Abstract
As one of the core components of the rocket engine, the working conditions of the nozzle are very bad. Ensuring the nozzle works normally is an important prerequisite for the normal operation of the rocket engine. To ensure the safety of the solid rocket motor nozzle in use, the temperature distribution and thermal stress of the nozzle must be preliminarily analyzed. Therefore, the three-dimensional model of an L-shaped nozzle is established. The temperature field and stress field of the structure is numerically simulated by FLUENT and Static Structural. The influence of gas temperature and material thermal conductivity on temperature distribution and thermal stress of solid structures are analyzed. The results show that the throat has the highest temperature and maximum thermal stress. When the gas temperature is 2600K, the maximum temperature of the throat is 1400K, and the thermal stress is 158MPa. When the thermal conductivity of the insulation layer is 2.8 W/(m·K), the thermal stress on the throat is 170 MPa. The conclusion can provide an important reference for the thermal protection design of the nozzle.
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