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Licensed Unlicensed Requires Authentication Published by De Gruyter December 13, 2012

Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor

  • Efrén M. Benavides EMAIL logo and Gregorio L. Juste
From the journal Int. J. Turbo Jet-Engines


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%. The paper presents a discussion about how the model can explain the different behaviours exhibited by the same rotor when the flow coefficient is reduced.

ETSI Aeronáuticos (UPM), Pza. Cardenal Cisneros 3, 28040 Madrid, Spain

Received: 2012-02-23
Accepted: 2012-02-28
Published Online: 2012-12-13
Published in Print: 2012-12-18

©[2012] by Walter de Gruyter Berlin Boston

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