Application of the substructure method for thermal stress-strain assessment of a liquid-propellant rocket engine combustion chamber
The paper specifies the procedure of a finite element analysis used to assess the stress-strain state of a liquid-propellant rocket engine combustion chamber and a nozzle end. A cyclic load for three steps is examined. The ANSYS finite element software is used during the analysis. The authors consider both the substructure method and a cyclic symmetry in order to reduce the model size significantly. The obtained results showed the planning plastic zones, which are critical for low-cycle fatigue. The procedure and numerical models were tested.