A Model for Rotating Stall and Surge in Axial Flow Compressors

Gogoi, Aishwarjya; Varma, S. V. K.; Sane, S. K.

doi:10.2514/6.2002-4086

Cited by 3 publications

(4 citation statements)

References 8 publications

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“…There are methods based on analyzing pressure signals from sensors [13][14][15][16], based on solving computational models [17][18][19], or based on analytical or engineering models [20][21][22][23][24]. In this article the model will be based on a previous work of the authors [11] where a different description of the mean-line stability was recently presented based on the idea given in [23].…”

Section: Theoretical Backgroundmentioning

confidence: 97%

On the Theoretical Calculation of the Stability Line of an Axial-flow Compressor Stage

Benavides

2011

International Journal of Turbo and Jet Engines

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Recently, an analytical model to calculate the stability of an axial-flow compressor rotor has been presented in the scientific literature. The range of validity of that theoretical characterization was supported by several lemmas and theorems. One of the main results was the definition of a dimensionless coefficient for determining the location of the stability line in the rotor map. In this work the mathematical structure of that solution is studied. As a result of this detailed study, a new stability theorem and a new stability coefficient are obtained. This stability coefficient is an improvement of the previous one since it is physically and mathematically well defined in all the operational points of the compressor map. As a consequence, the new model is able to capture the stall inception for rotors and stators as well as the full characteristic curve (pressure rise versus mass flow rate) including rotating stall and possibly reverse flow. It is proved, as a consequence of the restriction imposed by the Stability Theorem, that each local component (rotor or stator) has its own instability point and its own post-stall characteristic curve. This theoretical criterion for predicting the averaged characteristic curve is in good accord with the experimental data. The stability coefficient is also verified for a compressor stage. Finally, the model is shown to provide an adequate quantitative and qualitative description of the averaged stall line giving a physical explanation of the mechanism involved in the instable region of the compressor map.

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Section: Theoretical Backgroundmentioning

confidence: 97%

On the Theoretical Calculation of the Stability Line of an Axial-flow Compressor Stage

Benavides

2011

International Journal of Turbo and Jet Engines

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“…Fluid Mechanics imposes six relationships between the dimensionless variables defined in Eqs. (6). (For the sake of simplicity, choke will not be considered in the model.)…”

Section: Basic Equationsmentioning

confidence: 99%

“…Due to its importance, there is a large number of articles trying to calculate the pressure rise characteristic over the entire flow-rate range of a compressor, which, indeed, requires a method for calculating or predicting the stall onset. There are methods based on analysing pressure signals from sensors [1][2][3][4], based on solving computational models [5][6][7], or based on analytical or engineering models [8][9][10][11][12]. A good review of the types of stall and surge behaviour can be found in Ref.…”

Section: Introductionmentioning

confidence: 99%

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

Benavides¹,

Juste²

2012

Int. J. Turbo Jet-Engines

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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.

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“…Gogoi [13] employed a CFD-based model to capture the onset of rotating stall and surge. The model employs quasi-3D Euler equations, and the results indicate that the two modes of instabilities were captured reasonably well for two compressors.…”

Section: Introductionmentioning

confidence: 99%

Estimations of Compressor Stall and Surge Using Passage Stall Behaviors

2022

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The predictions of the onset of rotating stall and surge are very important in the preliminary design stage of a compressor. Rotating stall and surge are complex instabilities that cause efficiency loss and reduced pressure rise, and, therefore, compressor designers attempt to avoid them in the design stage. There are many criteria for predicting stability limits, including empirical, theoretical, and numerical investigations in the literature. However, these investigations have important limitations. The present study establishes a new method in which the stall and post-stall behavior of a compressor is estimated by an equivalent reconstructed compressor using special combinations of single-passage flow behavior in different mass flow rates. The combinations are generated such that pre-stall, in-stall, and surge flow regimes and between one and eight stall cells are reproduced in the full-annulus compressor. The method requires the least computational requirements and is time efficient. The results indicate that secondary flow total energy and spectral entropy are indeed correlated with compressor operating conditions. The predictions of the onset of stall and surge for the investigated compressor show good agreement with the experimental data.

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A Model for Rotating Stall and Surge in Axial Flow Compressors

Cited by 3 publications

References 8 publications

On the Theoretical Calculation of the Stability Line of an Axial-flow Compressor Stage

On the Theoretical Calculation of the Stability Line of an Axial-flow Compressor Stage

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

Estimations of Compressor Stall and Surge Using Passage Stall Behaviors

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