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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Im, H.-S., and Zha, G.-C., 2013, “Flutter Prediction of a Transonic Fan With Travelling Wave Using Fully Coupled Fluid/Structure Interaction,” ASME Paper No. GT2013-94341. [CrossRef]
Zhang, X. W., Wang, Y. R., and Xu, K. N., 2011, “Flutter Prediction in Turbomachinery With Energy Method,” Proc. Inst. Mech. Eng., Part G, 225(9), pp. 995–1002. [CrossRef]
Nowinski, M., and Panovsky, J., 2000, “Flutter Mechanisms in Low Pressure Turbine Blades,” ASME J. Eng. Gas. Turbines Power, 122(1), pp. 82–88. [CrossRef]
Vahdati, M., Sayma, A., Marshall, J., and Imregun, M., 2001, “Mechanisms and Prediction Methods for Fan Blade Stall Flutter,” J. Propul. Power, 17(5), pp. 1100–1108. [CrossRef]
Zhang, X., Wang, Y., and Xu, K., 2013, “Mechanisms and Key Parameters for Compressor Blade Stall Flutter,” ASME J. Turbomach., 135(2), p. 024501. [CrossRef]
Kielb, R. E., Barter, J. W., Thomas, J. P., and Hall, K. C., 2003, “Blade Excitation by Aerodynamic Instabilities: A Compressor Blade Study,” ASME Paper No. GT2003-38634. [CrossRef]
Kielb, R. E., Hall, K. C., Spiker, M., Thomas, J. P., Pratt, E. T., Jr., and Jeffries, R., 2006, “Non-Synchronous Vibration of Turbomachinery Airfoils,” Duke University, Durham, NC, Technical Report No. AFRL-SR-AR-TR-06-0269.
Drolet, M., Vo, H. D., and Mureithi, N. W., 2013, “Effect of Tip Clearance on the Prediction of Nonsynchronous Vibrations in Axial Compressors,” ASME J. Turbomach., 135(1), p. 011023. [CrossRef]
Vo, H. D., 2006, “Role of Tip Clearance Flow in the Generation of Non-Synchronous Vibrations,” 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 9–12, AIAA Paper No. 2006-629. [CrossRef]
Feng, Y. C., Hu, Z. A., Zhao, X. H., and Tao, D. P., 1986, “Experimental Research on the Effects of Tip Clearance on Stall Flutter,” J. Beijing Inst. Aviat., 9(4), pp. 79–84 (in Chinese).
Yang, H., and He, L., 2004, “Experimental Study on Linear Compressor Cascade With Three-Dimensional Blade Oscillation,” J. Propul. Power, 20(1), pp. 180–188. [CrossRef]
Huang, X., He, L., and Bell, D. L., 2008, “Effects of Tip Clearance on Aerodynamic Damping in a Linear Turbine Cascade,” J. Propul. Power, 24(1), pp. 26–33. [CrossRef]
Peng, C., 2011, “Tip Running Clearances Effects on Tip Vortices Induced Axial Compressor Rotor Flutter,” ASME Paper No. GT2011-45504. [CrossRef]
Sakulkaew, S., Tan, C. S., Donahoo, E., Cornelius, C., and Montgomery, M., 2013, “Compressor Efficiency Variation With Rotor Tip Gap From Vanishing to Large Clearance,” ASME J. Turbomach., 135(3), p. 031030. [CrossRef]
Wu, Q. F., Yang, S. J., and Duan, L. F., 1987, “Experimental Research on the Stall Flutter of Tuned and Mistuned Blade/Bladed Disk,” 606 Research Institution of Aero-Industry Ministry, Shen Yang, China (in Chinese).
Carta, F. O., 1967, “Coupled Blade-Disk-Shroud Flutter Instabilities in Turbojet Engine Rotors,” ASME J. Eng. Power, 89(3), pp. 419–426. [CrossRef]
Sanders, A. J., Hassan, K. K., and Rabe, D. C., 2004, “Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk,” ASME J. Turbomach., 126(1), pp. 166–174. [CrossRef]
Micallef, D., Witteck, D., Wiedermann, A., Kluß, D., and Mailach, R., 2012, “Three-Dimensional Viscous Flutter Analyses of a Turbine Cascade in Subsonic and Transonic Flows,” ASME Paper No. GT2012-68396. [CrossRef]
Fransson, T., Bölcs, A., Ott, P., and Jöcker, M., 1999, “Viscous and Inviscid Linear/Nonlinear Calculations Versus Quasi-Three-Dimensional Experimental Cascade Data for a New Aeroelastic Turbine Standard Configuration,” ASME J. Turbomach., 121(4), pp. 717–725. [CrossRef]
Moffatt, S., and He, L., 2003, “Blade Forced Response Prediction for Industrial Gas Turbines: Part 1—Methodologies,” ASME Paper No. GT2003-38640. [CrossRef]
Kielb, R., and Chiang, H.-W., 1992, “Recent Advancements in Turbomachinery Forced Response Analyses,” 30th Aerospace Sciences Meeting & Exhibit, Reno, NV, January 6–9, AIAA Paper No. 92-0012. [CrossRef]
Hsu, K., and Hoyniak, D., 2011, “A Fast Influence Coefficient Method for Linearized Flutter and Forced-Response Analysis,” 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, FL, January 4–7, AIAA Paper No. 2011-229. [CrossRef]


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Fig. 3

Blade FE model and first bending mode

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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. 4

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

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Fig. 2

Measured operating line, surge boundary, and flutter boundary

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Fig. 1

3D view of the compressor rotor

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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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