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Research Papers: Gas Turbines: Structures and Dynamics

Tip Clearance Effects on Aero-elastic Stability of Axial Compressor Blades

[+] Author and Article Information
Zhizhong Fu

School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: buaaxiaochuang@163.com

Yanrong Wang

School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: yrwang@buaa.edu.cn

Xianghua Jiang

School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: jxh@buaa.edu.cn

Dasheng Wei

School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: dasheng.w@163.com

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 6, 2014; final manuscript received June 22, 2014; published online August 5, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(1), 012501 (Aug 05, 2014) (11 pages) Paper No: GTP-14-1273; doi: 10.1115/1.4028019 History: Received June 06, 2014; Revised June 22, 2014

The tip clearance effects on aero-elastic stability of axial compressor blades are investigated with two independent three-dimensional (3D) flutter prediction approaches: energy method and aero-elastic eigenvalue analysis. An axial compressor rotor which has encountered broken fault caused by flutter during the test rig and flight has been analyzed for five tip gap configurations. A consistent conclusion obtained by these two independent approaches shows the variation trend of aerodynamic damping is not monotonic, but aerodynamic damping at the least stable case shows a trend of first decrease and then increase with the rising of tip gap size, which is different from the results of other researchers and can be utilized to understand the conflict between the conclusions of different research work. Apart from the results of tip clearance effects on aero-elastic stability, the employed two methods have revealed the key factors involved in the flutter occurrence from a different perspective.

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References

Figures

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Fig. 1

3D view of the compressor rotor

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Fig. 2

Measured operating line, surge boundary, and flutter boundary

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Fig. 3

Blade FE model and first bending mode

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Fig. 4

Fluid mesh: (a) blade surface and hub and (b) 50% span

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Fig. 5

Distributions of static pressure at 90% span

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Fig. 6

Mach contour at 90% span of tip gap 3 model

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Fig. 7

Streamlines on suction surface

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Fig. 8

Vector of velocity component in circumferential direction at 60%C. (a) Tip gap 0.17 mm, (b) tip gap 0.67 mm, (c) tip gap 1.69 mm, (d) tip gap 2.36 mm, and (e) tip gap 2.70 mm.

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Fig. 9

AMDR calculated from different blade vibration amplitudes

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Fig. 10

Pressure amplitude of 90% span at 302-deg IBPA. (a) Suction surface and (b) pressure surface.

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Fig. 11

The calculated AMDRs of five models

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Fig. 12

The variations of AMDR at 302-deg IBPA as the tip clearance changing

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Fig. 13

Blade profile at 50% span

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Fig. 14

Normalized unsteady aerodynamic force amplitude on blade surface

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Fig. 15

Distributions of aerodynamic force amplitude at 90% span. (a) Suction surface of blade −1, (b) pressure surface of blade −1, (c) suction surface of blade 0, (d) pressure surface of blade 0, (e) suction surface of blade +1, and (f) pressure surface of blade +1.

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Fig. 16

Mach number contour at 90% span

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Fig. 17

Distributions of eigenvalues for five tip gap models

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Fig. 18

The maximum real part of eigenvalue versus nondimensional tip gap size

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Fig. 19

AMDR at 302-deg IBPA obtained by aero-elastic eigenvalue analysis

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