FIELD: engine building.
SUBSTANCE: invention relates to liquid-propellant rocket engines. Liquid-propellant engine nozzle element includes an oxidizer channel, a central cavity fluidly connected to the oxidizer channel downstream of the oxidizer channel, a first annular space, at least partially enclosing the oxidizer channel and fluidly connected to the source of the igniting liquid downstream of the source of the igniting liquid, and the second annular space, at least partially enclosing the oxidizer channel and fluidly connected to the fuel source downstream of the fuel source. Second ring space is connected by fluid medium between the first annular space and the central cavity.
EFFECT: invention provides higher efficiency of fuel ignition in rocket engines.
6 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| NOZZLE WITH NOZZLE ELEMENTS ARRANGED IN CIRCUMFERENTIAL ROWS THAT ALTERNATE BETWEEN COUNTERCLOCKWISE TWISTING AND CLOCKWISE TWISTING | 2018 |
|
RU2765592C1 |
| COMBUSTION CHAMBER OF LOW-THRUST LIQUID-PROPELLANT ENGINE | 2016 |
|
RU2685166C2 |
| LIQUID-PROPELLANT ENGINE OF OPEN CONFIGURATION | 2010 |
|
RU2459970C2 |
| CHAMBER OF LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2449158C1 |
| LIQUID-PROPELLANT ROCKET ENGINE CHAMBER | 2011 |
|
RU2451203C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2011 |
|
RU2450155C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2013 |
|
RU2514582C1 |
| LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2445496C1 |
| LIQUID FUEL ROCKET MOTOR | 2013 |
|
RU2531831C1 |
| LIQUID PROPELLANT ROCKET ENGINE | 2012 |
|
RU2485339C1 |
