火箭推力室蝶形薄膜冷却孔气动性能的多目标优化

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2024-07-08 DOI:10.1515/tjj-2024-0040

Ningning Yu, Zhongwei Wang, Yuming Lu, Weicheng Xu, Yiming Shan, Hai Zhang

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引用次数: 0

摘要

摘要本研究使用多岛遗传算法（MIGA）和三维计算流体动力学（CFD）软件对火箭上级发动机推力室的蝶形薄膜冷却孔进行优化。其目标是满足高海拔地区的热保护和推力要求，而不会发生复燃。为便于在全球范围内进行全方位搜索，优化设计中的孔仍保持设定尺寸。喷嘴出口处的薄膜连续性和稳定性在很大程度上受到孔结构的影响。根据回归研究，进口角和发散角对推力影响不大，但唇高（de）和出口宽度（β）对冷气体喷射影响很大，而冷气体喷射会影响冷却和推力。优化结果通过减少超音速气流之间的干扰和提高薄膜稳定性，使监测部分的平均壁温降低了 20.49 K，推力增加了 52.8 N。

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Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber

Abstract This study uses Multi-Island Genetic Algorithm (MIGA) and three-dimensional Computational Fluid Dynamics (CFD) software to optimize butterfly-shaped film cooling holes in the upper-stage rocket engine thrust chamber. The goal is to meet thermal protection and thrust requirements at high altitudes without re-ignition. To facilitate an all-encompassing worldwide search, the holes in the optimized design remain at set dimensions. Film continuity and stability at the nozzle outlet are greatly impacted by the hole structure. Inlet and divergence angles have little effect on thrust, according to regression research, but lip height (de) and outlet width (β) have a big impact on cold gas ejection, which affects cooling and thrust. Optimized results lead to a 20.49 K decrease in the monitoring section’s average wall temperature and a 52.8 N boost in thrust by reducing interference between supersonic airflow and extending film stability.

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.