Patent ID: 6886327
Filing Date: 2005-05-03
Classification: B32B,C23C,F02K,F05C,F05D,Y10T

Abstract:
1. A combustion chamber for use in a rocket engine, the combustion chamber comprising: a substantially enclosed, hollow body having a rocket propellant inlet for receiving associated rocket propellant and an exhaust outlet for releasing exhaust, wherein the walls of the body are constructed of at least first and second structural layers, each comprising at least about 20% of the thickness of the walls of the body, said first structural layer being an interior structural liner layer of the body, having a thickness of at least about 20 mils and being formed of a first material selected from the group consisting of NiAl and NiAl-based alloys, and wherein said first material has a first predetermined ductility and a thermal conductivity of at least about 40 W/mK, and said second structural layer being formed of a second material selected from the group consisting of Ni-based superalloys, Co-based alloys, Fe-based alloys, Cu, and Cu-based alloys, wherein said second material is more ductile than said first material.