FIELD: engines and pumps.
SUBSTANCE: engine with two-position nozzle control includes combustion chamber, jet nozzle and pneumatic cylinder with piston and stock, which is located in combustion chamber. On pneumatic cylinder stock end there is central body partially closing the nozzle open flow area. Each cavity of pneumatic cylinder is connected via a three-way valve to atmosphere or to gas pressure source, and namely gas bottle or gas generating grain or the combustion chamber itself or its cooling jacket. Piston, stock and central body are hollow; at that, piston has non-return valves on both ends, which are directed towards the piston cavity, and central body has injectors or nozzles. Air or gas supply pipe to rear cavity of pneumatic cylinder is located in cavity of pneumatic cylinder and passes through the piston.
EFFECT: invention allows simplifying the design of engine with two-position nozzle control.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| STAROVEROV'S ROCKET ENGINE-12 | 2012 |
|
RU2514821C2 |
| DISPLACEMENT-TYPE LIQUID-PROPELLANT ROCKET (VERSIONS) | 2011 |
|
RU2468333C1 |
| ROCKET LAUNCHER AND ROCKET (VERSIONS) | 2012 |
|
RU2499973C1 |
| STAROVEROV'S-7 ROCKET ENGINE | 2012 |
|
RU2485341C1 |
| METHOD OF TURBOJET AFTERBURNING AND ENGINE TO THIS END (VERSIONS) | 2011 |
|
RU2474718C2 |
| ATMOSPHERIC LIQUID ROCKET /VERSIONS/ | 2011 |
|
RU2462687C1 |
| SELF-ADJUSTED TWO-MODE NOZZLE (VERSIONS) | 2011 |
|
RU2461729C1 |
| METHOD OF AIRCRAFT CONTROL AND DEVICE TO THIS END | 2011 |
|
RU2504815C2 |
| ADJUSTABLE LIQUID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2380564C1 |
| UNCASED MOTOR WITH SELF-FEEDING | 2010 |
|
RU2431052C1 |
