VORTEX LOW-THRUST ROCKET ENGINE ON GAS FUEL Russian patent published in 2016 - IPC F02K9/62 

FIELD: missile.

SUBSTANCE: invention relates to rocket engineering and can be used in development of rocket engines operating on gaseous fuel mixture components. Vortex low-thrust rocket engine on gas fuel comprises combustion chamber with nozzle and tangential swirlers for supply of fuel components. In combustion chamber on side of its front bottom there are internal and external swirlers made coaxially and separated by cylindrical barrel. Swirling chamber of inner swirler with radius R₁ is inner surface of shell, swirling chamber of outer swirler with radius R₂ is inner surface of combustion chamber. Tangential channels to feed fuel components to internal and external swirlers are directed oppositely. Height of cylindrical barrel is defined by relationship h = (0.4÷0.6)R₂, and combustion chamber has a narrowing of radius R₂ to radius R₁ at distance L = (1÷1.5)R₂ from front bottom. Ratio of radii of swirling chambers of outer and inner swirlers is determined by solving an algebraic equation.

EFFECT: invention provides operation with any gaseous fuel compositions and high energy-traction characteristics due to increased completeness of combustion at intensive mixing fuel and oxidiser in opposite swirled flows, as well as compensation of reactive force causing undesirable rotation of engine.

1 cl, 4 dwg