IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0523282
(2012-06-14)
|
등록번호 |
US-8794572
(2014-08-05)
|
우선권정보 |
FR-11 55332 (2011-06-17) |
발명자
/ 주소 |
- Porte, Alain
- Chelin, Frederic
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
9 |
초록
▼
An air intake of an aircraft nacelle includes: on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outsi
An air intake of an aircraft nacelle includes: on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).
대표청구항
▼
1. An air intake of an aircraft nacelle comprising: a lip (42) that is defined by a wall (52) having a surface that is in contact with aerodynamic flows, the lip being extended on an inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant;an outside wall (4
1. An air intake of an aircraft nacelle comprising: a lip (42) that is defined by a wall (52) having a surface that is in contact with aerodynamic flows, the lip being extended on an inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant;an outside wall (46);a surface Joule-effect defrosting system (58);at least a first alveolar structure (60.1) that is made of a material that conducts heat that is flattened against an inside surface of the wall (52) and inserted between said wall (52) and the defrosting system (58); andat least two second alveolar structures (60.2) that are made of composite material, the at least two second alveolar structures being adjacent to the first alveolar structure (60.1), the at least two second alveolar structures (60.2) being flattened against the inside surface of the wall (52), with the defrosting system (58) being inserted between the at least two second alveolar structures (60.2) and said wall (52), whereinthe first alveolar structure (60.1) is in a zone Z1 that corresponds to approximately ⅔ of a height of the air intake that is sized for mechanical strength, and at least of the second alveolar structures (60.2) is in at least one zone Z2 that is adjacent to the zone Z1. 2. The air intake of an aircraft nacelle according to claim 1, wherein a shock absorber in the form of a skin (62) is attached to the Joule-effect defrosting system (58). 3. The air intake of an aircraft nacelle according to claim 2, wherein the skin (62) comes in the form of a fiber-based layer. 4. The air intake of an aircraft nacelle according to claim 1, wherein the first alveolar structure (60.1) that is made of a heat-conductive material extends over a zone Z1 that corresponds to at least ⅔ of the height of the air intake. 5. The air intake of an aircraft nacelle according to claim 1, wherein the first alveolar structure in the zone Z1 is made of a conductive material, and the at least one of the second type of alveolar structures (60.2) is in the zone(s) Z2 made of composite material, and wherein the Joule-effect defrosting system (58) is flattened against the surface of the first alveolar structure (60.1) that is opposite to the wall (52) in the zone Z1 and flattened against the inside surface of the wall 52, inserted between said wall and the second alveolar structure(s) (60.2) in the zone(s) Z2. 6. The air intake of an aircraft nacelle according to claim 4, wherein edges (66) of the first alveolar structure (60.1) and adjacent second alveolar structures (60.2) have complementary beveled shapes. 7. The air intake of an aircraft nacelle according to claim 1, wherein free edges of the alveolar structure(s) have a beveled shape. 8. An aircraft nacelle that incorporates an air intake according to claim 1, wherein the nacelle comprises a rear frame (48) at a junction plane between said air intake and a power plant that is connected to the wall (52) that borders the lip (42). 9. The aircraft nacelle according to claim 8, wherein the rear frame is tilted, and the frame has an outside edge (72) offset toward a front of the nacelle relative to an inside edge (74) of the frame. 10. The air intake of an aircraft nacelle according to claim 1, wherein a shock absorber in the form of a skin (62) is attached to the Joule-effect defrosting system (58). 11. The air intake of an aircraft nacelle according to claim 1, wherein cells of the first alveolar structure (60.1) have a cross-section of 2 mm to 3 mm. 12. The air intake of an aircraft nacelle according to claim 1, wherein cells of each second alveolar structure (60.2) have a cross-section of 10 mm to 12 mm. 13. The air intake of an aircraft nacelle according to claim 1, wherein the first alveolar structure (60.1) is formed from conductive aluminum alloy, and each second alveolar structure (60.2) is a non-conductive honeycomb of conductive material. 14. An air intake of an aircraft nacelle comprising: a lip (42) that is defined by a wall (52) having a surface that is in contact with aerodynamic flows, the lip being extended on an inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant;an outside wall (46);a surface Joule-effect defrosting system (58);at least a first alveolar structure (60.1) that is made of a material that conducts heat that is flattened against an inside surface of the wall (52) and inserted between said wall (52) and the defrosting system (58); andat least two second alveolar structures (60.2) that are made of composite material, the at least two second alveolar structures being adjacent to the first alveolar structure (60.1), the at least two alveolar structures having cells with a diameter that is different from that of the first alveolar structure, the at least two second alveolar structures (60.2) being flattened against the inside surface of the wall (52), with the defrosting system (58) being inserted between the at least two second alveolar structures (60.2) and said wall (52),wherein edges (66) of the first alveolar structure (60.1) and adjacent second alveolar structures (60.2) have complementary beveled shapes so that the Joule-effect defrosting system is not flattened against an edge that borders two surfaces, andthe first alveolar structure (60.1) is in a zone Z1 that corresponds to approximately ⅔ of a height of the air intake that is sized for mechanical strength, and at least of the second alveolar structures (60.2) is in a or in at least one zone Z2 that is adjacent to the zone Z1. 15. The air intake of an aircraft nacelle according to claim 14, wherein a shock absorber in the form of a skin (62) is attached to the Joule-effect defrosting system (58). 16. The air intake of an aircraft nacelle according to claim 15, wherein the skin (62) comes in the form of a fiber-based layer. 17. The air intake of an aircraft nacelle according to claim 14, wherein the first alveolar structure (60.1) that is made of a heat-conductive material extends over a zone Z1 that corresponds to at least ⅔ of the height of the air intake. 18. The air intake of an aircraft nacelle according to claim 14, wherein the first alveolar structure in the zone Z1 is made of a conductive material, and the at least one of the second type of alveolar structures (60.2) is in the zone(s) Z2 is made of composite material, and wherein the Joule-effect defrosting system (58) is flattened against the surface of the first alveolar structure (60.1) that is opposite to the wall (52) in the zone Z1 and flattened against the inside surface of the wall 52, inserted between said wall and the second alveolar structure(s) (60.2) in the zone(s) Z2.
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