Abstract
This study presents a numerical investigation of the thermophysical and mechanical characteristics of a liquid rocket engine combustion chamber with nozzle assembly with regenerative cooling.The simulations were performed using Ansys Discovery, Ansys Steady-State Thermal, and Ansys Mechanical software packages.Various combinations of structural materials (copper, aluminum, and steel) were analyzed, along with the influence of the convective heat transfer coefficient on the thermal state of the structure.It was found that increasing the coolant heat transfer coefficient up to 1.2 W/mm²•K significantly reduces the temperature of the inner layer, thereby ensuring acceptable operating conditions.Based on the results obtained, a combustion chamber with nozzle assembly design was developed featuring an inner layer made of a CuCrZr alloy and an outer shell made of 30KhGSA steel with a regenerative cooling system.The proposed design ensures stable operation at temperatures up to 3000 K and internal pressures up to 6 MPa with a safety factor of at least 1.5.The proposed approach provides a practical framework for the design and material selection of high-performance rocket engine combustion chamber with nozzle assemblies.