Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane
When an aero engine operates under icing conditions, the windward surfaces of its intake components, such as the zero-stage guide vane, are prone to icing, posing a potential flight safety hazard. In this study, we establish a computational model for hot-air anti-icing of a full-scale zero-stage gui...
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| Format: | Article |
| Language: | English |
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AIP Publishing LLC
2025-05-01
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| Series: | AIP Advances |
| Online Access: | http://dx.doi.org/10.1063/5.0259853 |
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| author | Lifeng Gong Weiliang Zheng Yaping Hu Shuliang Jing Haoyu Yuan Chen Wu |
| author_facet | Lifeng Gong Weiliang Zheng Yaping Hu Shuliang Jing Haoyu Yuan Chen Wu |
| author_sort | Lifeng Gong |
| collection | DOAJ |
| description | When an aero engine operates under icing conditions, the windward surfaces of its intake components, such as the zero-stage guide vane, are prone to icing, posing a potential flight safety hazard. In this study, we establish a computational model for hot-air anti-icing of a full-scale zero-stage guide vane based on CFX and FENSAP-ICE software and conduct a numerical study on three-dimensional coupled heat transfer for anti-icing and the improvement of anti-icing structures. The computational results demonstrate that under anti-icing conditions, the lowest temperature is observed at the root of the leading edge of the guide vane. Icing predominantly occurs in the water droplets impinging on the area downstream of the stagnation point on the guide vane and in proximity to the root of the suction surface, with ice reaching a maximum thickness of ∼7.21 mm. When the hot-air inlet is shifted toward the leading edge and a deflector is introduced, the anti-icing surface temperature is elevated, the icing area is slightly reduced, and the total ice mass is decreased by ∼14.7% compared to the original model. Furthermore, after designing opening holes near the root of the suction surface to allow the hot air to flow out, the temperature on the guide vane’s surface is significantly increased, and the temperature gradient is reduced. The icing area is markedly decreased, with the maximum ice thickness reduced by ∼3.3 mm, and the total ice mass further decreased by about 33.1%. |
| format | Article |
| id | doaj-art-2092a04d72304a44b0157d2d43b5c0f8 |
| institution | DOAJ |
| issn | 2158-3226 |
| language | English |
| publishDate | 2025-05-01 |
| publisher | AIP Publishing LLC |
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| series | AIP Advances |
| spelling | doaj-art-2092a04d72304a44b0157d2d43b5c0f82025-08-20T03:19:43ZengAIP Publishing LLCAIP Advances2158-32262025-05-01155055020055020-1310.1063/5.0259853Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vaneLifeng Gong0Weiliang Zheng1Yaping Hu2Shuliang Jing3Haoyu Yuan4Chen Wu5AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, People’s Republic of ChinaNanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210000, People’s Republic of ChinaNanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210000, People’s Republic of ChinaNanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210000, People’s Republic of ChinaNanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210000, People’s Republic of ChinaNanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu 210000, People’s Republic of ChinaWhen an aero engine operates under icing conditions, the windward surfaces of its intake components, such as the zero-stage guide vane, are prone to icing, posing a potential flight safety hazard. In this study, we establish a computational model for hot-air anti-icing of a full-scale zero-stage guide vane based on CFX and FENSAP-ICE software and conduct a numerical study on three-dimensional coupled heat transfer for anti-icing and the improvement of anti-icing structures. The computational results demonstrate that under anti-icing conditions, the lowest temperature is observed at the root of the leading edge of the guide vane. Icing predominantly occurs in the water droplets impinging on the area downstream of the stagnation point on the guide vane and in proximity to the root of the suction surface, with ice reaching a maximum thickness of ∼7.21 mm. When the hot-air inlet is shifted toward the leading edge and a deflector is introduced, the anti-icing surface temperature is elevated, the icing area is slightly reduced, and the total ice mass is decreased by ∼14.7% compared to the original model. Furthermore, after designing opening holes near the root of the suction surface to allow the hot air to flow out, the temperature on the guide vane’s surface is significantly increased, and the temperature gradient is reduced. The icing area is markedly decreased, with the maximum ice thickness reduced by ∼3.3 mm, and the total ice mass further decreased by about 33.1%.http://dx.doi.org/10.1063/5.0259853 |
| spellingShingle | Lifeng Gong Weiliang Zheng Yaping Hu Shuliang Jing Haoyu Yuan Chen Wu Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane AIP Advances |
| title | Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane |
| title_full | Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane |
| title_fullStr | Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane |
| title_full_unstemmed | Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane |
| title_short | Hot-air anti-icing characteristics and anti-icing structures of a zero-stage guide vane |
| title_sort | hot air anti icing characteristics and anti icing structures of a zero stage guide vane |
| url | http://dx.doi.org/10.1063/5.0259853 |
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