A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions
Since the use of the compressor of a ship gas turbine is unavoidable at a low-speed operation, the flow field characteristics and stall mechanism at off-design speeds are important aspects for compressor designers. In this study, the first 1.5 stages of an eight-stage compressor are numerically simu...
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| Format: | Article |
| Language: | English |
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MDPI AG
2020-05-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/13/11/2691 |
| _version_ | 1797566954770268160 |
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| author | Wenfeng Zhao Qun Zheng Bin Jiang Aqiang Lin |
| author_facet | Wenfeng Zhao Qun Zheng Bin Jiang Aqiang Lin |
| author_sort | Wenfeng Zhao |
| collection | DOAJ |
| description | Since the use of the compressor of a ship gas turbine is unavoidable at a low-speed operation, the flow field characteristics and stall mechanism at off-design speeds are important aspects for compressor designers. In this study, the first 1.5 stages of an eight-stage compressor are numerically simulated. The mechanism of compressor rotor instability at lower speeds is identified. The characteristic lines of compressors with various partial clearance are calculated at low speed (0.6 N). The flow field of the same outlet pressure (near stall point of the original compressor without clearance) is compared and analyzed. The results show that, at the near stall point, the suction surface separation and backflow occur in the main flow of the rotor top. It develops along the blade span and finally blocks the flow passage of the rotor, which results in the compressor stall. At the same time, the stall also occurs at the corner of the stator hub. In this paper, the characteristics of partial clearance in four different positions of the stator hub are analyzed. The near stall point and the working point are selected for the flow field analysis. It is concluded that the radial development of the stall vortex on the suction surface of the stator can be restrained by the partial clearance at the stator. In this paper, a passive control method by partial clearance is used in the real compressors, which is different from previous studies on cascades. The margin increases at low speeds. |
| first_indexed | 2024-03-10T19:33:47Z |
| format | Article |
| id | doaj.art-78d4aee91ab145dfb03316914bb9ab2d |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-03-10T19:33:47Z |
| publishDate | 2020-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-78d4aee91ab145dfb03316914bb9ab2d2023-11-20T01:52:19ZengMDPI AGEnergies1996-10732020-05-011311269110.3390/en13112691A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed ConditionsWenfeng Zhao0Qun Zheng1Bin Jiang2Aqiang Lin3College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, ChinaCollege of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, ChinaSince the use of the compressor of a ship gas turbine is unavoidable at a low-speed operation, the flow field characteristics and stall mechanism at off-design speeds are important aspects for compressor designers. In this study, the first 1.5 stages of an eight-stage compressor are numerically simulated. The mechanism of compressor rotor instability at lower speeds is identified. The characteristic lines of compressors with various partial clearance are calculated at low speed (0.6 N). The flow field of the same outlet pressure (near stall point of the original compressor without clearance) is compared and analyzed. The results show that, at the near stall point, the suction surface separation and backflow occur in the main flow of the rotor top. It develops along the blade span and finally blocks the flow passage of the rotor, which results in the compressor stall. At the same time, the stall also occurs at the corner of the stator hub. In this paper, the characteristics of partial clearance in four different positions of the stator hub are analyzed. The near stall point and the working point are selected for the flow field analysis. It is concluded that the radial development of the stall vortex on the suction surface of the stator can be restrained by the partial clearance at the stator. In this paper, a passive control method by partial clearance is used in the real compressors, which is different from previous studies on cascades. The margin increases at low speeds.https://www.mdpi.com/1996-1073/13/11/2691compressor marginoff-design speedpartial clearancehub corner stall |
| spellingShingle | Wenfeng Zhao Qun Zheng Bin Jiang Aqiang Lin A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions Energies compressor margin off-design speed partial clearance hub corner stall |
| title | A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions |
| title_full | A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions |
| title_fullStr | A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions |
| title_full_unstemmed | A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions |
| title_short | A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions |
| title_sort | passive control method of hub corner stall in a 1 5 stage axial compressor under low speed conditions |
| topic | compressor margin off-design speed partial clearance hub corner stall |
| url | https://www.mdpi.com/1996-1073/13/11/2691 |
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