采用欧拉-拉格朗日方法的针栓推力室 燃烧性能数值仿真

To address the inherent trade-off between efficiency and cooling in rocket engines with pintle injectors featuring peripheral liquid film cooling, a three-dimensional numerical simulation of combustion processes in the thruster chamber of an monomethylhydrazine/nitrogen tetroxide (MMH/NTO)pintle engine is conducted using the Euler-Lagrange approach coupled with a multi-step chemical reaction mechanism. The influence mechanisms of the peripheral cooling ratio and momentum ratio on thrust chamber performance are systematically analyzed. The results show that as the cooling ratio increases, the wall temperature significantly decreases. However, when the cooling ratio exceeds 27%, the propellant mixture ratio deviates from the optimal value, leading to a reduction in chamber pressure. Considering both wall temperature safety and thrust chamber performance, the optimal range for the peripheral cooling ratio is 20%—27%. The study also reveals that the momentum ratio significantly affects the flow field distribution and combustion efficiency of the thrust chamber, with an optimal momentum ratio range identified. The recommended value for this configuration is 2.10—3.06. This study provides critical insights for the design optimization of MMH/NTO bipropellant pintle injector thrust chambers, offers engineering guidance for achieving efficient and safe operation of pintle engines, and serves as a design reference for performance optimization of similar attitude and orbit control engines.