A combined application of micro-vortex generator and boundary layer suction in a high-load compressor cascade

Ma, Shuai; Chu, Wuli; Zhang, Haoguang; Li, Xiangjun; Kuang, Haiyang

doi:10.1016/j.cja.2019.03.034

Cited by 36 publications

(27 citation statements)

References 13 publications

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“…36,37 The developments of boundary layer and separation are effectively suppressed by the BLS on blade suction surface. According to the previous research, 33 the total pressure loss shows a decreasing trend as the location of full-span suction slot moving upstream. However, the influence of the axial location of the suction slot on the cascade performance at the off-design condition is not discussed.…”

Section: Effects Of Boundary Layer Suction On Cascade Performancementioning

confidence: 65%

“…32 However, the stable operating range is rarely used as the evaluation standard to measure the flow control mothed. In some previous works, 33 micro-vortex generator and a full-span boundary layer suction on the blade suction surface are combined and introduced in a compressor cascade, the total pressure loss is reduced and the occurrence of failure is delayed. However, the effects of suction slot structure on the compressor cascade are not analyzed.…”

Section: Introductionmentioning

confidence: 99%

“…A unique analysis method is applied to quantitatively analyze the aerodynamic performance of different flow control strategies, the method has been proved to be reasonable and intuitive to compare the performances of different flow control technologies. 33 In the current study, some main objectives will be achieved as following:…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Effects of segmented layer suction and micro-vortex generator on a high-load compressor cascade performance

Chu

Sun

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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The axial location of full-span boundary layer suction is studied to explore the influences of suction slot on the cascade performance. At the design condition, the slot with 50% axial location shows a superior capability to reduce the total pressure loss. At the near stall condition, the more upstream of the suction slot is moved, the more total pressure loss is reduced, and the suction slot with a location of 0.7 axial chord length cannot effectively reduces the total pressure loss in all conditions. Moreover, a rearranged segmented suction slot according to the distribution characteristics of the flow reversal region is developed and compared with full-span boundary layer suction. The segmented suction slot shows significant advantages in delaying the stall occurrence, and the stall point is delayed from 7.9° to 10.0° compared with the baseline. According to a quantitative analysis method selected to measure the performances of flow control technologies, the wake loss is significantly reduced by the segmented suction slot. Finally, a set of micro-vortex generator is introduced in the cascade with a segmented suction slot, and the conclusion indicates that the portion near the end-wall is very effective to reduce the flow loss.

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Section: Effects Of Boundary Layer Suction On Cascade Performancementioning

confidence: 65%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effects of segmented layer suction and micro-vortex generator on a high-load compressor cascade performance

Chu

Sun

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

Self Cite

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show abstract

“…So, it is easier to cause the separation of the boundary layer and the corner zone, resulting in huge flow loss, a decrease in aerodynamic efficiency, and may even induce rotating stall or surge, causing the compressor to enter an unstable working state. Therefore, on the basis of in-depth study of the complex flow mechanism in the compressor, proper flow control means are used to delay or weaken the flow separation, so that the compressor can not only maintain high-load operation, but also has a wide and stable working range and a high aerodynamic efficiency, which has become one of the research hotspots of the compressor aerodynamics in recent years (Ma et al 2019).…”

Section: Introductionmentioning

confidence: 99%

Effect of Active Flow Control of Endwall Synthetic Jet on the Performance of a Transonic Axial Compressor

2021

JAFM

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In order to improve the performance of a high-load transonic axial compressor, this paper proposes a method of applying endwall synthetic jet to the casing for active flow control. Taking NASA Rotor35 as the research object, the aerodynamic performance of the compressor is numerically calculated by applying three sets of synthetic jets with different excitation parameters at five different axial positions of 0%Ca, 25%Ca, 50%Ca, 75%Ca and 96.15%Ca. The results show that the three parameters of excitation position, jet peak velocity and jet frequency all have an effect on the performance of the compressor. The excitation position has the greatest influence on the flow margin of the compressor, and the best position is 25%Ca. After the jet peak velocity is increased from 100m/s to 150m/s, the flow margin, total pressure ratio and efficiency of the compressor are not greatly improved, which shows that the impact of the jet peak velocity is not as good as the excitation position. After continuing to increase the excitation frequency of the synthetic jet from 600Hz to 1200Hz, although the flow margin of the compressor is slightly reduced, the total pressure ratio and efficiency are further improved. This shows that there may be a threshold for the jet frequency, and only when the jet frequency is greater than the threshold can the overall aerodynamic performance of the compressor be improved.

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“…In particular, when the corner separation turns into a corner stall, large backflow will occur at the corner surrounded by the blade suction surface and the end wall [1,2], and the compressor performance will decrease rapidly [3,4]. Hence, to suppress the corner separation, especially to delay the occurrence of the corner stall, many active and passive control techniques has been proposed, like the air aspiration [5][6][7][8], air blowing [1,[9][10][11], vortex generators [6,12], three-dimensional blade stacking [2,13,14] and so on, while the cantilevered stator is still an efficient technique to be frequently used in practice.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

Liu

Qiu

et al. 2019

Applied Sciences

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Three-dimensional corner separation is common in axial compressors, which can lead to large flow loss and blockage especially when it evolves into the corner stall (open separation). In this paper, the evolution of the three-dimensional flow structures inside a cantilevered stator of a 1.5 stage low-speed highly loaded axial compressor as the stator hub clearance varies, and its effect on the whole compressor performance are investigated experimentally. Firstly, when the stator hub is sealed, the hub corner stall will occur at small mass flow rate conditions. Then, when a very small stator hub clearance is introduced, the leakage flow tends to strengthen the hub corner separation at large mass flow rate conditions and prompts the occurrence of hub corner stall as the mass flow rate decreases. This is mainly caused by the fact that the leakage flow has relatively low energy due to the viscosity effect in the clearance and large flow loss generation as the clearance flow comes across and mixes with the transverse secondary flow. Finally, when the stator hub clearance increases, the effect of the flow viscosity becomes very weak and could be ignored, so the enhanced leakage flow can suppress the transverse migration of the low energy flow near the hub, and the hub corner separation at large mass flow rate conditions could be weakened and the hub corner stall at small mass flow rate conditions could be removed or delayed. As the stator hub clearance varies, the flow structures inside the stator passage could be summarized into five typical flow structures, and this is closely associated with the performance of the compressor.

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A combined application of micro-vortex generator and boundary layer suction in a high-load compressor cascade

Cited by 36 publications

References 13 publications

Effects of segmented layer suction and micro-vortex generator on a high-load compressor cascade performance

Effects of segmented layer suction and micro-vortex generator on a high-load compressor cascade performance

Effect of Active Flow Control of Endwall Synthetic Jet on the Performance of a Transonic Axial Compressor

Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

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