FIELD: rocket science.
SUBSTANCE: invention relates to rocket engineering, particularly, to mixing in combustion chamber of low-thrust liquid-propellant engine. Combustion chamber of low-thrust liquid-propellant engine comprising a chamber and mixing head with arranged along axis of two-component centrifugal atomiser, external and internal swirling chambers communicated with collectors of corresponding fuel components, according to present invention, between mixing head and chamber there is a prechamber with a cylindrical part adjacent to mixing head, and a conical part coupled on one side with said cylindrical part, and on other side with chamber, wherein closing line of conical films of fuel components of working chamber is located in close proximity to conical walls of prechamber. Line of joining conical films of operating chamber is located in close proximity to conical part of prechamber at point of interfacing with cylindrical part of prechamber.
EFFECT: invention ensures uniform distribution of ratio of fuel components and more complete conversion of fuel into combustion products.
1 cl, 1 dwg
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