Liquid rocket engine under the scheme with staged combustion cycle

摘要

1. A liquid-propellant rocket engine according to the scheme with staged combustion comprising cameras (at least two) with regenerative cooling paths and the mixing head; turbopump gas generators supply system and engine chambers; Control and regulation system having puskootsechnye valves, damper and a choke ratio of fuel component, characterized in that the turbo-pump system motor power supply comprises two turbopump unit fed by two autonomous oxidizing gas generators, wherein the first and second TSNAs have the same structure and include coaxially mounted and successively disposed on the same shaft as the fuel pump, oxidant pump, and a gas turbine, wherein the fuel pump is configured two-stage second turbopump, kro IU, the outputs of the pumps fuel and oxidizer first turbopump connected conduits to the inlets of pumps of fuel and oxidizer second turbopump, the pump oxidizer second turbopump is connected to the mixing head of said gas generator through conduits, in which are installed puskootsechnye valves, and the output of the first stage fuel pump of the second turbopump connected to the mixing head of the engine through a throttle chambers ratio propellants puskootsechnye valves, piping and cooling paths the regenerative chambers, and the output from the second stage fuel pump of the second turbopump connected to the mixing head via a conduit and a gas generator controller tyagi.2. LRE according to claim 1, characterized in that it is made two-stage and petrol pump when powered turbines two TSNAs producer gas with an excess of the second fuel pump oxidant TSNAs