|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||298/900.1 ; 209/523|
|발명자 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 12 인용 특허 : 7|
A fabricating method for a one-piece refractory metal rocket engine chamber is described. Hollow liner sections of a platinum group metal or alloy are inserted into a chamber barrel portion to form the combustion chamber, connecting into a conical portion, a venturi throat and into a second conical portion, forming an expansion nozzle exit of the chamber. The hollow liner sections correspond to the interior shapes of the chamber portions. A refractory metal split hollow mandrel completes an assembly which is subjected to a hot isostatic pressing cycle. T...
[What is claimed is:] [1.]forming a one piece hollow refractory metal thrust chamber having a barrel portion forming a combustion chamber, a first conical portion connecting the barrel portion to a venturi throat section, and a second conical portion extending downstream from the venturi throat portion and forming an expansion nozzle;positioning a first hollow metal cylindrical liner section, having a first end and a scarfed second end, in said barrel portion;positioning a second hollow metal liner section having a scarfed first end and a scarfed second ...