Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor
The axial compressor is crucial for heavy-duty gas turbines, with its aerodynamic performance directly affecting efficiency. The current trend in the development of these compressors is to increase the stage load and efficiency, thereby achieving a higher pressure ratio with fewer stages. The aerody...
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MDPI AG
2024-12-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/12/1/25 |
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| author | Kunhang Li Bo Song Suyu Jiang Jiao Wang Xiaojun Fan Jingyin Li |
| author_facet | Kunhang Li Bo Song Suyu Jiang Jiao Wang Xiaojun Fan Jingyin Li |
| author_sort | Kunhang Li |
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| description | The axial compressor is crucial for heavy-duty gas turbines, with its aerodynamic performance directly affecting efficiency. The current trend in the development of these compressors is to increase the stage load and efficiency, thereby achieving a higher pressure ratio with fewer stages. The aerodynamic characteristics of a 1.5-stage axial compressor from a 300 MW F-class heavy gas turbine at three different rotation speeds (100%, 90%, and 80%) were studied. Specifically, the distribution of the inlet Mach number, shock wave structures, isentropic Mach number of blade surface, and blade surface separation flow characteristics under three typical working conditions, at the near stall (NS) point, maximum efficiency (ME) point, and near choke point (NC), were discussed. The results indicate that at 80% rotational speed, 70~100% spanwise of the compressor rotor blade is operated under the transonic zone. Meanwhile, at 100% rotational speed, almost all the spanwise of the compressor rotor blade is operated under the transonic zone. Furthermore, compared to the detached shock wave observed under the NS condition, the normal passage shock wave observed under the NC condition exhibits more significant changes in shock intensity and shock pattern. |
| format | Article |
| id | doaj-art-951564033f5e4b7984215292aeb33892 |
| institution | Kabale University |
| issn | 2226-4310 |
| language | English |
| publishDate | 2024-12-01 |
| publisher | MDPI AG |
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| series | Aerospace |
| spelling | doaj-art-951564033f5e4b7984215292aeb338922025-01-24T13:15:30ZengMDPI AGAerospace2226-43102024-12-011212510.3390/aerospace12010025Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage CompressorKunhang Li0Bo Song1Suyu Jiang2Jiao Wang3Xiaojun Fan4Jingyin Li5School of Energy and Power, Jiangsu University of Science and Technology, Zhenjiang 212100, ChinaSchool of Mechanical Engineering, Jiangsu University of Science and Technology, Zhenjiang 212100, ChinaSchool of Automation, Jiangsu University of Science and Technology, Zhenjiang 212100, ChinaSchool of Energy and Power, Jiangsu University of Science and Technology, Zhenjiang 212100, ChinaSchool of Energy and Power, Jiangsu University of Science and Technology, Zhenjiang 212100, ChinaDepartment of Fluid Machinery & Engineering, Xi’an Jiaotong University, Xi’an 710049, ChinaThe axial compressor is crucial for heavy-duty gas turbines, with its aerodynamic performance directly affecting efficiency. The current trend in the development of these compressors is to increase the stage load and efficiency, thereby achieving a higher pressure ratio with fewer stages. The aerodynamic characteristics of a 1.5-stage axial compressor from a 300 MW F-class heavy gas turbine at three different rotation speeds (100%, 90%, and 80%) were studied. Specifically, the distribution of the inlet Mach number, shock wave structures, isentropic Mach number of blade surface, and blade surface separation flow characteristics under three typical working conditions, at the near stall (NS) point, maximum efficiency (ME) point, and near choke point (NC), were discussed. The results indicate that at 80% rotational speed, 70~100% spanwise of the compressor rotor blade is operated under the transonic zone. Meanwhile, at 100% rotational speed, almost all the spanwise of the compressor rotor blade is operated under the transonic zone. Furthermore, compared to the detached shock wave observed under the NS condition, the normal passage shock wave observed under the NC condition exhibits more significant changes in shock intensity and shock pattern.https://www.mdpi.com/2226-4310/12/1/25F-class heavy-duty gas turbinetransonic compressorshock wave/boundary layer interactionflow analysis |
| spellingShingle | Kunhang Li Bo Song Suyu Jiang Jiao Wang Xiaojun Fan Jingyin Li Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor Aerospace F-class heavy-duty gas turbine transonic compressor shock wave/boundary layer interaction flow analysis |
| title | Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor |
| title_full | Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor |
| title_fullStr | Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor |
| title_full_unstemmed | Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor |
| title_short | Flow Analysis of a 300 MW F-Class Heavy-Duty Gas Turbine 1.5 Stage Compressor |
| title_sort | flow analysis of a 300 mw f class heavy duty gas turbine 1 5 stage compressor |
| topic | F-class heavy-duty gas turbine transonic compressor shock wave/boundary layer interaction flow analysis |
| url | https://www.mdpi.com/2226-4310/12/1/25 |
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