|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||602/58 ; 600/259|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 23 인용 특허 : 3|
The engine comprises a chamber, fuel and oxidizer booster pumps, a turbopump unit, a gas generator, an electrically driven thrust regulator, and a fuel throttle. A programmable starting and ignition system is introduced, which includes a fuel tank, connected to the thrust regulator, and a first ampoule with starting fuel, an output of which through a starting/cut-off valve is connected to fuel injectors of the gas generator. The aforesaid tank is also connected through a second ampoule to the starting fuel and by a jet to autonomous ignition injectors lo...
[ What is claimed is:] [1.]1. A liquid-propellant rocket engine with turbine gas afterburning comprising:a combustion chamber, inside which a mixing head for a working mixture is mounted and in which ignition injectors are provided;booster prepumps--a fuel booster pump and an oxidizer booster pump, mounted at an engine inlet;a turbopump unit comprising a turbine, a single-stage oxidizer pump and a two-stage fuel pump, which are made as centrifugal inclined Archimedian screw pumps and inlet main lines of which are connected to said booster prepumps respec...