IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0440354
(2007-09-06)
|
등록번호 |
US-8167232
(2012-05-01)
|
우선권정보 |
FR-06 53606 (2006-09-07) |
국제출원번호 |
PCT/FR2007/051880
(2007-09-06)
|
§371/§102 date |
20090306
(20090306)
|
국제공개번호 |
WO2008/029062
(2008-03-13)
|
발명자
/ 주소 |
- Gantie, Fabrice
- Druon, Yann
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
16 |
초록
▼
A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe (36) into which a gas stream flows, whereby the pipe (36) is delimited by two approximately concentric inside walls (40) and outside walls (42), wherein the device includes at le
A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe (36) into which a gas stream flows, whereby the pipe (36) is delimited by two approximately concentric inside walls (40) and outside walls (42), wherein the device includes at least one partition (38, 38′) that extends over at least one portion of the length of the pipe (36) between the inside and outside walls (40, 42) and in that the profile of at least one wall (44, 46) of the at least one partition (38, 38′) is defined so as to increase the number of reflections of an acoustic beam on at least one of the inside and/or outside walls (40, 42) of the pipe and/or on at least one of the walls (44, 46) of the at least one partition (38, 38′).
대표청구항
▼
1. An aircraft nacelle comprising: a pipe (22, 36) into which a gas stream flows, whereby said pipe (22, 36) is delimited by two approximately concentric inside walls (40) and outside walls (42), covered at least partially by a coating whose purpose is to absorb a portion of sound energy,wherein at
1. An aircraft nacelle comprising: a pipe (22, 36) into which a gas stream flows, whereby said pipe (22, 36) is delimited by two approximately concentric inside walls (40) and outside walls (42), covered at least partially by a coating whose purpose is to absorb a portion of sound energy,wherein at least one partition (38, 38′) extends over at least one portion of a length of the pipe (22, 36) between said inside and outside walls (40, 42) and a profile of each of two walls (44, 46) of said at least one partition (38, 38′) comprises a convex portion, and on each side of said convex portion a concave portion oriented towards the inside wall of the pipe and a concave portion oriented towards the outside wall of the pipe to increase the number of reflections of an acoustic beam on the coating to absorb a portion of the sound energy. 2. The aircraft nacelle according to claim 1, wherein the two walls (44, 46) of the partition or the at least one junction (38, 38′) comprises an acoustic coating whose purpose is to absorb a portion of the sound energy. 3. The aircraft that comprises a nacelle according to claim 1. 4. The aircraft nacelle according to claim 1, wherein each of the two walls are opposite each other in a vertical axis of said at least one junction. 5. An aircraft nacelle comprising: a secondary pipe (36), into which a gas stream flows, whereby said pipe (36) is delimited by two approximately concentric inside walls (40) and outside walls (42), covered at least partially by a coating whose purpose is to absorb a portion of sound energy, and, at least one junction (38, 38′) that extends in a radial plane over at least a portion of a length of said pipe (36), wherein a profile of each of two walls (44, 46) of said at least one junction (38, 38′) comprises a convex portion, and on each side of said convex portion a concave portion oriented towards the inside wall of the pipe and a concave portion oriented towards the outside wall of the pipe to increase the number of reflections of an acoustic beam on the coating to absorb a portion of the sound energy. 6. The aircraft nacelle according to claim 5, wherein the two walls (44, 46) of a partition or the junction (38, 38′) comprises an acoustic coating whose purpose is to absorb a portion of the sound energy. 7. The aircraft that comprises a nacelle according to claim 5. 8. The aircraft nacelle according to claim 5, wherein the each of the two walls are opposite each other in a vertical axis of said at least one junction.
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