|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 8|
A turbo-rocket thruster is disclosed in which the turbine compressor is used to intake and compress a gaseous fuel for combustion with a stored oxidizer injected into the compressed gaseous fuel stream. The compressor stage is driven by the turbine stage, which is driven by burning gaseous fuel passing across the turbine blades. The burned gases are then expanded through an exhaust nozzle and thereby ejected to produce reaction thrust.
[ What is claimed is:] [1.] A gaseous-fuel breathing, stored-oxidizer turbo-rocket thruster comprising:(a) a gas duct defining a gaseous-fuel intake;(b) a source of gaseous fuel;(c) a source of stored oxidizer;(d) a compressor means for compressing gaseous fuel, the compressor means being disposed axially within the gas duct;(e) injector means to inject oxidizer into the compressed gaseous fuel so that the oxidizer mixes with the compressed gaseous fuel;(f) a turbine means operatively associated with the compressor means to drive the compressor means, th...