It is known for a rocket engine to include as a component thereof a thrust chamber having several sections joined to each other in an axial direction. Each of the sections is formed by a wall structure having an inner wall, an outer wall parallel thereto, and cooling channels formed between the inner and outer walls. The wall structure is continuous in the circumferential direction of the section.
The inner wall of each of two joined (to be joined) sections projects further (longer) in the extension direction of the wall structure than does the outer wall. The projecting end portion of the inner wall of one section is joined to the adjacent projecting end portion of the inner wall of the other section by a weld joint. In this way, a substantially continuous inner wall is achieved.
Thereafter, a ring-shaped element is radially arranged outside the weld joint, and said element is joined to the end portions of the adjacent outer walls. In this way, the cooling channels of one of the sections can communicate with the cooling channels of the adjacent section.
Even though the above described rocket engine component performs satisfactorily, there is still a desire to increase the life of the component so that it can be used for an increased number of engine cycles.