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| Design and Preparation of Inlet Leading Edge with Corrugated Lattice Structure of C/SiC Composites |
| Received:September 26, 2019 Revised:November 18, 2019 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2020.01.012 |
| KeyWord:C/SiC composite inlet leading edge corrugated lattice structure |
| Author | Institution |
| CHEN Yan-fei |
Beijing Institute of Technology, Beijing , China |
| AI Shi-gang |
Beijing Institute of Technology, Beijing , China |
| HE Ru-jie |
Beijing Institute of Technology, Beijing , China |
| CHENG Su |
Harbin University of Science and Technology, Harbin , China |
| XU Bao-sheng |
Beijing Institute of Technology, Beijing , China |
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| Abstract: |
| The paper aims to complete lightweight design and preparation of C/SiC composite inlet leading edge. Firstly, the finite element model of the inlet leading edge with corrugated lattice sandwich structure was established based on the requirements on aerodynamic shape and structure of inlet. Then the heat flux distribution at the inlet leading edge was obtained by inversion according to the data of the H2K supersonic wind tunnel test in the German aviation center. On this basis, the boundary condition was loaded. Three heat transfer models, including thermal conduction, surface radiation and cavity radiation, were considered in the heat transfer process. Secondly, the transient heat transfer algorithm was used to solve the temperature field of the inlet leading edge in 100 seconds. To further reduce the highest temperature at the C/SiC composite inlet leading edge with corrugated lattice sandwich structure, different inlet leading edge tip radii were designed and optimized. Finally, the leading edge of C/SiC composite lattice structure inlet was prepared by the PIP method according to the optimized geometric parameters of the corrugated lattice inlet. When the radius of the inlet tip was less than 0.5 mm, the maximum temperature was higher than 1800 ℃, which exceeded the limit temperature of C/SiC composite material. When the radius of the inlet tip was greater than 1.0 mm, the maximum temperature was 1520 ℃, which was lower than the limit temperature of C/SiC composite material. When the inlet tip radius was greater than 2.0 mm, increasing the radius had no obvious effect on reducing the maximum temperature of the inlet leading edge. It took different time for the maximum temperature to reach the steady state under different inlet leading edge radii. When the radius was equal to 0.5 mm, it took about 30 s for the leading edge of the inlet to reach the steady state. As the radius of the leading edge tip increased, the time for the maximum temperature to reach the steady state increased. When the radius was 1.0 mm, it took about 60 s for the leading edge to reach the steady state. The maximum temperature of the inlet leading edge decreases significantly with the increase of the tip radius. When the radius is greater than 2.0 mm, increasing the radius has no significant effect on reducing the maximum temperature on the inlet leading edge. |
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