The impact of various forward sweep angles on the performance of an ultra-high-load low-reaction transonic compressor rotor

Sun, Shijun; Wang, Songtao; Chen, Shaowen; Tao, Chen; Cai, Le; Chen, Jiawei

doi:10.1016/j.applthermaleng.2019.01.045

Cited by 23 publications

(8 citation statements)

References 41 publications

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“…Many scholars studying sweep in subsonic and transonic compressors have found that forward sweep in the tip region of a compressor rotor increases the stability of the tip region. This is supported by (Passrucker et al,2003;Sun, S. et al,2019). However, there is a controversy about the effect of backward sweep also can increases the stall margin of axial compressors in different operating conditions via means of matching the blade loading of the infinitesimal compressor along span over the stable operation range.…”

Section: Introductionmentioning

confidence: 96%

The Influence of Backward Sweep on Aerodynamic Performance of a 1.5-Stage Highly Loaded Axial Compressor

Huang¹,

Yang²,

Wang³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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As a degree of freedom in three-dimensional blade design of axial compressor, the sweep technique significantly affects aerodynamic performance of axial compressors. In this paper, the influence of backward sweep rotor configurations on aerodynamic performance of a 1.5-stage highly loaded axial compressor is studied by numerical simulation. The aim of this work is to improve understanding of flow mechanism of backward sweep on aerodynamic performance of a highly loaded axial compressor. A commercial CFD package is employed for flow simulations and analysis. The study found that backward sweep had little effect on peak efficiency of the 1.5-stage axial compressor. At the design rotational speed, compared with baseline, backward sweep rotor configurations reduce the blade loading near the leading edge but slightly increases the blade loading near the trailing edge in the hub region. As the degree of backward sweep increases, total pressure ratio and stall margin of the 1.5-stage axial compressor increase first and then decrease. Among different backward sweep rotor configurations, the 10% backward sweep rotor configuration has the highest stall margin, which is about 2.5% higher than that of baseline. This is due to the change of downstream stator incidence, which improves flow capacity near the hub region. At 60% rotational design speed, passage shock disappears. Backward sweep rotor configurations deteriorate stall margin of the compressor, but increase total pressure ratio and adiabatic efficiency when flow rate is lower than that at peak efficiency condition. Therefore, it's necessary to consider flow field structure of axial compressors in the design process and use the design freedom of sweep to improve the aerodynamic performance.

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Section: Introductionmentioning

confidence: 96%

The Influence of Backward Sweep on Aerodynamic Performance of a 1.5-Stage Highly Loaded Axial Compressor

Huang¹,

Yang²,

Wang³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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show abstract

“…Biollo and Benini (2009) found that a newly designed 3D swept and leaned rotor showed a higher efficiency which was due to a 3D modification of the shock wave structure. Sun et al (2019Sun et al ( , 2020 illustrated that the blade sweep had significant improvement effect on stall margin of a new-type low-reaction ultra-high-load transonic compressor rotor, which was due to the downstream migration of shock and the reduction of separation bubble on suction surface.…”

Section: Introductionmentioning

confidence: 99%

Influence of Blade Lean on Performance and Shock Wave/Tip Leakage Flow Interaction in a Transonic Compressor Rotor

Cao

Zhang

Liang

et al. 2022

JAFM

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Blade lean has been extensively used in axial compressor stators to control flow separations, but its influence mechanism on transonic compressor rotors remains to be revealed. The aim of this study is to numerically explore the influence of blade lean on the performance and shock wave/tip leakage flow interaction in a transonic compressor rotor. The effects of leaned pattern (positively lean and negatively lean), leaned angle and leaned height were studied. Results showed that, compared with baseline configuration, the efficiency and total pressure ratio of the entire constant rotating speed line of positively leaned rotor were both decreased. The absolute value of peak efficiency was reduced by as much as 4.34% at 20° lean angle, whereas the maximum reduction of peak total pressure ratio was 0.1 at 20° lean angle. The tip leakage flow streamlines of baseline transonic rotor can be divided into two parts, i.e., the primary vortex and secondary vortex which arises after the shock. Due to shock/tip leakage vortex interaction, the primary vortex enlarged and low-momentum region showed up after the shock; under near stall (NS) condition, tip leakage vortex breakdown occurred after interacting with shock. As positively leaned angle increased, the shock and the shock/tip leakage vortex interaction point moved upstream. In addition, the phenomenon of tip leakage vortex breakdown was enhanced. For negatively leaned rotors, as negatively leaned angle increased, the peak efficiency and total pressure ratio showed a tendency of first increasing and then decreasing. At 5° leaned angle, the peak efficiency was increased by 0.8% at most, and the maximum increment of total pressure ratio was 0.05 at 5° leaned angle. Besides, the loading of blade tip reduced and the loading moved toward trailing edge, resulting in the downstream movements of primary vortex, shock front and shock/tip leakage vortex interaction location. The results may help to improve the near tip flow field of transonic compressor rotor with leaned blade technology.

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“…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%

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

et al. 2022

Self Cite

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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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The impact of various forward sweep angles on the performance of an ultra-high-load low-reaction transonic compressor rotor

Cited by 23 publications

References 41 publications

The Influence of Backward Sweep on Aerodynamic Performance of a 1.5-Stage Highly Loaded Axial Compressor

The Influence of Backward Sweep on Aerodynamic Performance of a 1.5-Stage Highly Loaded Axial Compressor

Influence of Blade Lean on Performance and Shock Wave/Tip Leakage Flow Interaction in a Transonic Compressor Rotor

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

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