The influence of transient inlet distortions on the instability inception of a low-pressure compressor in a turbofan engine

Journal of Turbomachinery

Volumn 123, Issue 1, 2001, Pages 1-8

  Leinhos, D C ^a   Schmid, N R ^a   Fottner, L ^a  

^a BUNDESWEHR UNIVERSITY MUNICH   (Germany)

Author keywords

[No Author keywords available]

Indexed keywords

ALGORITHMS; COMPRESSORS; FLOW OF FLUIDS; SUPERSONIC AIRCRAFT;

TRANSIENT INLET DISTORTIONS;

TURBOFAN ENGINES;

COMPRESSOR; DESIGN; ENGINE; FLUID FLOW; INSTABILITY;

EID: 0034877484     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1330271     Document Type: Article

References (18)

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4. Rotating stall control in a high-speed stage with inlet distortion: Part II- Circumferential distortion
5. Active stabilization of rotating stall in a transonic single stage axial compressor
6. Stall inception and the prospects for active control in four high speed compresors
7. Stall inception in a 5-stage HP-compressor with increased load due to inlet distortions
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11. Stall inception in the compressor system of a turbofan engine
12. A system for monitoring, measurement and analysis of transient performance and stall phenomena of gas turbine engines
13. Stall inception in axial compressors
14. Rotating waves as a stall inception indication in axial compressors
15. Pres-stall behavior of several high-speed compressors