Research Papers: Techniques and Procedures

Research on the Turbine Blade Vibration Base on the Immersed Boundary Method

[+] Author and Article Information
Xiaolan Liu, Bo Yang, Qian Chen, Moru Song

School of Mechanical Engineering,
Shanghai Jiaotong University,
Shanghai 200230, China

Chunning Ji

School of Civil Engineering,
Tianjin University,
Tianjin 300072, China

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received May 31, 2017; final manuscript received December 7, 2017; published online February 6, 2018. Assoc. Editor: Hui Hu.

J. Fluids Eng 140(6), 061402 (Feb 06, 2018) (10 pages) Paper No: FE-17-1314; doi: 10.1115/1.4038866 History: Received May 31, 2017; Revised December 07, 2017

This paper is concerned with the study of a kind of discrete forcing immersed boundary method (IBM) by which the loosely aero-elasticity coupled method is developed to analyze turbine blade vibration. In order to reduce the spurious oscillations at steep gradients in the compressible viscous flowing field, a five orders weighted essentially nonoscillatory scheme (WENO) is introduced into the flow solver based on large eddy simulation (LES). The three-dimensional (3D) full-annulus domain of the last two stages of an industrial steam axial turbine is adopted to validate the developed method. By the method, the process of grid generation becomes very simple and the unsteady data transferring between stator and rotor is realized without the process of being averaged or weighted. Based on the analysis of some important aerodynamic parameters, it is believed that hypothesis of azimuthal periodicity is not reasonable in this case and full-annulus passages model is more feasible and suitable to the research of turbine blade vibration. Meanwhile, the blade vibration data are also discussed. It is at about 65% of rotor blade height of the last stage that an inflection point is observed and the midspan region of the blade is the vulnerable part damaged potentially by the blade vibration.

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Fig. 3

Overall performance of two stage turbine: (a) the last stage but one and (b) the last stage

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Fig. 1

IBM scheme and three types of calculation strategy of mirror points

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Fig. 2

Scheme of calculation domain and grid

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Fig. 4

Pressure contours from the single passage model (t = 64 R2) [25]

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Fig. 5

Pressure contours from the full-annulus model (t = 0 R1): (a) passage1, (b) passage2, and (c) passage3

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Fig. 6

Vectors of relative velocity in the rotor of the last stage, spanwise 20% (t = 0 R1)

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Fig. 8

Axial vibration of the rotor of the last but one stage: (a) axial vibration in time domain and (b) axial vibration in frequency domain

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Fig. 9

Axial vibration of the rotor of the last but one stage after being subtracted the average value: (a) axial vibration in time domain and (b) axial vibration in frequency domain

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Fig. 7

Temperature contours: (a) t = 0 R1, spanwise 20%, (b) t = 0 R1, spanwise 50%, (c) t = 0 R1, spanwise 80%, (d) t = 1/4 R1, spanwise 20%, (e) t = 1/4 R1, spanwise 50%, (f) t = 1/4 R1, spanwise 80%, (g) t = 2/4 R1, spanwise 20%, (h) t = 2/4 R1, spanwise 50%, (i) t = 2/4 R1, spanwise 80%, (j) t = 3/4 R1, spanwise 20%, (k) t = 3/4 R1, spanwise 50%, and (l) t = 3/4 R1, spanwise 80%

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Fig. 10

Axial vibration of the rotor of the last stage: (a) axial vibration in time domain and (b) axial vibration in frequency domain

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Fig. 11

Axial vibration of the rotor of the last stage after being subtracted the average value: (a) axial vibration in time domain and (b) axial vibration in frequency domain

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Fig. 12

Axial displacement of the rotor of the last stage in a period

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Fig. 13

The static deformation of two rotor blades

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Fig. 14

Axial vibration: (a) when inflection is at trough and (b) when inflection is at crest

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Fig. 15

Azimuthal vibration: (a) when inflection is at trough and (b) when inflection is at crest

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Fig. 16

Mises stress: (a) when inflection is at trough and (b) when inflection is at crest



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