LIQUID PROPELLANT ROCKET ENGINE CIRCULAR CHAMBER Russian patent published in 2015 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket propulsion engineering and can be used in development of liquid-propellant rocket engines running on cryogenic components, mainly, on oxygen and hydrogen. Circular combustion chamber comprises circular mixing head, circular regenerative cooling combustion chamber with dish-like nozzle of external divergence and shaped central body. Shaped inner and outer shells are interconnected over cooling path ribs. Hollow webs connecting ribs crests are arranged between cooling path ribs. Outer shape of said webs corresponds to shape of cooling path. Note here that said webs interconnect the set of ribs with cooling channels on each side at the location of said webs. Note here that adjacent webs are shifted relative to each other by cooling channel width at their location. Width of said webs equals that of cooling channel at the location of webs. Sets of ribs include three ribs.

EFFECT: higher stability of inner shell and pressure in the chamber at minimum overall dimensions.

2 cl, 3 dwg