METHOD OF COOLING HEAT-STRESSED SECTIONS OF LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2010 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: invention can be used in development of liquid-propellant rocket engines (LPRE), in particular LPRE without generator, running on cryogenic components, for example oxygen and hydrogen. Proposed method consists in making alternating ribs on rear side of cooled surface that make with outer case the cooling channels and forcing coolant via produced channels. In compliance with this invention, said ribs features invariable thickness and channels feature variable-width trapezoidal section with rounded angles adjoining inner surface of the case. Note here that inner surface of inner case has, on the side of combustion chamber whereon ribs are located, lengthwise shaped grooves with their profile being equidistant the profile of radius of transition between ribs and inner cylindrical surface of cooling part channels. Lengthwise ribs are arranged between said lengthwise grooves on the inner case inner surface.

EFFECT: improved cooling of heat-stressed sections and conditions of heat exchange between fuel combustion products and coolant.

2 cl, 3 dwg