LOW-THRUST LIQUID-PROPELLANT ENGINE CHAMBER Russian patent published in 2016 - IPC F02K9/62 

FIELD: rocket science.

SUBSTANCE: invention relates to rocket engineering, in particular to protection of chamber walls of liquid rocket engine of thruster particularly overheating when setting up combustion process. Chamber consists of mixing head with jet nozzles, chamber with subcritical and supersonic parts of nozzle, with concentrically and with a gap installed inside insert, made in form of thin-wall cover from heat-resistant material, tightly fixed in connection point of mixing head and chamber housing to form a cavity gap communicated with chamber, axis of jet nozzles are directed tangentially to insert surface while near intersection points of axes of nozzles with surface of insert is made at least one hole displaced from intersection points in direction from jet injectors within circuits spreading primary films of oxidiser and fuel. Additionally, hole is displaced towards projection of one of axes of nozzles on surface of insert. Near each point of intersection of axes of spray nozzles with surface of insert is made at least one hole, and axes of spray nozzles are arranged in parallel. Holes are arranged behind intersection points of axes of spray nozzles with surface of insert on projections of axes of nozzles on wall of insert and have a shape elongated in direction of projections of axes of nozzles on wall of insert.

EFFECT: invention provides protection of liquid-propellant engine chamber casing wall especially low thrust against action of non-uniform along perimeter and in cross section of combustion chamber and high temperatures in area of minimum nozzle cross-section.

6 cl, 3 dwg