PUMPLESS CRYOGENIC LIQUID PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2013 - IPC F02K99/00 F02K9/94 

FIELD: engines and pumps.

SUBSTANCE: in two versions of a pumpless cryogenic liquid propellant rocket engine, comprising an engine chamber with a combustion chamber and a cooling jacket, tanks with liquid fuel and oxidant, systems of fuel supply, for supply of each fuel component from a tank into an engine chamber a pair of parallel connected intermediate cylinders is used with stop devices at the inlet and outlet, inside the intermediate cylinders there is a metering reservoir with an expansion nozzle and a heat exchanger, and cavities of the intermediate cylinders via the stop devices are connected to a device of efficient discharge of gaseous remains. In the first version of the engine outlets of intermediate fuel cylinders are connected via a pressure controller with entry into the cooling jacket of the engine chamber, and outlets of the intermediate oxidant cylinders are connected via a pressure controller with entry into the engine combustion chamber. Besides, inlets of heat exchangers of intermediate cylinders via stop devices are connected to the outlet of the engine chamber cooling jacket, and outlets of heat exchanger are connected to the inlet of fuel into the engine combustion chamber. In the second version the engine chamber cooling jacket is divided into a cooling section by fuel and a cooling section by oxidant, at the same time outlets of intermediate cylinders of fuel and oxidant are connected via pressure controllers with inlets of the sections of the engine chamber jacket of cooling by fuel and oxidant accordingly, besides, inlets of heat exchangers of the intermediate fuel and oxidant cylinders via stop devices are connected to outlets of appropriate sections of engine chamber cooling, and outlets of heat exchangers of intermediate fuel and oxidant cylinders are connected with appropriate inlets of these components into the engine combustion chamber.

EFFECT: invention provides for development of a reliable and environmentally clean cryogenic liquid propellant rocket engine with a displacement system of fuel supply having higher efficiency and expanded area of application and having reduced dimensions and mass with higher reliability of start-up under conditions of zero gravity, higher evenness and cost-effectiveness of fuel consumption, simplified modes of operation, reduced cost of development and manufacturing of an engine.

2 cl, 3 dwg