LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2014 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry. Proposed chamber comprises outer and fire shells with cooling circuit ducts arranged there between and composed of H-beam spacers with flow turbulence promoters arranged thereat. H-beam spacer flanges feature variable width owing to alternating recesses made thereat. Note here that said turbulence promoters are formed by said alternating recesses. Said recesses of every H-beam spacer flange are staggered. Said recesses of top and bottom H-beam spacer flanges are staggered. Recesses of adjacent flanges are arranged so that recesses on flange of one spacer are located opposite the ledges of adjacent spacer. Recess depth makes 25-75% of flange width. Through channels are made in vertical walls of H-beam spacers.

EFFECT: higher efficiency of heat exchange in channels.

6 cl, 6 dwg