火箭发动机等离子体助燃的计算与分析

Calculation and Analysis on the Mechanism of Plasma Assisted Combustion for Rocket Engine

针对等离子助燃火箭发动机问题,依据俄罗斯A.Ktimov,V.Brovkin,A.Kuznetsov等提出的助燃模型,应用化学平衡计算程序CEA计算了辛烷C8H16在初温为298.15K和498.15K时的等离子体助燃效果。计算结果表明,火箭发动机等离子体助燃可增加化学反应过程中的活性中间体,提高化学反应速率,提高燃气的燃烧温度,火箭发动机助燃效果非常明显。

Focused on the problem in rocket engine plasma assisted combustion experiment, according to the assisted combustion model which put forward by the Russian A. Ktimov, V. Brovkin, A. Kuznetsov. The plasma assisted combustion effect of octane C8 H16 in 298. 15K and 498. 15K was calculated with the chemical equilibrium calculation program-CEA . The numerical results show that rocket engine plasma assisted combustion can increase active intermediate in chemical reaction, improve chemical reaction speed, rise burning temperature, and the effect of rocket engine assisted combustion is very obvious.