METHOD OF ORGANISING OF WORKING PROCESS IN COMBUSTION CHAMBER OF LOW THRUST LIQUID FUEL ROCKET MOTOR Russian patent published in 2014 - IPC F02K9/62 F02K9/52 

FIELD: motors and pumps.

SUBSTANCE: method consists in supply of one of self-igniting fuels, for example, fuel through centrifugal injector coaxial with the combustion chamber with formation of cylindrical fog, passing into conical one behind the injector nozzle section and second component, for example, oxidant through spray nozzle injectors, uniformly located circumferentially, coaxial with the centrifugal injector nozzle, according to the applied invention the second component is completely supplied through spray nozzle injectors to the conical deflector, coaxial with them, primary films are formed on it, which then are supplied from the deflector sharp edge to the internal wall of the combustion chamber, and secondary films are formed on it, which for the first time are contacted with the film of the first component on a wall of a combustion chamber for organizing of liquid phase mixing of components by interpenetration of fuel and oxidant for their complete thickness on the combustion chamber wall and its simultaneous cooling by complete supplied component, meanwhile the length of free span of spray cone of the centrifugal injector is ensured before contacting the combustion chamber, exceeding no more than twice the rated length of film disintegration start, and the thicknesses of films of oxidant and fuel are formed from the relationships: $$\frac{D_o^{in}+{\delta }_o^{ch}}{2\left(r_{m.ch}+{\delta }_f\right)}=12\dots \mathrm{18,}$$ where $$\frac{D_o^{in}+{\delta }_o^{ch}}{d_{c.o}{n}_{c.o}}=6\dots \mathrm{14,}$$ - inner diameter of location of oxidant secondary films on the combustion chamber wall; $$D_o^{in}$$ - thickness of the oxidant secondary film on the combustion chamber wall; r_m.k. - radius of vortex on the nozzle centrifugal injector wall; δ_f - fuel fog thickness in the centrifugal injector nozzle; d_c.o. - oxidant jet diameter; n_c.o. - number of oxidant sprays.

EFFECT: improvement of cost efficiency and reliability of the low thrust liquid fuel rocket motor at the expense of increase of specific impulse with simultaneous maintaining of acceptable thermal state with the significant reserve by temperature of the motor elements.

2 cl, 1 tbl, 9 dwg