LIQUID-PROPELLANT ROCKET ENGINE MIXING CHAMBER Russian patent published in 2013 - IPC F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: proposed mixing chamber comprises coaxial-jet injectors arranged in mixing head units in concentric circles. Said injectors comprise tubular case with axial inlet/outlet and main axial channel and one blind tube secured coaxially with said case on, at least, one pylon made integral therewith and with tubular case. Tubular case main axial channel features stepped flow section on outlet side. Stepped alteration of injector case flow section shows decrease from said pylons to outlet and is shaped to, at least, one confuser. Tubular case outlet has sleeve to make annular chamber between case outer surface and sleeve inner surface to accommodate helical channels extending to communication with main axial channel. Adjusting element, a chamfer is made on tubular case axial inlet to vary its geometrical parameters in adjustment. Tubular case represents a split design. Blind tube outer surface at tubular case outlet has pylons interacting with tubular case inner surface. Lengthwise axes of said pylons are located at definite angle to injector lengthwise axis. Said pylons has channels with their outlets directed at angle to injector lengthwise axis other than that of said pylons Outlet of said channels communicates with blind tube chamber while their inlet communicates with aforesaid annular chamber. Blind split tube consists of pylon part and adapter. Note here that jet is arranged at their joint. Said blind tube is secured coaxially inside the case at two pylons. Two transverse through holes are made inside every said pylon. Injector tubular is composed of inlet and outlet parts tightly welded together and provided with, at least, one annular bulge.

EFFECT: higher operating efficiency.

4 cl, 5 dwg