Numerical Investigation of a Transonic Axial Compressor Stage with Inlet Distortions
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Publisher
Springer Berlin Heidelberg
Link
http://link.springer.com/content/pdf/10.1007/978-3-642-13872-0_16.pdf
Reference17 articles.
1. Longley, J.P. and Greitzer, E.M. 1992: Inlet distortion effects in aircraft propulsion system integration. AGARD-LS-183
2. Cousins, W.T. 2004: History, philosophy, physics, and future directions of aircraft propulsion system inlet integration. ASME Paper GT2004-54210
3. Schmid, N.R., Leinhos, D.C., and Fottner, L. 2000: Steady performance masurements of a turbofan engine with inlet distortions containing co- and counter-rotating swirl from an intake diffuser for hypersonic flight. ASME Paper 2000-GT-11
4. Peters, T., Bürgener, T., and Fottner, L. 2001: Effects of rotating inlet distortions on a 5-stage HP compressor. ASME Paper 2001-GT-0300
5. Peters, T. and Fottner, L. 2002: Effects of co- and counter-rotating inlet distortions on a 5-stage HP-compressor. ASME Paper 2002-GT-30395
Cited by 2 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Supersonic centrifugal compressor flow part optimization experience;AIP Conference Proceedings;2018
2. Numerical investigation of effect of inlet swirl and total-pressure distortion on performance and stability of an axial transonic compressor;Journal of Thermal Science;2016-11-11
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