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TECHNICAL PAPERS

The Influence of Transient Inlet Distortions on the Instability Inception of a Low-Pressure Compressor in a Turbofan Engine

[+] Author and Article Information
Dirk C. Leinhos, Norbert R. Schmid, Leonhard Fottner

Institut für Strahlantriebe, Universität der Bundeswehr München, D-85577 Neubiberg, Germany

J. Turbomach 123(1), 1-8 (Feb 01, 2000) (8 pages) doi:10.1115/1.1330271 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Propulsion system of a hypersonic aircraft
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Inlet distortion generator (CO configuration)
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LARZAC 04 C5 design point performance data
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Positions of miniature pressure probes
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Sensor position relative to the CO (top) and COUNTER (bottom) distortion (viewed upstream)
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Wavelet transformation and statistical evaluation
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Cutaway of the LPC compressor map
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Time series of static pressure, nθ LPC=53 percent, CO, steady
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PSD of SFT’s second harmonic, nθ LPC=79.5 percent, CO, steady
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The wca of level 13 at sensor 13 against time, nθ LPC=95 percent, CO, steady
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The wca of level 11 at sensor 1 against time, nθ LPC =53 percent, COUNTER, steady
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SFT of first harmonic, nθ LPC=76 percent, COUNTER, steady
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The wca of level 11 (top) and 12 (bottom) at sensor 3 against time, nθ LPC=95 percent, COUNTER, steady
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DPSD of SFT’s second harmonic, nθ LPC=80 percent, CO, transient
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TWE of SFT’s first harmonic, nθ LPC=95 percent, CO, transient
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The wca of level 9 (top) and 13 (bottom) at sensor 5 against time, nθ LPC=80 percent, COUNTER, transient
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TWE of SFT’s first harmonic, nθ LPC=95 percent, COUNTER, transient

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