Combined application of negative bowed blades and unsteady pulsed holed suction in a high-load compressor in terms of aerodynamic performance and energy efficiency

Chen, Shaowen; Gong, Yun; Wang, Songtao; Wang, Zhongqi

doi:10.1016/j.applthermaleng.2018.08.046

Cited by 11 publications

(3 citation statements)

References 40 publications

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“…In order to reduce the computer resource and time cost, only one blade passage is simulated in the present investigation because of the periodicity of the compressor. In addition, according to the previous results (Zhang et al, 2018), the flow field in the upper half passage and lower half passage are the same at the present boundary condition; hence, only half of the blade passage is simulated. In this paper, three configurations are calculated, the baseline configuration, the CS configuration, and the PS configuration, and the calculation model is shown in Figures 1B, C.…”

Section: Methodsmentioning

confidence: 65%

“…A lot of work has been done on the flow field details in the high-loading compressor (Gbadebo et al, 2005;Gbadebo et al, 2008;Lei et al, 2008;Wei et al, 2013;Zambonini et al, 2017). Besides, the passive flow control methods, such as lean or sweep blade (Denton and Xu, 2002;Zhang et al, 2018), end-wall contouring (Heinichen et al, 2011;Sun et al, 2018;Sun et al, 2019), and vortex generator (Evans and Hodson, 2010), have been widely investigated to improve the compressor performance. Compared with the passive ones, the active flow control methods (Kerrebrock et al, 1997;Kerrebrock et al, 2008;Jabbal et al, 2013) can adjust according to the operating condition of the compressor; hence, they may be applied as more flexible in many cases, especially for some highly maneuverable aircraft.…”

Section: Introductionmentioning

confidence: 99%

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Active Flow Control Based Bleed in an Axial Compressor Cascade Using Large Eddy Simulation

et al. 2022

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The performance of the compressor is of great importance in developing advanced engine technology, and it dramatically influences the cycle efficiency and safety of the engine. The compressor bleed requires a part of the main flow extraction from the passage, and the removal of the airflow plays an essential role in the performance of the compressor. The influence of the constant suction and pulsed suction on the flow structures and the aerodynamic performance in a compressor cascade, and the control mechanisms are numerically studied using large eddy simulation. At a suction mass flow rate of 0.25% of the main flow rate, constant suction leads to a 9.36% reduction in Cpt, while pulsed suction gains 24% more benefit in Cpt reduction on the basis of the constant suction with an excitation frequency of 100 Hz. It indicates that the pulsed suction has more significant potential to control the loss generation in the compressor. Afterward, the flow field of the baseline, constant suction, and pulsed suction are compared to find out the flow control mechanisms of the constant suction and pulsed suction. Two different formation mechanisms of the passage vortex are found due to the excitation effect of the pulsed suction. Besides, the results of proper orthogonal decomposition and dynamic mode decomposition show that the pulsed suction can simplify and stabilize the compressor flow field, which could lead to a further benefit in Cpt.

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Section: Methodsmentioning

confidence: 65%

Section: Introductionmentioning

confidence: 99%

Active Flow Control Based Bleed in an Axial Compressor Cascade Using Large Eddy Simulation

et al. 2022

Self Cite

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show abstract

“…In order to eliminate flow separation in compressors, passive flow control techniques such as endwall profiling, 10 curved blading, 11 blade-end slot 12,13 as well as active flow control techniques such as boundary layer suction 14,15 and air injection (or blowing) 16,17 have been studied previously. As a passive flow control technique, vortex generator can be used to not only regulate the external flow 18 such as strake wing, 19 but also control the internal flow in aero-engine.…”

Section: Introductionmentioning

confidence: 99%

Performance enhancing for a highly loaded tandem cascade by endwall incoming vortex–corner separation interaction

Cao

Gao

Song

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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In highly loaded tandem compressor cascades, corner separations can still exist. In order to eliminate corner separations in highly loaded tandem compressor cascades, incoming vortex–corner separation interaction mechanism was investigated. Different schemes of the vortex generators, which located at different pitchwise locations and could generate vortexes with different rotation directions, were designed and investigated numerically. Results show that, severe corner separation occurred at the front blade passage of the tandem cascade; by utilizing flow control method of incoming vortex–corner separation interaction, the corner separation could be reduced significantly. The optimal control effect of incoming vortex on corner separation was achieved with anticlockwise rotation and the vortex generator is located right ahead of the leading edge of tandem cascade, a maximum loss coefficient reduction of 21.8% being achieved. Different from single blade configuration, the boundary layer of tandem cascade was regenerated at rear blade suction surface due to the injection flow from blade gap between the two blades. Though corner separations could be reduced at both conditions, the loss of tandem cascade with clockwise incoming vortex is higher than that with anticlockwise vortex, and a smaller corner separation region at suction surface was achieved by utilizing clockwise vortex. The mechanism was that anticlockwise incoming vortex reduced the corner separation but increased secondary flow, while clockwise vortex enhanced passage vortex and decreased secondary flow. For clockwise incoming vortex near pressure surface, the vortex would be divided into two parts at the leading edge of rear blade, one would go through the blade gap and deteriorate flow fluid near rear blade suction surface, the other flowed downstream along pressure surface. The rotation direction of different incoming vortexes became the same as the passage vortex at rear blade passage of tandem cascade, which was mainly due to the effect of secondary flow.

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A comparative experimental analysis of two unsteady flow control methods in a highly loaded compressor cascade

Chen

2020

Exp Fluids

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Combined application of negative bowed blades and unsteady pulsed holed suction in a high-load compressor in terms of aerodynamic performance and energy efficiency

Cited by 11 publications

References 40 publications

Active Flow Control Based Bleed in an Axial Compressor Cascade Using Large Eddy Simulation

Active Flow Control Based Bleed in an Axial Compressor Cascade Using Large Eddy Simulation

Performance enhancing for a highly loaded tandem cascade by endwall incoming vortex–corner separation interaction

A comparative experimental analysis of two unsteady flow control methods in a highly loaded compressor cascade

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