The inlet fogging effects on the stable range of a NASA transonic compressor stage, Stage 35, are numerically simulated and analyzed in this paper. The 3D two-phase flow fields in the compressor stage are investigated under different operating flow conditions with varying levels of the injected water flow rates and the fogging droplets sizes. The special attention is given to the stall and the choking operating points to investigate changes in the stable operating range of the compressor stage as a result of different wet compression conditions. The preliminary results indicate that the inlet fogging has different effects on either the stall and/or the choking range. The change in the stable range of this transonic compressor stage depends on the fogging flow rate and droplets diameters.
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February 2012
Research Papers
The Influence of Inlet Fogging for the Stable Range in a Transonic Compressor Stage
Lanxin Sun,
Lanxin Sun
Harbin Engineering University
, Harbin 150001, China
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Qingfeng Deng,
Qingfeng Deng
Harbin Engineering University
, Harbin 150001, China
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Song Li,
Song Li
Harbin Engineering University
, Harbin 150001, China
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Chunlei Liu,
Chunlei Liu
Harbin Engineering University
, Harbin 150001, China
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Rakesh K. Bhargava
Rakesh K. Bhargava
Turbomachinery Consultant Foster Wheeler USA Corp.
, Houston, TX 77052-3495
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Mingcong Luo
Qun Zheng
Lanxin Sun
Harbin Engineering University
, Harbin 150001, China
Qingfeng Deng
Harbin Engineering University
, Harbin 150001, China
Song Li
Harbin Engineering University
, Harbin 150001, China
Chunlei Liu
Harbin Engineering University
, Harbin 150001, China
Rakesh K. Bhargava
Turbomachinery Consultant Foster Wheeler USA Corp.
, Houston, TX 77052-3495J. Eng. Gas Turbines Power. Feb 2012, 134(2): 022002 (11 pages)
Published Online: December 20, 2011
Article history
Received:
April 25, 2011
Revised:
April 26, 2011
Online:
December 20, 2011
Published:
December 20, 2011
Citation
Luo, M., Zheng, Q., Sun, L., Deng, Q., Li, S., Liu, C., and Bhargava, R. K. (December 20, 2011). "The Influence of Inlet Fogging for the Stable Range in a Transonic Compressor Stage." ASME. J. Eng. Gas Turbines Power. February 2012; 134(2): 022002. https://doi.org/10.1115/1.4004163
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