The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade
To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trailing-edge shock. The flow control mechanism an...
| Main Authors: | , , , , , , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-11-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/11/713 |
| _version_ | 1797466165094645760 |
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| author | Yinxin Zhu Zhenbing Luo Wenqiang Peng Qiang Liu Yan Zhou Wei Xie Pan Cheng Zhengxue Ma Xuzhen Xie |
| author_facet | Yinxin Zhu Zhenbing Luo Wenqiang Peng Qiang Liu Yan Zhou Wei Xie Pan Cheng Zhengxue Ma Xuzhen Xie |
| author_sort | Yinxin Zhu |
| collection | DOAJ |
| description | To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trailing-edge shock. The flow control mechanism and effects of parameters were analyzed by computational methods. The results show that the air jet formed an oblique shock wave in the cascade passage which decelerated and pressurized the airflow. The resulting expansion wave downstream of the jet slot weakened the strength of the trailing-edge shock. This could effectively change the normal shock into oblique shock and thus weaken the shock loss. Optimal control effect was achieved when the mass flow rate ratio of the jet to the passage airflow remained 0.35–1.11% and the distance from the jet slot to the shock foot of the trailing-edge shock was about five times the thickness of the boundary layer. The proposed method can reduce the total pressure loss of a supersonic cascade, with the maximum improvement effect reaching 7.29% compared to the no-control state. |
| first_indexed | 2024-03-09T18:31:57Z |
| format | Article |
| id | doaj.art-22e482f38ab74295bd9a9a5c8bd29d8d |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T18:31:57Z |
| publishDate | 2022-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-22e482f38ab74295bd9a9a5c8bd29d8d2023-11-24T07:24:22ZengMDPI AGAerospace2226-43102022-11-0191171310.3390/aerospace9110713The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor CascadeYinxin Zhu0Zhenbing Luo1Wenqiang Peng2Qiang Liu3Yan Zhou4Wei Xie5Pan Cheng6Zhengxue Ma7Xuzhen Xie8College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaCollege of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, ChinaTo effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trailing-edge shock. The flow control mechanism and effects of parameters were analyzed by computational methods. The results show that the air jet formed an oblique shock wave in the cascade passage which decelerated and pressurized the airflow. The resulting expansion wave downstream of the jet slot weakened the strength of the trailing-edge shock. This could effectively change the normal shock into oblique shock and thus weaken the shock loss. Optimal control effect was achieved when the mass flow rate ratio of the jet to the passage airflow remained 0.35–1.11% and the distance from the jet slot to the shock foot of the trailing-edge shock was about five times the thickness of the boundary layer. The proposed method can reduce the total pressure loss of a supersonic cascade, with the maximum improvement effect reaching 7.29% compared to the no-control state.https://www.mdpi.com/2226-4310/9/11/713supersonic compressor cascadetrailing-edge shockair jetshock controltotal pressure loss |
| spellingShingle | Yinxin Zhu Zhenbing Luo Wenqiang Peng Qiang Liu Yan Zhou Wei Xie Pan Cheng Zhengxue Ma Xuzhen Xie The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade Aerospace supersonic compressor cascade trailing-edge shock air jet shock control total pressure loss |
| title | The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade |
| title_full | The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade |
| title_fullStr | The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade |
| title_full_unstemmed | The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade |
| title_short | The Influence of Steady Air Jet on the Trailing-Edge Shock Loss in a Supersonic Compressor Cascade |
| title_sort | influence of steady air jet on the trailing edge shock loss in a supersonic compressor cascade |
| topic | supersonic compressor cascade trailing-edge shock air jet shock control total pressure loss |
| url | https://www.mdpi.com/2226-4310/9/11/713 |
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