FIELD: aircraft engineering.
SUBSTANCE: proposed nacelle comprises rear section to make outer structure that forms annular secondary flow channel 3 together with concentric inner structure 4 including inner skin 10 surrounding turbojet rear. Said inner structure has release device 11 to ensure fast overpressure release into said annular channel.
EFFECT: higher efficiency.
8 cl, 9 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| NACELLE EQUIPPED WITH, AT LEAST, ONE OVERPRESSURE VALVE | 2008 |
|
RU2475418C2 |
| SOUND-ABSORBING PANEL FOR EJECTOR NOZZLE | 2009 |
|
RU2526215C2 |
| TURBOJET NACELLE WITH VENT DISCHARGE OPENING CONTROLLED CROSS-SECTION | 2011 |
|
RU2573686C2 |
| NACELLE AIR INTAKE AND NACELLE CONTAINING SUCH AIR INTAKE | 2020 |
|
RU2801764C2 |
| OVERPRESSURE RELEASE HATCH MOUNTED AT TURBOJET NACELLE WALL | 2009 |
|
RU2509687C2 |
| NACELLE WITH ADJUSTABLE OUTLET SECTION | 2008 |
|
RU2469923C2 |
| ACOUSTIC PANEL FOR TURBOJET ENGINE NACELLE, WITH IN-BUILT FASTENERS | 2011 |
|
RU2579785C2 |
| NACELLE AIR INTAKE WITH ACOUSTIC PANEL | 2020 |
|
RU2803661C2 |
| FIXATOR | 2008 |
|
RU2463424C2 |
| FLAP REVERSER | 2011 |
|
RU2570740C2 |
