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Research Papers: Gas Turbines: Turbomachinery

A Numerical Study on the Effect of Bleed System on Starting Ability and Flow Performance of Rampressor Inlet

[+] Author and Article Information
Weijia Kang

School of Energy Science and Engineering,
Harbin Institute of Technology,
Mailbox 458,
No. 92, Xi-Dazhi Street,
NanGang District, Harbin,
HeiLongjiang Province 150001, China
e-mail: kwj1221@163.com

Zhansheng Liu

Harbin Institute of Technology,
Mailbox 458,
No. 92, Xi-Dazhi Street,
NanGang District, Harbin,
HeiLongjiang Province 150001, China
e-mail: lzs@hit.edu.cn

Yu Wang

Harbin Institute of Technology,
Mailbox 458,
No. 92, Xi-Dazhi Street,
NanGang District, Harbin,
HeiLongjiang Province 150001, China
e-mail: thwangyu@126.com

Yanyang Dong

Harbin Institute of Technology,
Mailbox 458,
No. 92, Xi-Dazhi Street,
NanGang District, Harbin,
HeiLongjiang Province 150001, China
e-mail: dyydsghh@gmail.com

Yong Sun

Harbin Institute of Technology,
Mailbox 458,
No. 92, Xi-Dazhi Street,
NanGang District, Harbin,
HeiLongjiang Province 150001, China
e-mail: 1171043886@qq.com

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received September 11, 2013; final manuscript received May 24, 2014; published online June 27, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(12), 122601 (Jun 27, 2014) (12 pages) Paper No: GTP-13-1339; doi: 10.1115/1.4027761 History: Received September 11, 2013; Revised May 24, 2014

A unique supersonic compressor rotor with high pressure ratio, termed the Rampressor, is presented by Ramgen Power Systems, Inc., (RPS). Based on the models of Rampressor inlet, the inlet flow field with bleed system is numerically studied. Validation of the employed computational fluid dynamics (CFD) scheme is provided through test cases. The effects of boundary layer bleed location and bleed amount on Rampressor rotor inlet start and flow performance are analyzed. The results indicate that the boundary layer bleed has a significant effect for start and flow performance of Rampressor inlet. Boundary layer bleed technique has been applied to eliminate the emerging flow separation zone for enhancing Rampressor rotor inlet performance and enlarging its stable working range. The starting ability and flow performance of Rampressor inlet are efficiently improved by bleeding system, but the improvement effect is different for Rampressor inlet with different bleed location. Along the position of bleeding system moves forward, the range of Rampressor inlet normal work rotation speed is enlarged. The flow performance of Rampressor inlet improves obviously with the increment of bleed flow rate, and exit stability of Rampressor inlet enhances. And in the same back pressure work condition of Rampressor inlet, bleed system has been shown to be effective that exit stability of Rampressor inlet ameliorates, but the loss of compressed air from the bleed system has a negative effect on overall Rampressor inlet efficiency.

Copyright © 2014 by ASME
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Figures

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Fig. 1

Model of Rampressor rotor

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Fig. 2

2D model of Rampressor rotor inlet

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Fig. 3

Local enlarging graph of Rampressor flow-path with bleeding system

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Fig. 4

Specific boundary conditions of Rampressor inlet

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Fig. 5

Schematic of transonic diffuser flow and computational grid: (a) transonic diffuser geometry, (b) computational grid, and (c) Mach number distribution

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Fig. 6

Predicted static pressure for separating transonic diffuser

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Fig. 7

Contour line of Mach number [19]: (a) experimental results and (b) RNG k-ε

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Fig. 8

Mach number distribution of Rampressor rotor inlet without bleeding system

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Fig. 9

Mach number distribution of Rampressor rotor inlet with bleeding system: (a) program 1, (b) program 2, and (c) program 3

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Fig. 10

Comparison minimum rotation speed of Rampressor rotor inlet self-starting

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Fig. 11

Flow distribution of inlet with bleeding system case 1: (a) pressure contour and (b) Mach number contour

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Fig. 12

Flow distribution of inlet with bleeding system case 2: (a) pressure contour and (b) Mach number contour

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Fig. 13

Flow distribution of inlet with bleeding system case 4: (a) pressure contour and (b) Mach number contour

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Fig. 14

Flow performance of inlet with different bleeding systems (case 1, case 2, and case 4): (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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Fig. 15

Flow distribution of inlet with bleeding system case 2: (a) pressure contour and (b) Mach number contour

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Fig. 16

Flow distribution of inlet with bleeding system case 3: (a) pressure contour and (b) Mach number contour

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Fig. 17

Flow performance of inlet with different bleeding systems (case 2 and case 3): (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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Fig. 18

Flow performance of inlet in different bleed amount of bleed hole 9: (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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Fig. 19

Flow performance of inlet in different bleed amount of bleed hole 14: (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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Fig. 20

Flow performance of inlet in different total bleed amount of bleed hole 9 and bleed hole 14: (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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Fig. 21

Flow performance of inlet with different bleed amount in the critical work state: (a) static pressure ratio and pressurization ratio, (b) total-pressure recovery coefficient and kinetic energy efficiency, (c) loss coefficient, and (d) nondimensional total-pressure distortion

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