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

The performance of a compressor cascade is considerably influenced by flow control methods. In this paper, the synergistic effects of combination between micro-vortex generators (MVG) and boundary layer suction (BLS) are discussed in a high-load compressor cascade. Seven cases, which are grouped by a kind of micro-vortex generator and boundary layer suction with three locations, are investigated to control secondary flow effects and enhance the aerodynamic performance of the compressor cascade. The MVG is mounted on the end-wall in front of the passage. The rectangle suction slot with three radial positions is installed on the blade suction surface near the trailing edge. The numerical results show that: at the design condition, the total pressure loss is effectively decreased as well as the static pressure coefficient increase when the combined MVG and SBL method (COM) is used, which is superior to MVG in an aerodynamic performance. At the stall condition, the induced vortex coming from MVG could mix the low-energy fluid and mainstream, which result in the reduced separation, and the total pressure loss decreased by 11.54% when the suction flow ratio is 1.5%. The total pressure loss decreases by 14.59% when the COM control methods are applied.

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

Proceedings of the Institution of Mechanical Engineers Part C Journal of Mechanical Engineering Science ◽

10.1177/0954406220980502 ◽

2021 ◽

pp. 095440622098050

Author(s):

Shan Ma ◽

Wuli Chu ◽

Xiaolin Sun ◽

Zhengtao Guo ◽

Song Yan

Keyword(s):

Boundary Layer ◽

Pressure Loss ◽

Total Pressure ◽

Vortex Generator ◽

Total Pressure Loss ◽

Compressor Cascade ◽

Boundary Layer Suction ◽

Axial Location ◽

Micro Vortex Generator ◽

Suction Slot

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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The Cost of Flow Control in a Compressor

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

10.1115/gt2011-45059 ◽

2011 ◽

Cited By ~ 3

Author(s):

Simon W. Evans ◽

Howard P. Hodson

Keyword(s):

Boundary Layer ◽

Flow Control ◽

Vortex Generator ◽

Control Methods ◽

Compressor Cascade ◽

Suction Surface ◽

Boundary Layer Suction ◽

Blade Row ◽

Efficiency Increase ◽

The Cost

This paper documents an analysis performed to estimate the cycle cost of flow control in a compressor. The analysis is based on a series of experiments conducted in a low-speed compressor cascade at high incidence. In these experiments, flow control was applied to delay a turbulent separation on the suction surfaces of the blades in the cascade. The flow control methods studied include boundary layer suction and both steady and pulsed vortex generator jets. Endwall control was also applied to remove corner separations. Tip gaps and endwall suction were both studied for this purpose. The flow control methods studied were able to successfully delay a separation occurring on the suction surface of the blades, reducing the loss coefficient. The mass flow rates and jet supply pressures required to achieve control in each case were used to model a single flow-controlled blade row in a typical turbofan cycle using cycle analysis software. The cost of control to the cycle was calculated as the polytropic compressor efficiency increase required to maintain thrust relative to a conventional cycle with no flow control. The results of the analysis show that the benefits of flow control significantly outweigh the cost. They also show that boundary layer suction coupled with endwall suction yields the lowest cycle cost. This is because of the small pressure difference required to drive suction, which allows reinjection of the aspirated air a short distance upstream of the flow controlled blade row.

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Effects of Boundary Layer Suction on Aerodynamic Performance in a High-load Compressor Cascade

Chinese Journal of Aeronautics ◽

10.1016/s1000-9361(09)60202-8 ◽

2010 ◽

Vol 23 (2) ◽

pp. 179-186 ◽

Cited By ~ 6

Author(s):

Guo Shuang ◽

Chen Shaowen ◽

Song Yanping ◽

Song Yufei ◽

Chen Fu

Keyword(s):

Boundary Layer ◽

Aerodynamic Performance ◽

High Load ◽

Compressor Cascade ◽

Boundary Layer Suction

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Effect of Boundary Layer Suction on Aerodynamic Performance of High-Turning Compressor Cascade

Volume 6A: Turbomachinery ◽

10.1115/gt2013-94907 ◽

2013 ◽

Cited By ~ 1

Author(s):

Longxin Zhang ◽

Shaowen Chen ◽

Hao Xu ◽

Jun Ding ◽

Songtao Wang

Keyword(s):

Experimental Data ◽

Boundary Layer ◽

Experimental Studies ◽

Aerodynamic Performance ◽

Parameter Distribution ◽

Compressor Cascade ◽

Boundary Layer Suction ◽

End Wall ◽

Low Speed Wind Tunnel ◽

Good Agreement

Compared with suction slots, suction holes are (1) flexible in distribution; (2) alterable in size; (3) easy to fabricate and (4) high in strength. In this paper, the numerical and experimental studies for a high turning compressor cascade with suction air removed by using suction holes in the end-wall at a low Mach numbers are carried out. The main objective of the investigation is to study the influence of different suction distributions on the aerodynamic performance of the compressor cascade and to find a better compound suction scheme. A numerical model was first made and validated by comparing with the experimental results. The computed flow visualization and exit parameter distribution showed a good agreement with experimental data. Second, the model was then used to simulate the influence of different suction distributions on the aerodynamic performance of the compressor cascade. A better compound suction scheme was obtained by summarizing numerical results and tested in a low speed wind tunnel. As a result, the compound suction scheme can be used to significantly improve the performance of the compressor cascade because the corner separation gets further suppressed.

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Control of Corner Separation in a Linear Highly Loaded Compressor Cascade by Boundary Layer Suction

Fluid-Structure-Sound Interactions and Control - Lecture Notes in Mechanical Engineering ◽

10.1007/978-3-662-48868-3_49 ◽

2015 ◽

pp. 307-311

Author(s):

Yangwei Liu ◽

Jinjing Sun ◽

Lipeng Lu

Keyword(s):

Boundary Layer ◽

Compressor Cascade ◽

Corner Separation ◽

Boundary Layer Suction ◽

Highly Loaded

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Location Effect of Boundary Layer Suction on Compressor Hub-Corner Separation

Volume 2A: Turbomachinery ◽

10.1115/gt2014-25043 ◽

2014 ◽

Cited By ~ 3

Author(s):

Ping-Ping Chen ◽

Wei-Yang Qiao ◽

Karsten Liesner ◽

Robert Meyer

Keyword(s):

Boundary Layer ◽

Pressure Loss ◽

Total Pressure ◽

Three Dimensional ◽

Base Flow ◽

Total Pressure Loss ◽

Compressor Cascade ◽

Suction Surface ◽

Corner Separation ◽

Boundary Layer Suction

The large secondary flow area in the compressor hub-corner region usually leads to three-dimensional separation in the passage with large amounts of total pressure loss. In this paper numerical simulations of a linear high-speed compressor cascade, consisting of five NACA 65-K48 stator profiles, were performed to analyze the flow mechanism of hub-corner separation for the base flow. Experimental validation is used to verify the numerical results. Active control of the hub-corner separation was investigated by using boundary layer suction. The influence of the selected locations of the endwall suction slot was investigated in an effort to quantify the gains of the compressor cascade performance. The results show that the optimal chordwise location should contain the development section of the three-dimensional corner separation downstream of the 3D corner separation onset. The best pitchwise location should be close enough to the vanes’ suction surface. Therefore the optimal endwall suction location is the MTE slot, the one from 50% to 75% chord at the hub, close to the blade suction surface. By use of the MTE slot with 1% suction flow ratio, the total-pressure loss is substantially decreased by about 15.2% in the CFD calculations and 9.7% in the measurement at the design operating condition.

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