Research Papers

The Effect of Tip Leakage Vortex for Operating Range Enhancement of Centrifugal Compressor

[+] Author and Article Information
Isao Tomita

e-mail: isao_tomita@mhi.co.jp

Seiichi Ibaraki

e-mail: seiichi_ibaraki@mhi.co.jp
Nagasaki Research and Development Center,
Mitsubishi Heavy Industries, Ltd.,
Nagasaki 851-0392, Japan

Masato Furukawa

e-mail: furu@mech.kyushu-u.ac.jp

Kazutoyo Yamada

e-mail: k.yamada@mech.kyushu-u.ac.jp
Department of Mechanical Engineering Science,
Kyushu University,
Fukuoka 819-0395, Japan

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 16, 2012; final manuscript received October 3, 2012; published online June 28, 2013. Editor: David Wisler.

J. Turbomach 135(5), 051020 (Jun 28, 2013) (8 pages) Paper No: TURBO-12-1149; doi: 10.1115/1.4007894 History: Received July 16, 2012; Revised October 03, 2012

Recently, the application of turbochargers is increasing because they are effective in improving fuel consumption of engines. One of the most important turbocharger characteristics is compressor operating range, since it has been used in various driving patterns with the advent of variable geometry turbochargers. Owing to the complicated phenomena, such as rotating stall occurring at low flow rate condition, flow analysis is very difficult and details of flow structure have not been fully understood for a long time since the early 1970s. In this study, two compressors with different operating range width were investigated with experimental and computational flow analysis. In the compressor with narrow operating range, the amplitude of blade passing pressure fluctuation decreases rapidly and rotating stall occurs near surging. On the other hand, in the compressor with wide operating range, the blockage by the tip leakage vortex breakdown play a role in stabilizing the flow field and keeping up a high performance even at low flow rates.

Copyright © 2013 by ASME
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Fig. 2

Measurement locations

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Fig. 3

Computational domain

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Fig. 4

Pressure fluctuation of compressor A (160,000 rpm, measurement)

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Fig. 5

Pressure fluctuation of compressor B (160,000 rpm, measurement)

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Fig. 6

Details of low pass filtered wave (160,000 rpm, measurement, LFR in compressor A)

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Fig. 7

The amplitude of blade passing fluctuation (160,000 rpm, measurement)

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Fig. 8

Performance comparison (160,000 rpm)

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Fig. 9

Comparison between CFD and measurement of compressor A (160,000 rpm)

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Fig. 10

Comparison between CFD and measurement of compressor B (160,000 rpm)

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Fig. 11

Internal flow structure in compressor A (CFD, 160,000 rpm)

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Fig. 12

Internal flow structure in compressor B (CFD, 160,000 rpm)




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