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Research Papers: Gas Turbines: Industrial & Cogeneration

Numerical Simulation of a Complete Gas Turbine Engine With Wet Compression

[+] Author and Article Information
Lanxin Sun

e-mail: sunlanxin@yahoo.com.cn

Qun Zheng

e-mail: zhengqun@hrbeu.edu.cn

Mingcong Luo

Harbin Engineering University,
Harbin, 150001 P. R. C.

Rakesh K. Bhargava

Hess Corporation,
Houston, TX 77010

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 1, 2012; final manuscript received July 2, 2012; published online November 30, 2012. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(1), 012002 (Nov 30, 2012) (9 pages) Paper No: GTP-12-1245; doi: 10.1115/1.4007366 History: Received July 01, 2012; Revised July 02, 2012

In this paper, a thorough flow simulation of a small turbojet engine has been carried out to predict the engine performance as a result of water injected at the compressor inlet. Wet compression will not only change compressor performance characteristic map, but also has effects on both the combustor and the turbine sections. The match between the turbojet engine components, that is the compressor, combustor and turbine, will shift to a new operating point. In this paper, we present a steady-state numerical simulation of the entire gas turbine with wet compression in order to evaluate the effects on the gas turbine performance. Compared with the dry case, the results of wet cases show increased values of compressor compression ratios, turbine expansion ratios, intake mass flowrates, and engine thrusts including a decreased amount of specific fuel consumption. The wet compression reduces NOx production in the combustor, which is also simulated and with results presented. The study also indicates that the water mass flow rate and droplet diameter are key factors impacting the engine performance.

Copyright © 2013 by ASME
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References

Figures

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Fig. 1

Turbojet engine configuration

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Fig. 2

Grids for different components of the turbojet engine

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Fig. 3

Flame in combustor and temperature contours at 50% span of full turbojet engine (water injection: RR size 10 μm, 1%)

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Fig. 4

Droplet trajectory of liquid water and fuel (water injection: RR size 10 μm, 1%)

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Fig. 5

Water droplet residence time in compressor (In the third stator passage)

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Fig. 6

Turbojet cycle p-v diagram with/without water injection

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Fig. 7

Turbojet ideal cycle T-S diagram with/without water injection

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Fig. 8

Balance of mass flowrates between compressor and turbine

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Fig. 9

Liquid trap ratio for different mean diameters

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Fig. 10

Balance of power (or torque) between compressor and turbine

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Fig. 11

Inlet mass flow rate for different water injection rates

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Fig. 12

Temperature of compressor outlet for different water injection rates

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Fig. 13

Temperature of combustor and turbine outlet for different water injections

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Fig. 14

Compressor pressure ratio and turbine expansion ratio for different water injection rates

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Fig. 15

Turbojet thrust for different water injection rates

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Fig. 16

Relative specific fuel consumption (SFC) for different water injection rates

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Fig. 17

Component efficiency of compressor and turbine for different water injection rates

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Fig. 18

Concentration of NO and CO at combustor outlet for different water injection rates

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Fig. 19

Streamlines adjacent to suction surfaces and through tip clearance of compressor 1st stage (upper: rotor; lower: stator)

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Fig. 20

Streamlines through tip clearance and adjacent to rotor’s pressure surface of turbine

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