关键词: 固体推进剂火箭发动机;喷管气流;三维流;模拟

Abstract: SIMPLE mothod is opplied to finish 3-D flow simulation in chamber of SPRM. The considered physical factors are as follows: finocyl grain, 3-D mass addition and incompressible turbulent flow, moving boundaries of propellant buring surfaces, heat radiation of gas, and so on. Equations are: 3-D continuity, momentum and energy equations, k-εequations of trubulent model, 3-D flux equations of heat radiation, and so on. In order to treat moving boundaries of burning surfaces, the tracking technique with marked grid is proposed.The studied results indicate: 1) The distribution of 3-D flow parameters in the passages of finocyl grain of SPRM can be obtained by coupled solution for aforementioned equations. 2) Using the tracking technique with marked grid, automatic judgement and treatment can be realized by computer, and the problem of the complex 3-D burning boundaries moving may be solved better. 3) The geometry match between fin-canals and main passage, and intense degree of propellant mass addition will intensely influence the parameter distribution of flow field, even returning flow and eddy will occur. This 3-D flow field will lead to 3-D erosion combustion. However, no unchanged flow rule may be followed. Therefore, for concrete geometry disign and burning rate, the particular calculation must be carried out, and the particular flow field can then be obtained. 4) In certain condition, near down stream of 3-D fin-canals mass-addition flow, the obvious circumferential eddy flow can be caused. When the fin-canals are designed at tail of combustion chamber, the 3-D flow condition will produce 3-D influence for flow, combustion and ablation of the back and throat of submerged nozzle.

Key words: Solid propellant rocket engine;Nozzle gas flow;Three dimensional flow;Simulation