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Research Papers

Investigation of Forced Response Sensitivity of Low Pressure Compressor With Respect to Variation in Tip Clearance Size

[+] Author and Article Information
Majid Mesbah

Cenaero ASBL,
Gosselies 6041, Belgium
e-mail: majid.mesbah@cenaero.be

Jean-François Thomas, François Thirifay

Cenaero ASBL,
Gosselies 6041, Belgium

A. Naert, S. Hiernaux

Techspace-Aero,
Herstal 4041, Belgium

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 5, 2014; final manuscript received March 22, 2015; published online April 21, 2015. Assoc. Editor: Li He.

J. Turbomach 137(9), 091011 (Sep 01, 2015) (9 pages) Paper No: TURBO-14-1060; doi: 10.1115/1.4030250 History: Received May 05, 2014; Revised March 22, 2015; Online April 21, 2015

This study aims to numerically investigate the sensitivity of the forced response with respect to the variation of the tip clearance setting of a low pressure compressor BluM(monoblock bladed drum) when it is subjected to low engine order excitations. Two different types of blades are employed in the upstream row in order to generate the low engine order excitations. The forced response as well as the aerodynamic damping is numerically estimated using the TWIN approach. The experiments are conducted to measure the forced response for the nominal tip gap to validate the numerical results. Further, simulations are performed for a range of tip clearances. The variation of the steady load distributions due to the changes of the tip clearance are analyzed and presented. The aerodynamic damping and the forced response are calculated and compared for different tip clearances. It is observed that aerodynamic damping increases significantly with tip gap, whereas the excitation forces are reduced. As consequence of these two evolutions, the forced response decreases drastically for larger tip clearance.

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References

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]
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Norryd, M., and Bölcs, A., 1997, “Experimental Investigation of Unsteady Pressure Behaviours in a Linear Turbine Cascade,” 8th International Symposium on Unsteady Aerodynamics and Aeroelasticity of Turbomachines, Stockholm, Sept. 14–18, pp. 103–116. [CrossRef]
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Seinturier, E., 2008, “Forced Response Computation for Bladed Disks Application: Research Cases and Industrial Problems,” Structural Design of Aircraft Engines: Key Objectives and Techniques (VKI Lecture Series 2008-07), von Karman Institute for Fluid Dynamics, Rhode-St-Genese, Belgium.

Figures

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Fig. 1

Procedure to calculate the forced response in TWIN approach

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Fig. 2

Configuration 1S9s|1r corresponds to the 10N excitation. One stator blade out of 10 is different (in red).

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Fig. 3

Schematic of the experimental setup including 1.5 stages compressor

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Fig. 4

The real part of the first bending mode (1F) on the CFD mesh

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Fig. 5

Time evolution of Re.GAFTWIN(α0)

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Fig. 6

The calculated FFT of GAFTWIN(α0) signal over five periods of thick blade passing in frequency domain

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Fig. 7

Evolution of Imaginary part of temporal GAFTwin(α0) and GAFTwin(α1)

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Fig. 8

Imaginary part of GAFTWIN(α1)-GAFTWIN(α0). Reconstructed signals show the contribution of the blade motion on GAF.

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Fig. 9

Estimated and measured forced response

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Fig. 10

Simplified configuration. A tiny block is representative of the upstream row.

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Fig. 11

Colormap of stagnation pressure at the inlet of simplified configuration

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Fig. 12

Tip vortex visualization for tip clearances ranging from 0% to 2% of span. The vortexes are shown at five consequent planes using entropy color-map.

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Fig. 13

Pitchwise averaged of mass flow rate at the plane perpendicular to the rotational axis passing through the trailing edge at the hub

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Fig. 14

Deviation of local pressure coefficient with respect to the zero tip gap, Cp – Cp0%, at 20%, 50%, 70%, 90%, and 95% of blade span

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Fig. 15

Normalized value of the local aerodynamic damping for five tip clearance setting

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Fig. 16

Variation of the nondimensional aerodynamic damping versus tip clearance for the case 1F-10φ-10 N. The aerodynamic damping is normalized by the value of 1% tip clearance.

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Fig. 17

Norm of excitation forces versus tip clearance for the case 1F-10φ-10 N. The norm is normalized by the value of 1% tip clearance.

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Fig. 18

Maximum forced response versus tip clearance for the case 1F-10φ-10 N. The forced response normalized by the value of 1% tip clearance.

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