LIQUID-PROPELLANT ENGINE WITH GENERATOR GAS STAGED COMBUSTION CYCLE Russian patent published in 2014 - IPC F02K9/48 

FIELD: engines and pumps.

SUBSTANCE: invention relates to liquid-propellant engines, particularly, to multichamber rocket engines. Proposed engine has at least two chambers incorporating regenerative cooling circuit and mixing heads, turbopump system to feed gas generators and engine chambers. Besides, it incorporates control system with starting-shutoff valves, thrust regulator and fuel components ratio throttle. In compliance with this invention, engine feed turbopump system comprises two turbopump units supplied by two self-contained oxidative gas producers. Note here that first and second turbopump units feature identical power and comprises aligned fuel pump, oxidiser pump and gas turbine fitted on one shaft. Note also that second turbopump unit pump represents a two-stage design. Besides, outlets of first turbopump unit fuel and oxidiser pumps are communicated via pipelines with inputs of second turbopump unit fuel and oxidiser pumps. Second turbopump unit oxidiser pump communicates with mixing heads of said gas producers via pipelines incorporating starting-shutoff valves. Outlet of second turbopump unit oxidiser pump first stage is connected with mixing heads of engine chambers via fuel components ratio throttle, starting-shutoff valves, pipelines and chamber regenerative cooling circuits. Note also that second turbopump unit fuel pump second stage is connected with gas producer mixing heads via pipeline and thrust regulator.

EFFECT: decreased dynamic loads at turbopump unit, higher thrust.

1 dwg