论文部分内容阅读
针对液体火箭发动机燃烧室内有隔板和无隔板的情况，用数值模拟的方法对发动机冷态全流场进行了计算，探讨了燃烧室内有隔板时边界条件的处理、计算区域的离散以及隔板对流场参数的影响等问题，用欧拉坐标系下的Navier－Stokes方程组描述气相控制方程，通过数值模拟成功地对燃烧室内有隔板和无隔板的流场进行了数值仿真，表明了对隔板体的数值处理方法的可行性。
Aiming at the condition that the liquid rocket engine combustion chamber has partition plate and no partition plate, the full flow field of the engine is calculated by numerical simulation. The boundary conditions of the combustion chamber are discussed, the calculation area is discretized and The influence of the diaphragm on the flow field parameters and so on. The Navier-Stokes equations in the Eulerian coordinate system are used to describe the gas-phase governing equations. Numerical simulations are performed to simulate the flow field with and without baffles in the combustion chamber , Indicating the feasibility of numerical methods for the separator body.