FIELD: rocket engines.
SUBSTANCE: invention relates to device for amplifying transfer of heat to coolant on inner side of nozzle wall provided with cooling channels in rocket engines with expansion cycle. To disturb boundary layer at nozzle wall and amplify transfer of heat, inner side of nozzle wall pointed to flame has surface with roughness at least 50y+ where y+ is lower limit at which roughness of surface is most effective from point of view of heat transfer. At roughness of surface at least 50y+ it penetrates through viscous sublayer of boundary layer at nozzle wall.
EFFECT: increased power of rocket engine owing to amplification of heat transfer on wall of nozzle of rocket engine.
3 cl, 1 dwg
