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Research Papers

Experimental Study of Effects of Grooved Tip Clearances on the Flow Field in a Compressor Cascade Passage

[+] Author and Article Information
Hongwei Ma

School of Jet Propulsion, Beihang University,  National Key Laboratory of Science and Technology on Aero-Engines, 37 Xueyuan Road,Beijing 100191, Chinamahw@buaa.edu.cn

Jun Zhang

School of Jet Propulsion, Beihang University,  National Key Laboratory of Science and Technology on Aero-Engines, 37 Xueyuan Road,Beijing 100191, Chinazhangzhangsky@163.com

Jinghui Zhang

School of Jet Propulsion, Beihang University,  National Key Laboratory of Science and Technology on Aero-Engines, 37 Xueyuan Road,Beijing 100191, Chinazhangjinghui@163.com

Zhou Yuan

 University of Toronto Institute for Aerospace Studies, 4925 Dufferin Street,Toronto, Ontario M3H 5T6, Canadazyuan@utias.utoronto.ca

J. Turbomach 134(5), 051012 (May 08, 2012) (12 pages) doi:10.1115/1.4004484 History: Received April 09, 2011; Revised June 20, 2011; Published May 08, 2012; Online May 08, 2012

This paper presents an experimental investigation of effects of grooved tip clearances on the flow field of a compressor cascade. The tests were performed in a low-speed large-scale cascade, respectively, with two tip-clearance configurations, including the flat tip and the grooved tip with a chordwise channel on the blade top. The flow field at 10% chord downstream from the cascade trailing edge was measured at four incidence angles using a mini five-hole pressure probe. The static pressure distribution was measured on the tip endwall. The results show that the pressure gradient from the pressure side to the suction side on the blade tip is reduced due to the existence of the channel. As a result, the leakage flow is weakened. The high-blockage and high-loss region caused by the leakage flow is narrower with the grooved tip. In the meantime, the leakage flow migrates to lower span-wise position. The combined result is that the flow capacity in the tip region is improved at the incidence angles of 0 deg and 5 deg with the grooved tip. However, the loss is slightly greater than that with the flat tip at all the incidence angles.

Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 24

Pitchwise averaged axial velocity coefficient and total pressure loss coefficient (i = 8 deg)

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Figure 1

The compressor cascade wind tunnel

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Figure 2

The cascade with different tip clearances. (a) Flat tip (baseline). (b) Grooved tip.

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Figure 10

Contours of total pressure loss coefficient (i = −5 deg). (a) Flat tip. (b) Grooved tip.

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Figure 11

Pitchwise averaged total pressure loss coefficient (i = −5 deg)

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Figure 12

Contours of static pressure coefficient (i = 0 deg). (a) Flat tip. (b) Grooved tip.

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Figure 13

Contours of axial velocity coefficient (i = 0 deg). (a) Flat tip. (b) Grooved tip.

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Figure 14

Contours of total pressure loss coefficient (i = 0 deg). (a) Flat tip. (b) Grooved tip.

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Figure 15

Pitchwise distribution of axial velocity coefficient and total pressure loss coefficient at 94% span (i = 0 deg)

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Figure 16

Pitchwise averaged axial velocity coefficient and total pressure loss coefficient (i = 0 deg)

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Figure 17

Contours of static pressure coefficient (i = 5 deg). (a) Flat tip. (b) Grooved tip.

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Figure 18

Contours of axial velocity coefficient (i = 5°). (a) Flat tip. (b) Grooved tip.

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Figure 19

Pitchwise distribution of axial velocity coefficient and total pressure loss coefficient at 94% span (i = 5 deg)

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Figure 20

Pitchwise averaged axial velocity coefficient and total pressure loss coefficient (i = 5 deg)

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Figure 21

Contours of static pressure coefficient (i = 8 deg). (a) Flat tip. (b) Grooved tip.

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Figure 22

Contours of axial velocity coefficient (i = 8 deg). (a) Flat tip. (b) Grooved tip.

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Figure 23

Streamline of the secondary flow and contour of the axial vortictiy (i = 8 deg). (a) Flat tip. (b) Grooved tip.

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Figure 3

Measuring stations at the outlet and on the tip end wall

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Figure 4

Contours of static pressure coefficient (i = −5 deg). (a) Flat tip. (b) Grooved tip.

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Figure 5

Pitchwise distribution of static pressure coefficient (i = −5 deg). (a) 8% chord. (b) 36%chord. (c) 64% chord. (d) 91% chord.

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Figure 6

Secondary flow vectors and contour of ωz (i = −5 deg). (a) Flat tip. (b) Grooved tip.

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Figure 7

Contours of axial velocity coefficent (i = −5 deg). (a) Flat tip. (b) Grooved tip.

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Figure 8

Pitchwise distribution of axial velocity coefficent (i = −5 deg). (a) y/H = 94%. (b) y/H = 84%.

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Figure 9

Pitchwise averaged axial velocity coefficient (i = −5 deg)

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Figure 25

Mass-averaged flow angle. (a) i = −5 deg. (b) i = 0 deg. (c) i = −5 deg. (d) i = 8 deg.

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Figure 26

Overall performance of the cascade. (a) Area-averaged axial velocity coefficient. (b) Mass-averaged total pressure loss coefficient.

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