Numerical Study on Coupled Heat Transfer and Structural Deformation of Compound Nozzle with Copper Infiltrated Tungsten-Lined Throat

Compound nozzles are widely used in the field of solid rocket engine (SRM). However, problems such as nozzle burn-out often occur in engineering, which is due to the different thermal expansion between components of different materials, and the combination interface is easy to fail. Based on this, the model of nozzle heat transfer and structural deformation is established and verified. Then, the heat transfer law and material deformation characteristics of the compound nozzle with copper infiltrated tungsten-lined throat are studied. The results show that the heat transfer of nozzle throat is the most intense, and there is obvious temperature jump and stress concentration at the junction of different components in addition to the heavy load on the throat lining, which may even cause the material to exceed the yield limit. Therefore, the combination and interaction between different components should be emphasized in the design of compound nozzle. A certain gap can be designed at the interface extrusion, which can effectively reduce the stress concentration value and optimize the uniformity of distribution.