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Gas Turbines: Industrial & Cogeneration

The Effects of Wet Compression and Blade Tip Water Injection on the Stability of a Transonic Compressor Rotor

[+] Author and Article Information
Mingcong Luo

 Harbin Engineering University, Harbin 150001, Chinatrylove39@163.comHess Corporation, Houston, TX 77450trylove39@163.com

Qun Zheng

 Harbin Engineering University, Harbin 150001, Chinazhengqun@hrbeu.edu.cnHess Corporation, Houston, TX 77450zhengqun@hrbeu.edu.cn

Lanxin Sun, Qingfeng Deng, Jiyou Chen, Jie Wang, Rakesh K. Bhargava

 Harbin Engineering University, Harbin 150001, ChinaHess Corporation, Houston, TX 77450

J. Eng. Gas Turbines Power 134(9), 092001 (Jul 18, 2012) (10 pages) doi:10.1115/1.4006991 History: Received June 19, 2012; Revised June 19, 2012; Published July 18, 2012; Online July 18, 2012

The rotor blade tip leakage flow and associated formation of the tip leakage vortex and interaction of the tip leakage vortex with the shockwave, particularly in the case of a transonic compressor rotor have significant impact on the compressor performance and its stability. Air injection upstream of the compressor rotor tip has been shown to improve compressor performance and enhance its stability. The air required for rotor blade tip injection is generally taken from the later stages of the compressor thus causing penalty on the gas turbine performance. In this study, effects of water injection at the rotor tip with and without the wet compression on the compressor performance and its stability have been examined. To achieve the stated objectives, the well tested transonic compressor rotor stage, NASA rotor stage 37, has been numerically simulated. The evaluation of results on various performance parameters, such as total pressure ratio, inlet flow capacity, and adiabatic efficiency combined with contours of total pressure losses, entropy, Mach number, and temperature including limiting streamlines, shows that the blade tip water injection could help in reducing low energy region downstream of the shockwave and strength of the tip leakage vortex with the compressor operating at its rotating stall boundary condition. The extent of reduction depends on the droplet size, injection flow rate, and its velocity. Furthermore, results show that combined case of the blade tip water injection and the wet compression could provide better stall margin enhancement than the blade tip water injection case.

Copyright © 2012 by by ASME
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References

Figures

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Figure 1

Computational geometric model and computational grids for NASA Rotor 37

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Figure 2

Contrast of simulated results of k-ɛ turbulence model with experimental data

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Figure 3

Comparison of inlet mass flow rates

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Figure 4

Comparison of the rotor total pressure ratio

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Figure 5

Comparison of the rotor adiabatic efficiency of dry and tip injection cases

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Figure 6

Entropy contour of 98% span on rotor blade to blade surfaces in different water tip injection cases

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Figure 7

Mach number contours at 98% span on the rotor’s blade-to-blade surfaces under different tip injection cases

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Figure 8

Limiting streamlines in the clearance of the blade under different water tip injection cases

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Figure 9

Leakage streamlines at the clearance of the blade under different water tip injection cases

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Figure 10

Comparison of inlet mass flow rate under different wet compression conditions

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Figure 11

Comparison of the rotor total pressure ratio under different wet compression conditions

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Figure 12

Comparison of the rotor adiabatic efficiency under different wet compression conditions

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Figure 13

Comparison of the rotor outlet temperature under different wet compression conditions

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Figure 14

Partial enlarged Mach number contour under different wet compression cases

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Figure 15

Limiting streamlines on the rotor blades’ suction surface

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Figure 16

Comparison of inlet mass flow rate under different cases

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Figure 17

Comparison of the rotor total pressure ratio under different conditions

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Figure 18

Comparison of the rotor adiabatic efficiency under different conditions

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Figure 19

Comparison of the rotor outlet temperature under different condition

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Figure 20

Mach number contours at 98% span on the rotor’s blade-to-blade surfaces

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Figure 21

Temperature contours on the blade-to-blade surface at 98% span of the rotor blade

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Figure 22

Rotor blade loads under different combination conditions (span: 98%)

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Figure 23

Rotor blade loads under different conditions

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Figure 24

Effects of the three different droplet injecting methods on the compressor stall margin

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