Role of the Hub-Corner-Separation on the Rotating Stall

Choi, Minsuk; Baek, Je Hyun; Oh, Seong Hwan; Ki, Dock Jong

doi:10.2514/6.2006-4462

Cited by 4 publications

(2 citation statements)

References 18 publications

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“…Hence, in the past few decades, it was always a key flow phenomenon concerned by compressor aerodynamicists. Great amount of researches were conducted for clarifying the flow mechanisms and aerodynamic features in turbomachinery by experimental, theoretical, and numerical methods [4][5][6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Zhang

Liu

2013

Experimental Thermal and Fluid Science

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Section: Introductionmentioning

confidence: 99%

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Zhang

Liu

2013

Experimental Thermal and Fluid Science

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“…Several researchers presented that the corner separation decreased the compressor stability. 11,12 To improve the blade performance, many designers tried to control the corner separation by using the bowed blade 13 or sucking the low-momentum flow. 14 As previously mentioned, the compressor stability is dominated by the complicated secondary flows.…”

Section: Introductionmentioning

confidence: 99%

Effects of low Reynolds number on flow stability of a transonic compressor

Zhao

Zhu

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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As the aircraft cruising at high altitude over 20,000 m with subsonic speed, the Reynolds number in terms of the compressor blade becomes very low and the compressor performance decreases dramatically due to separation of boundary layer and secondary-flow. The main objective in this paper is to understand the physical mechanism by which Reynolds number affects the compressor stable range. In this paper, a series of steady and unsteady numerical simulations were carried out for a transonic compressor rotor under several conditions, which corresponded to the operations at sea level, and at high altitude. Detailed analyses of the flow visualization have exposed the different flow topologies of the complicated secondary flow. It was found that the transonic axial-flow compressor rotor used in current investigation was prone to tip stall behavior, and the complex flow mechanisms which occur near the blade tip are found to be the key factors for the limited flow stability both under high Reynolds number and low Reynolds number. Under high Reynolds number, the tip flow field was dominated by the low momentum zones generated by the interaction between tip leakage flow and incoming flow, and with the decrease of Reynolds number, the tip leakage flow was weakened and the low-momentum fluid due to the surface boundary layer separation and radial transport of lowenergy fluid was dominant in the tip flow.

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A Prediction Model for Corner Separation/Stall in Axial Compressors

Liu

2010

Volume 7: Turbomachinery, Parts A, B, and C

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Endwall corner stall can cause significant aerodynamic blockage and losses production. Hence, pre-prediction of it during the preliminary processes of compressors is important. However, Lieblein’s diffusion factor often fails near the endwall region for the strong three-dimensionality flow effects. A new model for predicting endwall corner stall phenomenon in axial compressors was developed based on the methodology used by Lei et al. [1] (J. Turbomach. 2008, 031006). At first, the influencing factors for the flows of endwall corner separation/stall were analyzed by numerical simulations. The results showed that, besides the parameters determining the loading of a two-dimensional blade profile, blade aspect ratio was also a key factor. Then, by using both the theoretical and empirical methods, a modified diffusion parameter, which can be used as a criterion for axial compressor corner stall, was defined to consider the combined effects of three factors: the streamwise pressure gradient, the circumferential pressure gradient and the passage mass-flow-rate redistribution effect (controlled mainly by blade aspect ratio). Finally, the stall criterion was validated by experimental results of various test facilities with different blade geometries and experimental conditions. The results showed that the modified diffusion parameter can predict the corner separation/stall flows in a good agreement with the experimental results in axial compressors without blade three-dimensional designs.

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Role of the Hub-Corner-Separation on the Rotating Stall

Cited by 4 publications

References 18 publications

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Effects of low Reynolds number on flow stability of a transonic compressor

A Prediction Model for Corner Separation/Stall in Axial Compressors

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