Device that makes it possible to improve the effectiveness of the acoustic treatments in a pipe of an aircraft power plant
View Patent ↗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′ ).
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.