|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/257; 060/267; 239/127.1|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 3|
A combustion chamber/supersonic nozzle assembly is cooled by an array of coolant channels in the wall of the assembly with coolant being fed to the assembly at the throat plane between the subsonic (convergent) and supersonic (divergent) sections. A minor portion of the coolant entering at the throat plane is directed to coolant channels in the supersonic section wall, while the remainder is directed to a complex arrangement of channels in the subsonic section wall. The latter arrangement includes an outer layer of wide axially oriented channels for deli...
What is claimed is: 1. A convergent-divergent rocket nozzle comprising convergent and divergent sections meeting at a throat with said divergent section terminating at an exit plane, coolant jackets surrounding said convergent and divergent sections, an inlet manifold arranged to supply coolant to said coolant jackets through entry ports at said throat, a first set of coolant channels in said coolant jacket surrounding said convergent section, and a second set of coolant channels in said coolant jacket surrounding said divergent section and extending fr...