航天推进技术研究院主办
[1]刘占一,张魏静,周康,等.基于增材制造技术的液氧/甲烷燃烧室身部设计及热试分析[J].火箭推进,2023,49(04):82-89.
LIU Zhanyi,ZHANG Weijing,ZHOU Kang,et al.Design and hot-test analysis on LO2/methane combustion chamber body based on additive manufacturing technology[J].Journal of Rocket Propulsion,2023,49(04):82-89.
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LIU Zhanyi,ZHANG Weijing,ZHOU Kang,et al.Design and hot-test analysis on LO2/methane combustion chamber body based on additive manufacturing technology[J].Journal of Rocket Propulsion,2023,49(04):82-89.
基于增材制造技术的液氧/甲烷燃烧室身部设计及热试分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年04期
页码:
82-89
栏目:
目次
出版日期:
2023-08-25
- Title:
- Design and hot-test analysis on LO2/methane combustion chamber body based on additive manufacturing technology
- 文章编号:
- 1672-9374(2023)04-0082-08
- 分类号:
- V434.2
- 文献标志码:
- A
- 摘要:
- 为了更深入地了解增材制造技术应用于液体火箭发动机燃烧室身部研制的可行性,开展了基于增材制造技术的燃烧室身部设计、加工以及热试。通过采取全身螺旋槽道设计、减薄内壁厚度等措施实现了以高温合金作为燃烧室内壁的内外壁一体化身部方案设计; 采用中空加肋法兰设计,在实现燃烧室模块化设计的同时保证了法兰密封效果; 采用激光选区熔化技术(SLM)进行了产品加工,并进行了全方位产品检测; 产品经过了热试试验验证,试后结构完好。
- Abstract:
- In order to further understand the feasibility of applying the additive manufacturing technology to the development of combustion chamber body in liquid rocket engine, the design, processing and hot-test of combustion chamber body have been carried out based on additive manufacturing technology. To realize theintegration scheme of internal and external walls with superalloy as the internal wall of combustion chamber, some measures such as spiral channel design, reducing the thickness of internal wall have been adopted. In addition, a hollow flange with ribs has been taken to ensure the sealing effect of the flange while achieving the modular design of the combustion chamber. Selective Laser Melting(SLM)technology was utilized to process the product, and the detection on all aspects of the product was carried out. The product has been verified by the hot-test, and the structure is still in good condition after the test.
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备注/Memo
收稿日期:2022-12-14; 修回日期:2023-01-06
基金项目:国家自然科学基金项目(52005385)
作者简介:刘占一(1985—),男,博士,研究员,研究方向为液体火箭发动机。
更新日期/Last Update:
1900-01-01