An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp
Shockwaves induce considerable flow separation loss; it is essential to reduce this using the flow control method. In this manuscript, a method for suppressing flow separation in turbomachinery through a constant adverse-pressure gradient was investigated. The first-passage shock was split into a co...
Saved in:
| Main Authors: | , , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2025-05-01
|
| Series: | Applied Sciences |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2076-3417/15/10/5664 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1849327741763059712 |
|---|---|
| author | Yongzhen Liu Zhen Fan Weiwei Cui Qiang Zhou Jianzhong Xu |
| author_facet | Yongzhen Liu Zhen Fan Weiwei Cui Qiang Zhou Jianzhong Xu |
| author_sort | Yongzhen Liu |
| collection | DOAJ |
| description | Shockwaves induce considerable flow separation loss; it is essential to reduce this using the flow control method. In this manuscript, a method for suppressing flow separation in turbomachinery through a constant adverse-pressure gradient was investigated. The first-passage shock was split into a compression wave system of the vane suction surface. The aim of this was to reduce loss from shockwave/boundary layer interactions (SWBLIs). This method promotes the performance parameters of the supersonic compressor cascade. The investigation targets were a baseline cascade and the improved system. Both cascades were numerically studied with the aid of the Reynolds-averaged Navier–Stokes (RANS) method. The simulation results of the baseline cascade were also validated through experimentation, and a further physical flow analysis of the two cascades was conducted. The results show that the first-passage shockwave was a foot above the initial suction surface, with a weaker incident shock along with a clustering of the compression wave corresponding to the modified cascade. It was also concluded that the first-passage shockwave foot of the baseline cascade was replaced with a weak incident shock, and a series of compression waves emanated from the adopted negative-curvature profile. The shock-induced boundary layer separation bubble disappeared, and much smaller boundary layer shape factors over the SWBLI region were obtained for the improved cascade compared to the baseline cascade. This improvement led to a high level of stability in the boundary layer state. Sensitivity analyses were performed through different simulations on both cascades, unveiling that the loss in total pressure was lower in the case of the updated cascade as compared to the baseline. |
| format | Article |
| id | doaj-art-8299f79f4afc4e6b904f986c048ab053 |
| institution | Kabale University |
| issn | 2076-3417 |
| language | English |
| publishDate | 2025-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Applied Sciences |
| spelling | doaj-art-8299f79f4afc4e6b904f986c048ab0532025-08-20T03:47:48ZengMDPI AGApplied Sciences2076-34172025-05-011510566410.3390/app15105664An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature RampYongzhen Liu0Zhen Fan1Weiwei Cui2Qiang Zhou3Jianzhong Xu4School of Mechanical Engineering, Chaohu University, Hefei 238024, ChinaSchool of Aeronautics and Astronautics, Beihang University, Beijing 100191, ChinaCollege of Energy Storage Technology, Shandong University of Science and Technology, Qingdao 256601, ChinaInstitute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, ChinaInstitute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, ChinaShockwaves induce considerable flow separation loss; it is essential to reduce this using the flow control method. In this manuscript, a method for suppressing flow separation in turbomachinery through a constant adverse-pressure gradient was investigated. The first-passage shock was split into a compression wave system of the vane suction surface. The aim of this was to reduce loss from shockwave/boundary layer interactions (SWBLIs). This method promotes the performance parameters of the supersonic compressor cascade. The investigation targets were a baseline cascade and the improved system. Both cascades were numerically studied with the aid of the Reynolds-averaged Navier–Stokes (RANS) method. The simulation results of the baseline cascade were also validated through experimentation, and a further physical flow analysis of the two cascades was conducted. The results show that the first-passage shockwave was a foot above the initial suction surface, with a weaker incident shock along with a clustering of the compression wave corresponding to the modified cascade. It was also concluded that the first-passage shockwave foot of the baseline cascade was replaced with a weak incident shock, and a series of compression waves emanated from the adopted negative-curvature profile. The shock-induced boundary layer separation bubble disappeared, and much smaller boundary layer shape factors over the SWBLI region were obtained for the improved cascade compared to the baseline cascade. This improvement led to a high level of stability in the boundary layer state. Sensitivity analyses were performed through different simulations on both cascades, unveiling that the loss in total pressure was lower in the case of the updated cascade as compared to the baseline.https://www.mdpi.com/2076-3417/15/10/5664negative-curvature profileconstant adverse-pressure gradientshockwave/boundary layer interactionsupersonic compressor cascade |
| spellingShingle | Yongzhen Liu Zhen Fan Weiwei Cui Qiang Zhou Jianzhong Xu An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp Applied Sciences negative-curvature profile constant adverse-pressure gradient shockwave/boundary layer interaction supersonic compressor cascade |
| title | An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp |
| title_full | An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp |
| title_fullStr | An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp |
| title_full_unstemmed | An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp |
| title_short | An Investigation of the Promotion of the Aerodynamic Performance of a Supersonic Compressor Cascade Using a Local Negative-Curvature Ramp |
| title_sort | investigation of the promotion of the aerodynamic performance of a supersonic compressor cascade using a local negative curvature ramp |
| topic | negative-curvature profile constant adverse-pressure gradient shockwave/boundary layer interaction supersonic compressor cascade |
| url | https://www.mdpi.com/2076-3417/15/10/5664 |
| work_keys_str_mv | AT yongzhenliu aninvestigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT zhenfan aninvestigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT weiweicui aninvestigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT qiangzhou aninvestigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT jianzhongxu aninvestigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT yongzhenliu investigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT zhenfan investigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT weiweicui investigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT qiangzhou investigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp AT jianzhongxu investigationofthepromotionoftheaerodynamicperformanceofasupersoniccompressorcascadeusingalocalnegativecurvatureramp |