旋转爆震发动机燃烧室与喷射器的准二维模拟
Quasi-Two-Dimensional Simulation of a Rotating Detonation Engine Combustor and Injector
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中文总结 AI 辅助
本文采用准二维方法模拟环形旋转爆震发动机，研究了面积比为4时爆震与喷射器的相互作用，发现喷射器扩张段激波导致总压损失无法弥补，发动机出口总压低于稳压室。
中文摘要 AI 辅助
开展了化学计量比氢氧环形旋转爆震发动机的数值模拟研究，提出了一种通用、适定且易实现的准二维方法，用于模拟旋转爆震发动机喷射器与燃烧室内的面积变化。针对燃烧室与喷射器喉道面积比为4的情况，研究了爆震与喷射器的相互作用：由于燃烧室内爆震产生的高背压，在喷射器的扩张段形成了一道激波；对流线和粒子轨迹进行的 Favre 平均稳态分析表明，该激波会导致总压产生不可恢复的损失，而燃烧室内的总压增益不足以弥补这一损失，最终流体离开发动机时的总压低于其在稳压室中的总压。
英文摘要
A numerical simulation of an annular rotating detonation engine with stoichiometric hydrogen-oxygen is performed. A generic, well posed, and easily implemented approach using a quasi-two-dimensional method to model the area variations through the rotating detonation engine's injector and combustor is presented. The detonation--injector interaction is studied for the case with a ratio of four between the combustor and injector's throat areas. A shock wave is formed in the divergent portion of the injector due the high back pressure created by the detonation in the combustor. A Favre-averaged steady-state analysis of stream lines and particle paths reveals that the shock causes an irrecoverable loss of stagnation pressure. Stagnation pressure gain in the combustor is insufficient to make up for the loss and the flow leaves the engine with lower stagnation pressure than in the plenum.
发表机构
- National Research Council（国家研究委员会）
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