Structural optimization of rocket engine cooling channels

A mathematical and computational oriented design concept for the geometry of a rocket combustion chamber wall will be presented. This design concept is mainly composed of two components: First, a 'finite element analysis' of the thermomechanical problem of the structure, and second, a 'mathematical programming' applied to the optimization of the geometry. Optimization methods allow the improvement of an initial design of the combustion chamber such that the stress or temperature level is decreased and congruously, the life time will be increased. The main advantage of the presented method is that a design change will be determined automatically and furthermore the improvement of the structure with respect to a user defined objective is guaranteed. The proposed optimization strategy will be applied to the design improvement of a H₂/O₂ combustion chamber.