FIELD: turbojet engines.
SUBSTANCE: air intake (1) of the turbojet engine nacelle contains a ring structure (110), including an outer fairing (100) defining the outer aerodynamic surface, and an inner fairing (102) defining the inner aerodynamic surface. The outer (100) and inner (102) fairings are connected at the front downstream by the edge (108) of the air intake, forming the leading edge. The inner fairing (102) includes an outer skin (114) attached to the edge (108) of the air intake via an upstream mounting flange (118). The outer casing (114) is configured to be attached to the outer casing (116) of the fan by means of a downstream mounting flange (122). The air intake (1) contains individual acoustic panels (2) attached to the outer skin (114) and containing a perforated acoustic skin (200) and a cellular core (202).
EFFECT: simplification of maintenance and repair is achieved.
13 cl, 11 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIR INTAKE FOR TURBOJET ENGINE NACELLE | 2020 |
|
RU2806229C2 |
| NACELLE AIR INTAKE AND NACELLE CONTAINING SUCH AIR INTAKE | 2020 |
|
RU2801764C2 |
| NACELLE AIR INTAKE AND NACELLE CONTAINING SUCH AIR INTAKE | 2020 |
|
RU2802275C2 |
| AIRCRAFT ENGINE ASSEMBLY | 2011 |
|
RU2570181C2 |
| NACELLE AIR INTAKE AND NACELLE CONTAINING SUCH AIR INTAKE | 2020 |
|
RU2804492C2 |
| TURBOJET ENGINE POD | 2008 |
|
RU2471681C2 |
| TURBOJET NACELLE | 2011 |
|
RU2569503C2 |
| ACOUSTIC PANEL FOR TURBOJET ENGINE NACELLE, WITH IN-BUILT FASTENERS | 2011 |
|
RU2579785C2 |
| AIRCRAFT MODULE AND AIR INTAKE CONNECTED TO IT | 2019 |
|
RU2789463C2 |
| TURBOJET NACELLE AIR INTAKE LOCK SYSTEM | 2008 |
|
RU2500586C2 |
