Numerical Investigations into the Origin of Tip Unsteadiness in a
                        Transonic Compressor

Guo, An; Lang, Jinhua; Chen, Z.; Wang, B.

doi:10.29252/jafm.11.04.28084

Cited by 5 publications

(2 citation statements)

References 18 publications

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“…Results showed that nonuniform tip clearance effectively reduced the leakage mass flow rate, leading to enhancement of overall performance of the transonic compressor. An et al (2018) analyzed the blade tip unsteadiness in a transonic compressor using NASA Rotor 35. The unsteady results indicated that the shock/tip leakage vortex interaction generated the tip leakage vortex breakdown and caused a U-type vortex, whose periodic migration along blade pressure surface led to blade loading variation and flow unsteadiness near blade tip region; the shock oscillation was observed as indication of flow unsteadiness.…”

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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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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“…The unsteady characteristics of clearance leakage flow may also cause compressor rotating stall, which will have a very adverse impact on compressor performance. At present, it is considered that the self-induced unsteadiness (Du et al 2010), vortex splitting and vortex breakdown (Liu et al 2016b;An et al 2018;Wu et al 2019), are the main reasons of stall initiation mechanism, and a lot of work has been done (Vo et al 2008).…”

Section: Introductionmentioning

confidence: 99%

Numerical Research on the Impact of Axial Position of Endwall Suction Slot on Tip Leakage Flow

Zhang

Liu

Rehman

et al. 2020

JAFM

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In order to reduce the adverse effect of the tip leakage flow of cantilever stator on compressor performance, the impact of the axial position of endwall streamwise suction slot on tip leakage flow was numerically studied. The study on the overall performance of the compressor and the details of the flow field near the stator end region with and without suction showed that all suction schemes could weaken the tip leakage flow intensity to a certain extent, and the flow control effect was gradually enhanced with the increase of the suction flow rate. In the case of small suction flow rate, for example, 0.5%, the short slot schemes can improve the overall efficiency of the compressor by about 0.5%, which is more advantageous than the long slot scheme, and the overall efficiency improvement of the latter is about 0.3%. The advantage of the long slot scheme in flow control is reflected in the case of large suction flow rate, that is, 1.0%, which may improve the overall efficiency of the compressor by about 0.96%. The axial position of suction slot has a significant influence on flow control effect of the tip leakage flow. Compared with the downstream suction, which only modified the flow field by reducing the blocking effect generated by tip flow vortex, the upstream suction could better control the tip leakage flow by restraining the development of the initial stage of the leakage vortex. Besides, the endwall suction scheme with a full chord length slot has the greatest impact on the passage vortex, its effect on modifying the flow field near the end zone was determined by the combinatorial action of the enhancement of the passage vortex and the attenuation of the leakage vortex.

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Vortex trajectory prediction and mode analysis of compressor stall with strong non-uniformity

Yang

et al. 2020

Aerospace Science and Technology

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Numerical Investigations into the Origin of Tip Unsteadiness in a Transonic Compressor

Cited by 5 publications

References 18 publications

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

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

Numerical Research on the Impact of Axial Position of Endwall Suction Slot on Tip Leakage Flow

Vortex trajectory prediction and mode analysis of compressor stall with strong non-uniformity

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