Research Papers: Gas Turbines: Structures and Dynamics

Method for Predicting Unsteady Vibration of Gas Turbine Compressor Blades Under Subsonic Near-Stall Conditions

[+] Author and Article Information
Kazuyuki Yamaguchi

Department of Reliability Science Research,
Mechanical Engineering Research Center,
Hitachi Research Laboratory,
Hitachi, Ltd.,
832-2 Horiguchi, Hitachinaka,
Ibaraki 312-0034, Japan
e-mail: kazuyuki.yamaguchi.jg@hitachi.com

Yasuo Takahashi

Department of Turbo Machinery Research,
Research & Development Center,
Mitsubishi Hitachi Power Systems, Ltd.,
832-2 Horiguchi, Hitachinaka,
Ibaraki, 312-0034, Japan
e-mail: yasuo_takahashi@mhps.com

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 6, 2014; final manuscript received May 15, 2014; published online June 27, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(12), 122501 (Jun 27, 2014) (7 pages) Paper No: GTP-14-1186; doi: 10.1115/1.4027743 History: Received April 06, 2014; Revised May 15, 2014

Wind tunnel tests and numerical calculations using computational fluid dynamics (CFD) analysis and structural finite element analysis were conducted to clarify the vibration characteristics of gas turbine compressor blades under subsonic near-stall conditions. The results show that discrete low-frequency components of pressure are created by variation of the separation region and that discrete high-frequency components are created by vortex shedding when the compressor blade incidence angle is in the stall region. The natural frequency component resonated by the random fluid force is dominant in blade vibration. The numerically calculated phenomena agree well with the measured phenomena. The vibration amplitude increases with the incidence angle and the Mach number, and it increases rapidly at higher angles. A simple method for predicting the vibration stress using static calculations is reasonably accurate.

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Fig. 4

CFD analysis model

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Fig. 5

Structural finite element calculation model

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Fig. 6

Calculated pressure recovery ratio

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Fig. 7

Calculated natural vibration modes. The contour shows absolute value of displacement.

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Fig. 8

Measured frequency spectra of pressure and stress

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Fig. 9

Measured amplitudes of pressure and stress

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Calculated frequency spectra of pressure and stress

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Fig. 11

Calculated frequency spectrum of pressure for incidence angle of 20 deg

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Fig. 12

Calculated transition of pressure on blade and stream lines. The contour shows pressure distribution.

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Fig. 13

Stress amplitude calculated using Eq. (2) compared with measured amplitude




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