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Zhu Cheng, Yu Xiaobing, Chen Si, et al. Cooling design and wall temperature analysis of swirl-cup combustor head[J]. Journal of Aerospace Power, 2026, 41（X）：20250258 doi: 10.13224/j.cnki.jasp.20250258
Citation: Zhu Cheng, Yu Xiaobing, Chen Si, et al. Cooling design and wall temperature analysis of swirl-cup combustor head[J]. Journal of Aerospace Power, 2026, 41（X）：20250258 doi: 10.13224/j.cnki.jasp.20250258
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Cooling design and wall temperature analysis of swirl-cup combustor head

doi: 10.13224/j.cnki.jasp.20250258

  • Guiyang Engine Design Research Institute，Aero Engine Corporation of China，Guiyang 550081

  • Received Date: 2025-05-30
    Available Online: 2026-08-24
    Abstract

  • For the cooling design for the complex and compact structure of the swirl-cup combustor head, three cooling design schemes were proposed. Numerical simulations were conducted to calculate the flow field, temperature field, and wall temperature distribution for different schemes. The results showed that, without cooling, corner vortices near the wall in the head led to the formation of high-temperature stagnation vortices by drawing in burning gases, causing a wide range of high temperatures on the surface of the flame tube head with a maximum wall temperature of 1178 K. The head cooling designs involved introducing cooling air between the inner and outer fairings to form a protective air film and disperse the near-wall corner vortices, effectively reducing the head wall temperature to varying degrees. The use of inclined multi-hole in the thermal shield was limited by geometrical dimensions, resulting in uneven development and poor adhesion of the air film, and leading to ineffective cooling. By designing a guide ring structure, it is possible to control the diversion of cooling in a compact space and to adjust the flow path design to increase the cooling airflow rate and velocity, forming a uniform air film adhering to the wall at the thermal shield and the swirler housing, with a wall temperature below 870 K. Under high temperature and high pressure conditions, the optimized scheme was validated through combustor component tests. The results demonstrated that the combustor head wall temperature did not exceed the material's long-term permissible operating temperature, proving that the head cooling design could effectively control the wall temperature.

     

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