LIQUID-PROPELLANT ENGINE WITH IONISER IN COMBUSTION CHAMBER AND HEATING OF GASES BY PLASMA IN NOZZLE Russian patent published in 2024 - IPC F02K9/42 F02K99/00 F03H1/00 

FIELD: engines; cosmonautics.

SUBSTANCE: invention relates to rocketry for use in spacecraft, including those launched from the surface of the earth or flying along ballistic trajectories. Engine comprises small-size combustion chamber, ceramic conical nozzle, their cooling circuits, one or several nozzles. In order to increase the thrust of the liquid-propellant engine, a combined engineering solution is proposed, which enables to significantly increase the specific impulse with a certain optimum increase in the weight of additional parts, assemblies and instruments. It is proposed to use heating of gas flow by plasma in ceramic, cooled, conical nozzle by inductor of electromagnetic high-frequency field with high specific power exceeding specific thermal power of combustion chamber. Number of inductors can be more than one, operating at multiple frequencies in permitted ranges and arranged along conical nozzle of certain dimensions. Main inductor(s) is necessarily placed between the critical and design sections. Number of inductors depends on the pressure in the combustion chamber, which determines their diameter and power. In order to increase the degree of fuel combustion, a special device is installed on the combustion chamber - an ioniser of dense gas flows using the Compton effect, which emits an intense, pulsed, directed flow of X-ray quanta with energy depending on the gas pressure in the combustion chamber and the type of fuel. Another purpose of the ionizer is to create a stream of ionised gas with optimum conductivity at the inlet of the main inductor.

EFFECT: invention allows reducing the amount of unburned fuel in the combustion chamber and thus increasing its efficiency.

2 cl, 3 dwg