FIELD: engines and pumps.
SUBSTANCE: aircraft engine output device contains an outlet nozzle (1), a main engine outlet nozzle (2), at least one rotary damper (3), a control gear drive and a noise silencer (4). The device is provided with additional outlet nozzle (5) and a distributing branch pipe (6) coaxially connected to outlet branch pipe (1) of the engine and divided in the zone of rotary damper installation into two branch pipes connected to each other from the side of outlet branch pipe, each of which is provided with outlet nozzle, the main one (2) is in the form of the main outlet nozzle of the engine, and the other one is additional (5). The noise silencer (4) is located in one of the branches before the additional outlet nozzle (5). Actuator of the control mechanism is connected to the damper (3). The rotary damper (3) is installed for alternate closure of each of the branches.
EFFECT: invention improves efficiency of noise suppression during take-off and landing, reduces pressure losses of the outlet jet and fuel consumption during cruising operation.
12 cl, 6 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| OUTPUT DEVICE OF AIRCRAFT JET ENGINE | 2018 |
|
RU2682804C1 |
| INTERNAL COMBUSTION ENGINE | 2017 |
|
RU2644795C1 |
| AIRCRAFT TURBOFAN ENGINE | 2002 |
|
RU2243399C2 |
| AIRCRAFT POWER PLANT | 2017 |
|
RU2652842C1 |
| FAN OF TURBOFAN AIRCRAFT ENGINE | 2017 |
|
RU2675031C1 |
| AIRCRAFT TURBOJET ENGINE FURNISHED WITH ACOUSTIC NOISE KILLER | 2005 |
|
RU2373415C2 |
| AIRCRAFT ENGINE NACELLE WITH CASCADE TYPE THRUST REVERSER AND VARIABLE GEOMETRY NOZZLE | 2011 |
|
RU2571999C2 |
| AIRCRAFT CONROD-FREE FAN ENGINE | 2010 |
|
RU2433292C1 |
| OUTPUT DEVICE OF A TURBOJET ENGINE | 2023 |
|
RU2807307C1 |
| ULTRA SHORT VERTICAL TAKE OFF AND LANDING AIRCRAFT | 0 |
|
SU1816717A1 |
