| 摘要 |
FIELD: rocketry; power engineering. ^ SUBSTANCE: proposed mixing element consists of outer, inner and middle bushings forming circular spaces for delivery of gaseous propellant and liquid oxidizer. Circular slots are made in outer bushing from side of delivery of propellant parallel to axis of mixing element. Said slots are separated by lands in which holes are made perpendicular to axis to deliver oxidizer into circular channel opening into combustion chamber, and in outer bushing pointed to combustion zone ring circular space for propellant is made. Middle and inner bushings form second additional circular channel to deliver propellant into chamber, and outer and middle bushings, from side opposite to zone of combustion, are installed close to each other. ^ EFFECT: provision of maximum possible combustion of propellants of different types reduced number of mixing elements on burner plate. ^ 2 cl, 2 dwg |
