eprintid: 22668 rev_number: 10 eprint_status: archive userid: 1903 dir: disk0/00/02/26/68 datestamp: 2014-11-12 17:43:40 lastmod: 2014-11-12 17:43:40 status_changed: 2014-11-12 17:43:40 type: article metadata_visibility: show item_issues_count: 0 creators_name: Moreno Benavides, Efren creators_name: López Juste, Gregorio title: Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compresor Rotor rights: by-nc-nd ispublished: pub subjects: aeronautica full_text_status: public keywords: axial compressor, stability, surge, stall, performance, compressor map, stability line, inception abstract: Recently, a theoretical criterion to calculate the stability of an axial-flow compressor rotor has been presented in the scientific literature. This theoretical criterion was used for determining the locus of the stability line over the rotor map and for predicting the post-stall evolution of the constant-speed line of a rotor. The main objective of this paper is to improve the predictions of such a model. To do that, the paper proposes a different characterization of the characteristic azimuthal length and a calculation of the ratio of specific heats based on a polytropic exponent. Thanks to these new values, the model predicts two bifurcation points in the behaviour of the flow: the inception point of the instability and the surge point. Experimental data from a pure axial compressor are used to validate the model showing that the prediction of the flow coefficient at the surge point has an error inferior to 5%. For the rotor studied, the paper provides a quantitative and qualitative description of the inception of the instability and of the mechanism involved in the instable region of the compressor map. The paper also discusses the role of rotor efficiency in the position of the bifurcations and gives a sensitivity analysis of its position. Finally, it presents a discussion about how the model can explain the different behaviours exhibited by the same rotor when the flow coefficient is reduced date_type: published date: 2012 publication: International Journal of Turbo And Jet Engines volume: 29 number: 4 pagerange: 243-257 id_number: 10.1515/tjj-2012-0010 institution: Aeronauticos department: Motopropulsion refereed: TRUE issn: 0334-0082 official_url: http://www.degruyter.com/view/j/tjj.2012.29.issue-4/tjj-2012-0010/tjj-2012-0010.xml referencetext: 1 Hoying, D.A., Stall Inception in a Multistage High-Speed Axial Compressor, Journal of Propulsion and Power, Vol. 11, no. 5, 1995, pp.915-922 2 Dhingra, M., Neumeier, Y., and Prasad, J.V.R., Stall and Surge precursosrs in Axial Compressors, AIAA 2003-4425 3 McDougall, N.., Cumpsty, N.A., and Hynes, T.P., Stall Inception in Axial Compresors, Journal of Turbomachinery, Vol. 112, 1990, pp. 116-125 4 Sane, .K., and Tagade, P., Effect of Rotor Solidity on Stall Inception and Growth in Axial Flow Fan, AIAA 2004-3550 5 He, L., Computational Study of Rotating-Stall Inception in Axial Compressors, Journal of Propulsion and Power, Vol. 13, no. 1, 1997, pp. 31-38 6 Gogoi, A., Verma, S., Sane, S.K., A Model for Rotati ng Stall and Surge in Axial Flow Compressors, AIAA 2002-4086 7 Markopoulus, N., Neumeier, Y., Prasad, J.V.R. and Zinn, B.T. 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Escuret, J., Cherrett, M. and Wilson, A., Stall Inception and the prospects for active control in four high speed compressors, ASME J. Turbomachinery, Vol. 121, pp. 18-27 citation: Moreno Benavides, Efren and López Juste, Gregorio (2012). Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compresor Rotor. "International Journal of Turbo And Jet Engines", v. 29 (n. 4); pp. 243-257. ISSN 0334-0082. https://doi.org/10.1515/tjj-2012-0010 . document_url: http://oa.upm.es/22668/1/INVE_MEM_2012_153150.pdf