LOW-THRUST ROCKET ENGINE ON NON-SELF-INFLAMMABLE LIQUID FUEL AND GASEOUS OXIDANT Russian patent published in 2020 - IPC F02K9/52 F02K9/62 

FIELD: aerospace engineering.

SUBSTANCE: invention relates to aerospace engineering, particularly, to low-thrust rocket engines on non-self-igniting gaseous oxidant and liquid fuel. Rocket engine includes ignition unit and plug, electric pneumatic valves of oxidising agent "O" and fuel "Γ", mixing head with igniter, combustion chamber and nozzle. At that ignition of fuel components is carried out in ignition device consisting of two cylindrical stages, into which liquid fuel (upper stage) and gaseous oxidiser (lower stage) are supplied tangentially, wherein the latter by its peripheral area is connected by two longitudinal channels with discharge cavity of ignition plug for supply of gas-liquid mixture to spark discharge zone and ignition of main fuel charge in engine combustion chamber by means of flame coming from igniter. Effective mixture formation is organized by means of a different-type circumferential wedge element on the inner side of which a thin film of liquid fuel flows from the jet nozzles "Γ" onto the wedge plane, the thickness of which is an order of magnitude smaller than the diameter of drops at the nozzles outlet, and the outer edge of the wedge element forms a slit nozzle of the gaseous oxidiser with parameters, in particular component speed, approximately five times higher than the liquid velocity. After interaction of gaseous oxidant and liquid fuel on sharp edge of wedge element, crushing of wreath of liquid component into fragments 15–20 mcm, vector of gas-liquid flow pulse is directed at angle of 25–35° to axis of engine, which ensures high completeness of combustion in combustion chamber.

EFFECT: invention improves reliability of ignition of non-self-igniting gas-liquid fuel with high dynamic and energy parameters while ensuring allowable thermal state of the structure.

3 cl, 2 dwg