|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||29/89001 ; ; 29/428|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 13 인용 특허 : 3|
A method of fabricating a rocket engine combustion chamber comprising assembling a liner having cooling channels, a plurality of throat support sections, and a structural jacket having inlet and outlet manifolds. Then heating the assembly in a pressurized furnace to bond the assembled parts to each other.
A method of making a rocket engine combustion chamber comprising: forming a coolant liner having an outside surface; forming a plurality of coolant channels on the outside surface of the coolant liner so that the surface has a plurality of lands; forming at least two throat support sections; assembling the throat support sections together around the outside surface of the coolant liner; forming a structural jacket having an inside cavity, an inlet manifold, inlet feed passages, an outlet manifold, and outlet feed passages; inserting the coolant liner wit...