Partial tip air injection to extend the stall margin in an axial flow compressor with circumferential inlet distortion

Li, Jichao; Liu, Yang; Liu, Jingyuan; Peng, Feng; Zhang, Hongwu

doi:10.1016/j.ast.2023.108810

Cited by 4 publications

(1 citation statement)

References 18 publications

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“…Due to the extremely important role of the status, extremely demanding working environment, and extremely strict performance and safety requirements, flow control for axial flow compressors, expanding their stable working range, and improving their aerodynamic performance have always been one of the hot research topics in this field. Common flow control strategies include boundary layer suction [1,2], plasma excitation [3,4], casing treatment [5][6][7], or air injection [8][9][10]. These methods either require complex external piping systems or significantly reduce the efficiency of the compressor.…”

Section: Introductionmentioning

confidence: 99%

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Wang,

Wu,

Liao

et al. 2024

Applied Sciences

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In order to investigate the effect of a synthetic jet arranged at the suction surface on the aerodynamic performance of an axial flow compressor, a high-speed subsonic axial flow compressor rotor was numerically simulated in this paper. The results showed that after being excited by the synthetic jet, the flow margin of the compressor decreased by 1.3%, but the peak efficiency increased by 0.47%. After analyzing the internal flow field, it was found that although the alternating blowing and suction effect of the synthetic jet can reduce the separation loss of the suction surface, the radial velocity of the flow is higher when stimulated and converges towards the blade tip, resulting in more severe blockage at the blade tip than in the prototype compressor, leading to a slight decrease in stability margin. To balance the stability margin of the compressor, a coupled flow control numerical simulation combining passive control of the casing treatment and active control of the suction surface synthetic jet was subsequently carried out. The results showed that the coupled flow control could exert their respective advantages, resulting in an increase of 17.84% in the compressor flow margin and a decrease of only 0.2% in peak efficiency.

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Section: Introductionmentioning

confidence: 99%

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Wang,

Wu,

Liao

et al. 2024

Applied Sciences

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An improved wiener filter-based method for identifying stall inception of transonic compressor

Yuan,

Liu,

Yan

et al. 2024

Aerospace Science and Technology

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Influence of tip air injection on the unsteady blade force under circumferential pressure distortion

Li,

Peng,

Zhang

et al. 2024

Physics of Fluids

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In order to further understand the impact of tip air injection on compressor stability under circumferential pressure distortion, a series of experimental studies on tip air injection under uniform and circumferential distortion were conducted on a low-speed single rotor axial flow compressor. The unsteady measurements were carried out by use of microsensors and strain gauges bonded on the rotor blade surfaces, and a collection of dynamic pressure sensors installed on the casing wall. Results indicate that with the increase in the injected momentum ratio, the load at the leading edge near the rotor blade tip obviously decreases, thereby delaying the stall. By comparing the pressure distribution on the rotor blade surface under different injected momentum ratios, tip air injection can effectively suppress flow separation at the blade tip to enhance flow capability. In addition, it can also weaken the fluctuation of tip leakage flow and reduce the dynamic stress similar to natural vibration near the blade root both in stationary and rotating coordinate systems. Under the condition of inlet circumferential distortion, tip air injection can significantly reduce the load at the distorted region and suppress the low-frequency disturbances measured on the rotor blade surface caused by inlet distortion. In addition, the dynamic stress near the blade root can also be effectively reduced by tip air injection. It implies that tip air injection can both extend the stall margin and reduce blade vibration when suffering from circumferential distortion; thus, the compressor can safely operate.

show abstract

Partial tip air injection to extend the stall margin in an axial flow compressor with circumferential inlet distortion

Cited by 4 publications

References 18 publications

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

Influence of Active Flow Control of Synthetic Jet at Suction Surface on the Performance of a Subsonic Axial Compressor Rotor

An improved wiener filter-based method for identifying stall inception of transonic compressor

Influence of tip air injection on the unsteady blade force under circumferential pressure distortion

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