Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Hu, Shuzhen; Lu, Xingen; Zhang, Hongwu; Zhu, Jihong; Xu, Qian

doi:10.1007/s11630-010-0014-8

Cited by 19 publications

(7 citation statements)

References 9 publications

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“…Hu et al. 24 exerted NAEP on hub of a compressor rotor and it could mitigate secondary flow. Iliopoulou et al.…”

Section: Introductionmentioning

confidence: 99%

“…Chu et al 23 designed a NAEP based on endwall velocity modification method, which reduced the endwall loss in an axial compressor. Hu et al 24 exerted NAEP on hub of a compressor rotor and it could mitigate secondary flow. Iliopoulou et al 25 optimized the profiled hub endwall of a compressor rotor, which showed that the performance improvement was due to the influence of shock rather than the variation of secondary flows.…”

Section: Introductionmentioning

confidence: 99%

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Flow physics of highly loaded tandem compressor cascade with non-axisymmetric endwall profiling

Cao

Guo

Song

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Tandem configuration is an effective methodology to reduce flow separation on compressor blade suction surface and to improve blade loading. However, in modern highly loaded cases, corner separation remains as its single blade counterpart. In this study, non-axisymmetric endwall profiling (NAEP) was utilized in a highly loaded tandem cascade (diffusion factor D = 0.69), aiming at reducing its severe corner separation and revealing the unique flow mechanism while NAEP is utilized in tandem cascade. NAEP was designed in both forward (F) blade and rare (R) blade separately, and was investigated numerically in tandem environment. Results show that, NAEP in F blade passage can effectively eliminate the corner separation and reduce loss generation, whereas NAEP in R blade passage has no positive effect on corner separation and even promotes loss production. The optimal NAEP approximately removes the corner separation completely, with loss coefficient reducing by as much as 37.8%. The optimal NAEP for the tandem cascade features optimal axial location at the origin of corner separation. There is an optimal NAEP height (0.02 of blade height), under which NAEP can achieve pretty good control effect while the peak of NAEP varies in a large axial location range. In the tandem configuration, it is found that NAEP transfers blade loading from R blade to F blade; the static pressure increases significantly for the entire cascade, but the static pressure distribution of F blade does not exhibit as the design intent of NAEP. In addition, it is interesting to find that the flow turning near endwall reduces after endwall profiling, which is unique in tandem cascade and is contrast to the view on conventional configuration. On the contrary, NAEP in R blade has no influence on the corner separation of the tandem cascade; due to the decrement of cross-passage pressure gradient for R blade, the flow overturning near endwall reduces.

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“…Hu et al. 24 exerted NAEP on hub of a compressor rotor and it could mitigate secondary flow. Iliopoulou et al.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Flow physics of highly loaded tandem compressor cascade with non-axisymmetric endwall profiling

Cao

Guo

Song

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Compared with active flow control methods, passive flow control methods can be achieved easily by device with the relatively simple geometry and does not require any external energy supply. Many passive flow methods have been investigated in axial compressors, including three-dimensional blade shaping, 10 endwall profiling, 11,12 and vortex generators. 13 These passive flow control methods can restrain corner separations and display the huge potential to improve the aerodynamic performance of highly loaded axial compressors.…”

Section: Introductionmentioning

confidence: 99%

Passive flow control of the corner separation in an annular compressor cascade with a micro-blade

Wang

2018

Proceedings of the Institution of Mechanical Engineers, Part A:

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Corner separation contributes greatly to the loss and the passage blockage in a compressor stage. In order to mitigate the corner separation and improve the aerodynamic performance of compressors, a novel passive flow control method, an off-surface micro-blade installed upstream of the separation onset location, was proposed. A numerical investigation has was performed in an annular compressor cascade to assess the control effectiveness of the micro-blade. The results show that the location of the micro-blade affects the control effect significantly. The application of the well-designed micro-blade enhances the diffusion capacity considerably under the inflow incidence from −2° to +10°, accompanied by a slight loss reduction at some particular incidences. Detailed analysis of the predicted flow field was carried out to understand the underlying mechanism. It indicates that a “jet” forms upstream of the separation onset location with the application of the micro-blade. The formation of the jet reduces the thickness of boundary layer on the suction surface and builds a “jet barrier” near the endwall to hinder the accumulation of the low momentum fluid. The influence of the incidence was also investigated. It is concluded that the incidence increase has both positive and negative influences on the control effect of the micro-blade. As a result, the performance of the micro-blade is sensitive to the variation of inlet incidence.

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“…The other method is based on previous experience, which is well developed in turbines but seldom published in compressors except for Hu's paper. 3 The perturbation of the end wall geometry in this approach is defined using some smooth function, which is commonly controlled by very few parameters. The values of parameters are typically given by previous experience and adjusted by trial-and-error to find a satisfactory result.…”

Section: Introductionmentioning

confidence: 99%

“…An optimization procedure is then performed via a certain algorithm to get the optimum result. The other method is based on previous experience, which is well developed in turbines but seldom published in compressors except for Hu's paper [3] . The perturbation of the end wall geometry in this approach is defined using some smooth function, which is commonly controlled by very few parameters.…”

mentioning

confidence: 99%

Effective end wall profiling rules for a highly loaded compressor cascade

Chu

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper presents a numerical study of a linear compressor cascade to investigate the effective end wall profiling rules for highly-loaded axial compressors. The first step in the research applies a correlation analysis for the different flow field parameters by a data mining over 600 profiling samples to quantify how variations of loss, secondary flow and passage vortex interact with each other under the influence of a profiled end wall. The result identifies the dominant role of corner separation for control of total pressure loss, providing a principle that only in the flow field with serious corner separation does the does the profiled end wall change total pressure loss, secondary flow and passage vortex in the same direction. Then in the second step, a multi-objective optimization of a profiled end wall is performed to reduce loss at design point and near stall point. The development of effective end wall profiling rules is based on the manner of secondary flow control rather than the geometry features of the end wall. Using the optimum end wall cases from the Pareto front, a quantitative tool for analyzing secondary flow control is employed. The driving force induced by a profiled end wall on different regions of end wall flow are subjected to a detailed analysis and identified for their positive/negative influences in relieving corner separation, from which the effective profiling rules are further confirmed. It is found that the profiling rules on a cascade show distinct differences at design point and near stall point, thus loss control of different operating points is generally independent.

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Numerical investigation of a high-subsonic axial-flow compressor rotor with non-axisymmetric hub endwall

Cited by 19 publications

References 9 publications

Flow physics of highly loaded tandem compressor cascade with non-axisymmetric endwall profiling

Flow physics of highly loaded tandem compressor cascade with non-axisymmetric endwall profiling

Passive flow control of the corner separation in an annular compressor cascade with a micro-blade

Effective end wall profiling rules for a highly loaded compressor cascade

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