-8561, Japan
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Kunio Sumida,
Kunio Sumida
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
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Tooru Suita
Tooru Suita
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
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Hirotaka Higashimori
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
Kiyoshi Hasagawa
Mitsubishi Heavy Industries, Ltd., Nagoya Guidance & Propulsion Systems Works, 1200 Higashi-Tanaka, Komaki, Aichi 485-8561, Japan
Kunio Sumida
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
Tooru Suita
Mitsubishi Heavy Industries, Ltd., Nagasaki R&D Center, 5-717-1 Fukahori-Machi, Nagasaki 851-0392, Japan
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-53435. Manuscript received by IGTI, October 1, 2003; final revision, March 1, 2004. IGTI Review Chair: A. J. Strazisar.
J. Turbomach. Oct 2004, 126(4): 473-481 (9 pages)
Published Online: December 29, 2004
Article history
Received:
October 1, 2003
Revised:
March 1, 2004
Online:
December 29, 2004
Citation
Higashimori, H., Hasagawa, K., Sumida , K., and Suita, T. (December 29, 2004). "Detailed Flow Study of Mach Number 1.6 High Transonic Flow With a Shock Wave in a Pressure Ratio 11 Centrifugal Compressor Impeller ." ASME. J. Turbomach. October 2004; 126(4): 473–481. https://doi.org/10.1115/1.1791645
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