An Optimization Study of Circumferential Groove Casing Treatment in a High-Speed Axial Flow Compressor

In this paper, a numerical optimization study of single-groove casing treatment was conducted on a high-speed axial compressor. One of the aims is to find the optimal structure of a single groove that can improve compressor stability with minimal loss in efficiency. Another aim is to explore suitabl...

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Bibliographic Details
Published in:Aerospace 2024-07, Vol.11 (7), p.541
Main Authors: Liu, Wenhao, Chu, Wuli, Zhang, Haoguang, Wang, Hao
Format: Article
Language:English
Subjects:
axial flow compressor
Design
Design analysis
Design optimization
Design parameters
Efficiency
Genetic algorithms
groove
Grooves
High speed
Neural networks
Numerical analysis
Optimization
optimization design
Performance evaluation
R&D
Radial basis function
Research & development
stability
Stability analysis
Turbocompressors
Turbulence models
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Summary:In this paper, a numerical optimization study of single-groove casing treatment was conducted on a high-speed axial compressor. One of the aims is to find the optimal structure of a single groove that can improve compressor stability with minimal loss in efficiency. Another aim is to explore suitable parameters for rapidly evaluating the compressor stall margin. A design optimization platform has been constructed in this paper, which utilizes NSGA-II and a Radial Basis Function (RBF) neural net model to carry out the optimization. The stall margin of the compressor with A single groove was accurately determined by calculating its entire overall performance line. A Pareto front is obtained through optimization, and the optimal design can be selected from the Pareto front. By considering both stall margin and efficiency loss, one of the optimal designs was found to achieve a 7.49% improvement in stall margin with a 0.24% improvement in peak efficiency. Based on the database, the effect of design parameters of a single groove on compressor stability and performance is analyzed. A series of evaluation parameters of stall margin were compared to their degree of correlation with the real stall margin calculated by the entire overall performance line. As a result, tip blockage and momentum ratio can be used as efficient parameters for quickly evaluating the compressor stall margin without the need to calculate the entire performance curve of the compressor.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace11070541