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Research Papers: Gas Turbines: Turbomachinery

Unsteady Investigation on Tip Flow Field and Rotating Stall in Counter-Rotating Axial Compressor

[+] Author and Article Information
Limin Gao

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China;
Collaborative Innovation Center
of Advanced Aero-Engine,
Beijing 100191, China
e-mail: gaolm@nwpu.edu.cn

Ruiyu Li

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China;
Collaborative Innovation Center
of Advanced Aero-Engine,
Beijing 100191, China
e-mail: liruiyu-258@163.com

Fang Miao

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China;
Collaborative Innovation Center
of Advanced Aero-Engine,
Beijing 100191, China
e-mail: miaofangletter@126.com

Yutong Cai

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China;
Collaborative Innovation Center
of Advanced Aero-Engine,
Beijing 100191, China
e-mail: cyt283211837@163.com

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received August 14, 2014; final manuscript received November 3, 2014; published online December 23, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(7), 072603 (Jul 01, 2015) (11 pages) Paper No: GTP-14-1489; doi: 10.1115/1.4029101 History: Received August 14, 2014; Revised November 03, 2014; Online December 23, 2014

Contra-rotating axial compressor/fan (CRAC) is a promising technology to meet the future goals aircraft industry. Massive time accurate simulations are performed to investigate rotating stall in CRAC containing two counter-rotating rotors. Particularly, the back pressure increasing with a very small step to avoid missing flow field transition from stability to instability. Due to the canceling of the stator, the instability of downstream rotor is more stronger. The present studies mostly focus on the downstream rotor. The tip leakage flow field is analyzed in detail under near stall condition, which indicates that a secondary leakage flow plays an important role in the unsteadiness of CRAC's unsteady flow field. The frequency analysis in the tip clearance of downstream rotor under multiple near stall conditions captured the transition of the second harmonic frequency which can be used as stall inception signal. Moreover, the rotating stall onset process in real CRAC is simulated on the numerical stall.

Copyright © 2015 by ASME
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References

Figures

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Fig. 3

Comparison performance map of CRAC between experiment and computation (a) pressure ratio performance and (b) partial enlarged drawing

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Fig. 4

Static pressure coefficient at 99% span

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Fig. 5

Unsteadiness intensity at 99% span of ROT2

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Fig. 6

Tip leakage flow (a) tip leakage flow, (b) main leakage flow, and (c) secondary leakage flow

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Fig. 7

Static pressure envelope at different height in tip clearance

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Fig. 8

Convergence history of static pressure on ROT2 tip (a) leading edge, (b) middle, and (c) trailing edge

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Fig. 9

FFT analysis on ROT2 tip (a) leading edge, (b) middle, and (c) trailing edge

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Fig. 10

Convergence history of static pressure and FFT analysis at the leading edge on ROT2 50% span (a) convergence history of static pressure and (b) FFT analysis

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Fig. 11

Convergence history of outlet mass flow (a) design condition, (b) condition A, (c) condition B, and (d) condition C

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Fig. 12

FFT analysis (a) design condition, (b) condition A, (c) condition B, and (d) condition C

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Fig. 13

Comparison of mass-iteration histories

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Fig. 14

Static pressure–time histories for five probes located

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Fig. 15

Tip region flow field at T = 3

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Fig. 19

Tip vortex distribution in different passages at T = 7: (a) passage 1, (b) passage 2, (c) passage 3, (d) passage 4, and (e) passage 5

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Fig. 18

Entropy contour at 25% axial chord from the blade leading edge of ROT1: (a) T = 3, (b) T = 7, and (c) T = 8

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Fig. 17

Entropy contour at 25% axial chord from the blade leading edge of ROT2: (a) T = 3, (b) T = 6, (c) T = 7, and (d) T = 8

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Fig. 16

Tip region flow field at T = 8

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