LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2015 - IPC F02K9/42 F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: engine comprises combustion chamber with mixing head, turbopump unit, gas generator, power supply and control units. Proposed chamber comprises inner shaped shell with cooling path ribs made at outer surface of the latter, outer shaped shell fitted at inner one and secured therewith by crests of said ribs. Said shells and ribs make the cooling channels. Hollow webs are made between cooling path ribs to connect crests of said ribs, outer profile of said web complying with that of cooling path. Said webs connect the sets of ribs. Channel is made between sets of ribs, on their every side, its width being equal to that of cooling path at the location of 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 includes three ribs.

EFFECT: higher reliability owing to higher stiffness of outer shell.

2 cl, 3 dwg