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Research Papers

Unsteady Flow and Aeroelasticity Behavior of Aeroengine Core Compressors During Rotating Stall and Surge

[+] Author and Article Information
M. Vahdati, G. Simpson, M. Imregun

Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London SW7 2BX, UK

J. Turbomach 130(3), 031017 (May 06, 2008) (9 pages) doi:10.1115/1.2777188 History: Received February 20, 2007; Revised February 22, 2007; Published May 06, 2008

This paper will focus on two core-compressor instabilities, namely, rotating stall and surge. Using a 3D viscous time-accurate flow representation, the front bladerows of a core compressor were modeled in a whole-annulus fashion whereas the rest of bladerows were represented in single-passage fashion. The rotating stall behavior at two different compressor operating points was studied by considering two different variable-vane scheduling conditions for which experimental data were available. Using a model with nine whole bladerows, the unsteady flow calculations were conducted on 32 CPUs of a parallel cluster, typical run times being around 3–4 weeks for a grid with about 60×106 points. The simulations were conducted over several engine rotations. As observed on the actual development engine, there was no rotating stall for the first scheduling condition while malscheduling of the stator vanes created a 12-band rotating stall which excited the rotor blade first flap mode. In a separate set of calculations, the surge behavior was modeled using a time-accurate single-passage representation of the core compressor. It was possible to predict not only flow reversal into the low pressure compression domain but also the expected hysteresis pattern of the surge loop in terms of its mass flow versus pressure characteristic.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Compressor characteristic

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Figure 2

Steady-state flow domain

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Figure 3

Comparison of computed total pressure (▵) at rotor exit against test data (◻)

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Figure 4

Hybrid single-passage, whole-annulus model

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Figure 5

Mistuning pattern to initiate rotating stall

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Figure 6

Time history of negative axial flow at midpassage

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Figure 7

Hysteresis loop for mass flow versus pressure ratio

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Figure 8

Time history of mass flow and blade forcing (upper plot); Fourier components of forcing (lower plot)

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Figure 9

Overall performance: DS versus MS

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Figure 10

Front stage performance

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Figure 11

Total pressure along compressor

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Figure 12

Instantaneous static pressure upstream of Rotor 1: DS versus MS

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Figure 13

Static pressure upstream of Rotor 1 and its Fourier components at 70% and 90% height

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Figure 14

Development of stall cell

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Figure 15

Instantaneous negative axial velocity at 70% height

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Figure 16

Fourier components of axial velocity upstream of rotor blades

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Figure 17

Fourier components of forcing on the blade

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