Experimental and numerical study of tip injection in a subsonic axial flow compressor

Wang, Wei; Chu, Wuli; Zhang, Haoguang; Kuang, Haiyang

doi:10.1016/j.cja.2017.04.004

Cited by 27 publications

(14 citation statements)

References 28 publications

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“…The results concluded that tip injector at stator can greatly increase the performance of the compressor. Wei Wang et al [22] and Mingcong Luo et al [23] studied the performance of a transonic axial flow compressor stage and investigated the unsteady effects of discrete tip injection and the effects of the size of the tip injector on the performance of the compressor. By controlling the size of the tip injector, injection efficiency can be achieved which correlates to improve flow stability.…”

Section: Introductionmentioning

confidence: 99%

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

Srinivas

Raghunandana

Shenoy

2022

J. Inst. Eng. India Ser. C

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The aerodynamic performance and pressure ratio of modern aircraft engine compressor are degrading due to unsteady flow distorted aerodynamic loads and complex phenomena in the blade tip. This paper attempts to improve the performance of modern axial flow transonic compressor stage under distorted flow conditions by incorporating the combination of groove casing, tip injection technique with surface roughness effects. This is performed for the Mach number ranging between 0.8 and 1.3. The obtained numerical results are compared with experimental studies and found to be in good agreement. Through the numerical analysis, the compressor stage flow interaction with the shock waves as well as vortex formation and boundary layer separation is studied in detail. While evaluating the performance of the axial flow compressor, more emphasis is given to the flow properties like pressure, density, temperature, velocity, etc. The performance improvement is observed at a particular Mach number for a specified aerodynamic flow property.

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Section: Introductionmentioning

confidence: 99%

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

Srinivas

Raghunandana

Shenoy

2022

J. Inst. Eng. India Ser. C

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“…(Hoying et al 1998;Davis et al 2006) At present, there are mainly two methods for improving the stall margin of the compressor: the active control method and the passive control method. Active control methods include blade tip inject (Li et al 2019;Wang et al 2017), plasma excitation (Degiorgi et al 2016), etc. Passive control methods include slot-type casing treatment (Zhang et al 2020), groove-type casing treatment (Liu et al 2016), end wall molding technology (Chu et al 2016), etc.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Blade Tip Recess Improving the Aerodynamic Performance of Transonic Axial Flow Compressor

Yan

Chu

Liu

et al. 2021

JAFM

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The development of high-performance aero engines put forward higher performance requirements for compressor components, and the improvement of aerodynamic performance of compressors has important engineering application value. The blade tip recess has great potential and advantages in improving the aerodynamic performance of compressors. In order to better understand the effect of the blade tip recess on the compressor aerodynamic performance, in this paper, the influence mechanism of the blade tip recess on the aerodynamic performance of the isolated rotor of a transonic axial compressor stage is discussed. Under the premise that the numerical method's results are almost consistent with the experimental test results, the full three-dimensional unsteady numerical results show that the main reason for the original blade rotor stall is the leading edge of the blade tip blockage, which is caused by blade tip clearance leakage vortex breakage. After adopting the measures of the blade tip recess, the study shows that the blade tip recess can increase the rotor stall margin by 2.10% without reducing the rotor efficiency and the total pressure ratio. A detailed analysis of the blade tip flow field shows that the blade tip recess can reduce the intensity of the tip clearance leakage flow by increasing the turbulence intensity of the blade tip near the casing wall, and reduces the leading edge of blade tip blockage, improves the rotor blade tip flow field, thereby achieving the purpose of enhancing rotor stability.

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“…It is shown that the level of flow non-uniformity after the impeller reduces. In article [7], authors presented results of research into combined use of discrete injection into peripheral part of the compressor and over-the-rotor unit. It is shown that optimal parameters can improve gas-dynamic stability of the com-…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…Results of studies [1][2][3][4][5][6][7][8][9][10] demonstrated effectiveness of gas-dynamic action on the current in a compressor. At the same time, there are still unresolved problems related to the choice of optimal parameters of the gas-dynamic action.…”

Section: L a S T I V K Amentioning

confidence: 99%

See 1 more Smart Citation

Examining the effect of annular injection on the parameters of the axial compressor’s stage

Tereshchenko

Дорошенко

Lastivka

2017

EEJET

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Experimental and numerical study of tip injection in a subsonic axial flow compressor

Cited by 27 publications

References 28 publications

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

Investigation on the Mechanism of Blade Tip Recess Improving the Aerodynamic Performance of Transonic Axial Flow Compressor

Examining the effect of annular injection on the parameters of the axial compressor’s stage

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