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Research Papers: Gas Turbines: Industrial & Cogeneration

The Influence of Inlet Fogging for the Stable Range in a Transonic Compressor Stage

[+] Author and Article Information
Mingcong Luo

 Harbin Engineering University, Harbin 150001, Chinatrylove39@163.com

Qun Zheng

 Harbin Engineering University, Harbin 150001, Chinazhengqun@hrbeu.edu.cn

Lanxin Sun, Qingfeng Deng, Song Li, Chunlei Liu

 Harbin Engineering University, Harbin 150001, China

Rakesh K. Bhargava

 Turbomachinery Consultant Foster Wheeler USA Corp., Houston, TX 77052-3495

J. Eng. Gas Turbines Power 134(2), 022002 (Dec 20, 2011) (11 pages) doi:10.1115/1.4004163 History: Received April 25, 2011; Revised April 26, 2011; Published December 20, 2011; Online December 20, 2011

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.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Computational geometric model and grids for NASA Stage 35

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Figure 2

Contrast of simulated results of the k − ɛ turbulence models with experimental data

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Figure 3

Comparison of simulated results for the wet and dry stage performance characteristic curves

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Figure 4

Comparison of inlet mass flowrates at dry and wet cases boundary

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Figure 5

Comparison of the stage total pressure ratio under dry and wet conditions — all dry cases at the stall boundary

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Figure 6

Comparison of the stage efficiency under dry and wet conditions — all dry cases at the stall boundary

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Figure 7

Comparison of outlet temperature under dry and wet conditions — all dry cases at the stall boundary

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Figure 8

Contours of Mach number on rotor B2B surface of span 97% under the same injected droplet size

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Figure 9

Contours of Mach number on rotor B2B surface of span 97% under the same fogging flow rate

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Figure 10

Contours of temperature on rotor B2B surface of span 97%

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Figure 11

Contours of velocity vector on S3 surface of clearance leakage vortex position

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Figure 12

Rotor blade loads under different fogging conditions

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Figure 13

Comparison of inlet mass flow rate under different inlet fogging conditions at the choking boundary

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Figure 14

Comparison of the stage total pressure ratio under different inlet fogging conditions

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Figure 15

Comparison of the stage outlet temperature under different inlet fogging conditions

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Figure 16

Comparison of the stage adiabatic efficiency under different inlet fogging conditions

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Figure 17

Contours of static pressure on B2B surfaces of span 50%

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Figure 18

Contours of Temperature on B2B surfaces of span 97%

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Figure 19

Limiting streamlines on suction surfaces of the stator blade

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Figure 20

Partial enlarged contours of velocity vector on rotor B2B surface

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Figure 21

Blade loads of Span 97% for dry and wet cases

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