LIQUID-PROPELLANT THRUSTER AND METHOD OF STARTING SUCH THRUSTER Russian patent published in 2002 - IPC

FIELD: rocket pods for space engineering. SUBSTANCE: mixing member introduced into engine combustion chamber has internal reaction chamber and auger provided on its inner surface for twisting the gaseous component. Cavity for delivery of fuel with injection orifices is located in ignition unit mounted before mixing member. Mounted at outlet of mixing member, on its outer surface if bush forming fuel flow twisting cavity together with body of mixing member; this cavity is provided with tangential holes for fuel. Outlet of fuel twisting cavity to main combustion chamber is pinched by circular projection made in bush. Provision is made for cutout of delivery of fuel to prechamber after initial pressure in main combustion chamber has been attained and entire mass flow is changed-over to main combustion chamber. EFFECT: enhanced completeness of combustion, increased specific thrust pulse of engine working on non-hypergolic propellant components. 3 cl, 2 dwg