Long-to-Short Length-Scale Transition: A Stall Inception Phenomenon in an Axial Compressor With Inlet Distortion

[+] Author and Article Information
Feng Lin

Applied Research Center, Indiana Institute of Technology, Fort Wayne, IN 46803flin@indianatech.edu

Meilin Li, Jingyi Chen

Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, People’s Republic of China

J. Turbomach 128(1), 130-140 (Feb 01, 2005) (11 pages) doi:10.1115/1.2098808 History: Received October 01, 2004; Revised February 01, 2005

A theoretical and experimental study of stall inception processes in a three-stage low-speed axial flow compressor with inlet distortion is presented in this paper. Since inlet distortion provides asymmetric flows imposing onto the compressor, the main goal of this research is to unveil the mechanism of how such flows initiate long and/or short length-scale disturbances and how the compression system reacts to those disturbances. It is found that the initial disturbances are always triggered by the distorted flows, yet the growth of such disturbances depends on system dynamics. While in many cases the stall precursors were the short length-scale spikes, there were some cases where the compressor instability was triggered after the disturbances going through a long-to-short length-scale transition. A Moore-Greitzer-based (system scale) model was proposed to qualitatively explain this phenomenon. It was found that, when the compressor operated in a region where the nonlinearity of the characteristics dominated, long length-scale disturbances induced by the inlet distortion would evolve into short length-scale disturbances before they disappeared or triggered stall. However, the model was not able to predict the fact that many disturbances that were triggered by the distorted sector(s) were completely damped out in the undistorted sector(s). It is thus suggested that in future research of compressor instability, one should consider the flows in blade passage scale, the dynamics in system scale, and their interaction simultaneously.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 1

The test compressor and probe locations

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Figure 2

Tested distortion cases. The numbers indicate the locations of the pressure sensors.

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Figure 3

The lumped system model with inlet distortion

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Figure 4

Test results of steady clean and distorted compressor characteristics (case 90mup in Fig. 2)

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Figure 5

Test results of steady stall limits with distortion

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Figure 6

Simulated distorted background flows

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Figure 7

(a) A segment of time series for pressure for case 90mup; (b) The wavelet spectrum of the data in (a); (c) The global wavelet spectrum for the same data; (d) The Fourier power spectrum. The horizontal axes in (a) and (b) are time axis in rotor revolutions before stall onset. f∕frot means the frequency as multiples of the rotor rotating frequency.

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Figure 8

Segments of time series from all seven pressure sensors and their wavelet spectra placed side-by-side

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Figure 9

Simulated time traces of eight virtual velocity probes

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Figure 10

Simulated velocity contours

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Figure 11

Simulated growth of the first five spatial Fourier modes

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Figure 12

Test data and wavelet spectra of case 1×30up

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Figure 13

Test data and wavelet spectra of case 1×30down

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Figure 14

Simulated results for case 1×30

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Figure 15

Wavelet spectra of test results case for 2×30×180

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Figure 16

Wavelet spectra of test results of case 4×30

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Figure 17

Simulated scenario 1 for case 2×30×90

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Figure 18

Simulated scenario 2 for case 2×30×90

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Figure 19

Simulated scenario 3 for case 2×30×90

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Figure 20

Wavelet spectra of test results for case 2×30×90




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