Coating for acoustic treatment that integrates the function of hot-air treatment of frost
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0663608
(2008-06-03)
|
등록번호 |
US-8172037
(2012-05-08)
|
우선권정보 |
FR-07 55586 (2007-06-08) |
국제출원번호 |
PCT/FR2008/050974
(2008-06-03)
|
§371/§102 date |
20091208
(20091208)
|
국제공개번호 |
WO2009/001002
(2008-12-31)
|
발명자
/ 주소 |
- Porte, Alain
- Lalane, Jacques
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
4 |
초록
▼
The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at least one cellular structure (30) and a reflective layer (32), cha
The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at least one cellular structure (30) and a reflective layer (32), characterized in that it comprises ducts (34) provided between said cellular structure (30) and the acoustically resistive structure (28), the ducts being each defined by a wall (36) separate from the walls of the cellular structure (30) and one end of the ducts being connected to a hot air supply.
대표청구항
▼
1. Coating for acoustic treatment that is connected at one surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby said coating comprises an acoustically resistive layer (28), at least one alveolar structure (30), and a reflective layer (32), cha
1. Coating for acoustic treatment that is connected at one surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby said coating comprises an acoustically resistive layer (28), at least one alveolar structure (30), and a reflective layer (32), characterized in that it comprises pipes (34) that are placed between said alveolar structure (30) and the acoustically resistive structure (28), whereby the pipes are each delimited by a wall (36) that is separate from the walls of the alveolar structure (30) and whereby one of the ends of the pipes is connected to a hot air intake. 2. Coating for acoustic treatment according to claim 1, wherein the pipes (34) are separate and each have a concave section with ends (38) on both sides that are connected to the inside surface of the acoustically resistive structure. 3. Coating for acoustic treatment according to claim 1, wherein the pipes (34) are obtained by the shaping so as to form pipes (34) with a layer that is inserted between the alveolar structure (30) and the acoustically resistive layer (28). 4. Coating for acoustic treatment according to claim 2, wherein the alveolar structure (30) comprises grooves (40) on the surface that can be flattened against the acoustically resistive structure (28), and the shapes of said grooves are adapted to those of the pipes. 5. Coating for acoustic treatment according to claim 1, wherein the pipes (34) are essentially rectilinear and parallel to one another. 6. Aircraft nacelle that comprises an air intake (22) that incorporates a coating for acoustic treatment according to claim 1. 7. Aircraft nacelle according to claim 6, wherein the pipes (34) extend upstream from the coating for acoustic treatment to form stiffeners. 8. Aircraft nacelle according to claim 6, wherein the acoustically restive structure comprises perforations to deliver the air that is used for defrosting. 9. Aircraft nacelle according to claim 6, wherein the hot air intake is connected to pipes so that the hot air flows in the pipes in the same direction as the outside air that enters into the nacelle. 10. Aircraft nacelle according to claim 6, wherein the hot air intake is connected to pipes so that the hot air flows into the pipes in counter-current relative to the outside air that enters into the nacelle. 11. Coating for acoustic treatment according to claim 3, wherein the alveolar structure (30) comprises grooves (40) on the surface that can be flattened against the acoustically resistive structure (28), and the shapes of said grooves are adapted to those of the pipes. 12. Aircraft nacelle according to claim 7, wherein the acoustically restive structure comprises perforations to deliver the air that is used for defrosting. 13. Aircraft nacelle according to claim 7, wherein the hot air intake is connected to pipes so that the hot air flows in the pipes in the same direction as the outside air that enters into the nacelle. 14. Aircraft nacelle according to claim 8, wherein the hot air intake is connected to pipes so that the hot air flows in the pipes in the same direction as the outside air that enters into the nacelle. 15. Aircraft nacelle according to claim 7, wherein the hot air intake is connected to pipes so that the hot air flows into the pipes in counter-current relative to the outside air that enters into the nacelle. 16. Aircraft nacelle according to claim 8, wherein the hot air intake is connected to pipes so that the hot air flows into the pipes in counter-current relative to the outside air that enters into the nacelle.
이 특허에 인용된 특허 (4)
-
Cook Leonard J. (Canoga Park CA) Rosenthal Herman A. (San Diego CA), Aircraft anti-icing plenum.
-
Parente Charles A., Combined acoustic and anti-ice engine inlet liner.
-
Tindell Runyon H. ; Parente Charles A., Low drag inlet design using injected duct flow.
-
Porte, Alain, Process for de-icing by forced circulation of a fluid, an air intake cowling of a reaction motor and device for practicing the same.
이 특허를 인용한 특허 (3)
-
Chelin, Frederic; Menier, Christophe; Thomy, Jean Yves; Bertin, Etienne; Surply, Thierry; Haro, Dominique; Gantie, Fabrice, Method for making a network of drainage pipes and acoustic processing panel including such a network of drainage pipes.
-
Hurlin, Herve; Caruel, Pierre, Method of manufacturing a sound absorbing panel.
-
Porte, Alain; Albet, Grégory; Ring, Guillaume; Galletti, Pascal, Panel for the acoustic treatment comprising hot air ducts and at least one stabilization chamber.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.