Toward Optimum Configuration of Circumferential Groove Casing Treatment in Transonic Compressor Rotors

Hah, Chunill

doi:10.1115/ajk2011-05020

Cited by 7 publications

(2 citation statements)

References 15 publications

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“…11 Among the various casing treatments, the circumferential groove casing treatment is simple in structure and has less negative effect on the efficiency of compressors. 12,13 Many investigations have been carried out to reveal the flow mechanisms for stall margin improvement by circumferential groove casing treatments. Prince et al 14 identified several effects of circumferential grooves on compressors.…”

Section: Introductionmentioning

confidence: 99%

Investigation of groove casing treatment in a transonic compressor at different speeds with control volume method

Zhou

Zhao

Xiang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article uses a control volume method to analyze the circumferential groove casing treatment in a transonic compressor. To analyze the axial momentum transport through the tip gap, the control volume near the casing is divided into two parts: the control volumes inside and outside the tip gap. Besides, the association between the forces acting on the control volume and flow structures is studied by analyzing the distributions of axial momentum flux and axial shear stress. With this method, the flow mechanisms of stall margin improvement due to casing grooves in Rotor 35 are quantitatively analyzed. The analysis is conducted at 100% and 60% design speed with supersonic and subsonic tip speed, respectively. At design speed, the casing grooves decrease the axial shear force and the axial force due to the transport of axial momentum induced by the tip leakage flow. Meanwhile, the bleeding and injecting effect of grooves contribute much to the axial force due to the transport of axial momentum. Based on the axial distribution of the axial forces, the contribution of each groove to the stall margin improvement is assessed. And the grooves that play a major role in stall margin improvement are ascertained. At 60% design speed, because the blade loading is reduced, the axial momentum transport caused by the grooves cannot suppress the boundary layer separation effectively. Consequently, the stall margin of the compressor is not significantly improved by the casing grooves.

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Section: Introductionmentioning

confidence: 99%

Investigation of groove casing treatment in a transonic compressor at different speeds with control volume method

Zhou

Zhao

Xiang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…[4][5][6][7] Among the widely investigated casing treatment geometries, circumferential groove casing treatment is simple in structure, and can extend the stall margin with relatively small efficiency penalty. [8][9][10] However, the fundamental working mechanisms of circumferential casing grooves on the performance of compressors are still not well understood. The universal design criterion of circumferential casing grooves has not been established yet.…”

Section: Introductionmentioning

confidence: 99%

Multi-objective optimization of groove casing treatment in a transonic compressor

Zhao

Zhou

Xiang

2014

Proceedings of the Institution of Mechanical Engineers, Part A:

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The paper presents a multi-objective optimization of circumferential casing grooves geometries for the NASA Rotor 37 transonic compressor. The depth normalized by the tip clearance and the width normalized by the tip chord are selected as the design variables. The stall margin and peak efficiency are used as the objective functions. The Latin Hypercube Sampling technique was used to select the sample points in the design space. Based on the numerical results of the sample points, the radial basis function network model of the artificial neural network was constructed. The NSGA-II multi-objective evolutionary algorithm is then employed to search for Pareto-optimal solutions. The leave-one-out cross validation method was also used to evaluate the precision of the radial basis function network model. The results of the optimization show the present method can be effectively used for the design of circumferential casing grooves to take account of the stall margin and efficiency. From the Pareto-optimal solutions, two groove configurations are selected and the internal flow fields are compared with the smooth casing. The effect mechanism of the circumferential casing grooves on the performance of the transonic compressor is discussed by the analysis of the flow in the blade tip region.

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Suppressing tip-leakage vortex cavitation by overhanging grooves

et al. 2020

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Toward Optimum Configuration of Circumferential Groove Casing Treatment in Transonic Compressor Rotors

Cited by 7 publications

References 15 publications

Investigation of groove casing treatment in a transonic compressor at different speeds with control volume method

Investigation of groove casing treatment in a transonic compressor at different speeds with control volume method

Multi-objective optimization of groove casing treatment in a transonic compressor

Suppressing tip-leakage vortex cavitation by overhanging grooves

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