一种双环多模推力室
By designing a dual-ring multi-mode thrust chamber, combining conventional combustion in the inner ring and detonation combustion in the outer ring, the problems of combustion instability and low specific impulse of liquid rocket engines under low thrust conditions were solved, achieving improved combustion stability and specific impulse, possessing the ability to adjust thrust in depth, and improving the performance and efficiency of rocket engines.
CN117028073BActive Publication Date: 2026-07-17QINGHANG AEROSPACE (BEIJING) TECH CO LTD
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- QINGHANG AEROSPACE (BEIJING) TECH CO LTD
- Filing Date
- 2023-09-04
- Publication Date
- 2026-07-17
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Figure CN117028073B_ABST
Abstract
本申请提供了一种双环多模推力室，属于火箭发动机技术领域，包括第一壳体、第二壳体和第三壳体，第一壳体形成的腔体为内环推力室，内环推力室头部为燃烧室，尾部设有第一喷嘴；第一壳体和第二壳体之间形成冷却通道，位于尾部一侧的冷却通道设有燃料入口；第二壳体和第三壳体之间形成的腔体为外环爆震推力室，外环爆震推力室头部与内环推力室头部位于同一侧，头部为爆震燃烧区，尾部设有第二喷嘴；内环推力室头部设有燃料喷嘴、氧化剂喷嘴和第一点火组件，外环爆震推力室头部设有爆震燃料喷嘴、爆震氧化剂喷嘴和第二点火组件，燃料喷嘴和爆震燃料喷嘴分别与冷却通道相通。本申请的处理方案提高了燃烧稳定性和比冲。
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