Thrust chamber of high performance bi-propellant liquid rocket engines is a critical component of the launch vehicles because it is designed to operate in some of the most severe conditions seen in engineering practice. The requirement of reducing the temperature of the walls exposed to the hot gas can be met with high-thermal-conductivity copper alloys while the mechanical stiffness is achieved by using high-strength steel or nickel alloys. Because the stress–strain behaviour of a regeneratively cooled thrust chamber is directly correlated with its temperature behaviour, it is of primary importance to select the correct alloy. Nowadays manufacturing processes are playingan important role in the global space industry, with particular emphasis respect to space propulsion.