System for reducing the installation noise of an aeroplane wing

Patent metadata

Field	Value
Publication number	US-11292575-B2
Application number	US-201615737505-A
Country	US
Kind code	B2
Filing date	Jun 17, 2016
Priority date	Jun 19, 2015
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

In the field of aeronautics, there is disclosed an aircraft with reduced installation noise and specifically an aircraft wing and jet engine system including an aircraft wing and at least one jet engine with high bypass ratio attached to the wing, suitable for emitting a jet intercepted by a first portion of the trailing edge of the wing. The range formed by the set of angles with orientation α defined by a vector following the direction of the jet and by a vector following the tangent at a point of the first portion of the trailing edge and oriented towards the wing tip of the wing, is included within a range of angles selected from the range delimited by 5° and 65°, and the range delimited by 115° and 175°.

First claim

The invention claimed is:

1. A device comprising:
an aircraft wing;
at least one jet engine ( 3 ) with high bypass ratio attached to said wing ( 2 ), suitable for emitting a jet ( 4 ) intercepted exclusively by a first portion ( 5 ) of a trailing edge of said wing, wherein angles with orientation α 3 are defined by a vector following a direction ( 11 ) of the jet ( 4 ) and by a vector following a tangent at a point of the first portion ( 5 ) of the trailing edge ( 6 ) and oriented towards the wing tip of said wing, and angles with orientation γ 2 are defined by a vector following the direction ( 11 ) of the jet and a vector following a tangent at a point of the trailing edge not belonging to the first portion ( 5 ) of the trailing edge and oriented towards the wing tip of the wing, wherein:
a range formed by a set of angles with orientation α 3 , is included within a range of angles selected from a range delimited by 5° and 65°;
an average over a length of said trailing edge ( 6 ) of the angles with orientation γ 2 is at least 10° greater than the average of the angles α 3 of each said first portion ( 5 ) of the trailing edge when α 3 is included within the range delimited by 5° and 65°.

2. The device according to claim 1 wherein at least one said first portion ( 5 ) of the trailing edge ( 6 ) is linear, said angle α 3 is constant and included within a range of angles selected from the range delimited by 5° and 65°.

3. The device according to claim 1 wherein said wing ( 2 ) comprises at least one fixed main portion ( 10 ) of which a portion ( 8 ) of a rear longitudinal edge is suitable for intercepting said jet ( 4 ), and wherein a range formed by the set of angles with orientation α 6 ′ defined by a vector following the direction ( 11 ) of said jet and a vector following the tangent at each point of said portion ( 8 ) of the rear longitudinal edge and oriented towards the wing tip of said wing ( 2 ), is included within the range of angles selected from the range delimited by 5° and 65°.

4. The device according to claim 3 wherein each said angle α 6 ′ is included within the range delimited by 5° and 65° and wherein an average over the length of said rear longitudinal edge of angles with orientation γ 4 ′ formed by a vector following the direction ( 11 ) of a said jet and a vector following the tangent at a point of said rear longitudinal edge not belonging to each said portion ( 8 ) of the rear longitudinal edge and oriented towards the wing tip of said wing, is at least 10° greater than the average of the angles α 6 ′ of each said portion ( 5 ) of the rear longitudinal edge.

5. The device according to claim 1 wherein the ratio of the distance r between the main axis of the jet engine ( 3 ) and the wing ( 2 ), to the diameter D of said jet at the exit of said jet engine is less than 2.

6. The device according to claim 1 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.3 Mach and 0.9 Mach.

7. An aircraft comprising at least two devices according to claim 1 .

8. The device according to claim 2 wherein said wing ( 2 ) comprises at least one fixed main portion ( 10 ) of which a portion ( 8 ) of the rear longitudinal edge is suitable for intercepting said jet ( 4 ), and wherein the range formed by the set of angles with orientation α 6 ′ defined by a vector following the direction ( 11 ) of said jet and a vector following the tangent at each point of said portion ( 8 ) of the rear longitudinal edge and oriented towards the wing tip of said wing ( 2 ), is included within a range of angles selected from the range delimited by 5° and 65°.

9. The device of claim 5 , wherein the ratio of the distance r between the main axis of the jet engine ( 3 ) and the wing ( 2 ), to the diameter D of said jet at the exit of said jet engine is less than 1.5.

10. The device according to claim 2 wherein the ratio of the distance r between the main axis of the jet engine ( 3 ) and the wing ( 2 ), to the diameter D of said jet at the exit of said jet engine is less than 2.

11. The device according to claim 3 wherein the ratio of the distance r between the main axis of the jet engine ( 3 ) and the wing ( 2 ), to the diameter D of said jet at the exit of said jet engine is less than 2.

12. The device according to claim 4 wherein the ratio of the distance r between the main axis of the jet engine ( 3 ) and the wing ( 2 ), to the diameter D of said jet at the exit of said jet engine is less than 2.

13. The device according to claim 6 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.6 Mach and 0.8 Mach.

14. The device according to claim 2 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.3 Mach and 0.9 Mach.

15. The device according to claim 3 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.3 Mach and 0.9 Mach.

16. The device according to claim 4 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.3 Mach and 0.9 Mach.

17. The device according to claim 5 wherein the maximum velocity of the gas flow at the exit of said jet engine ( 3 ) is between 0.3 Mach and 0.9 Mach.

18. The device according to claim 1 wherein at least one said first portion ( 5 ) of the trailing edge ( 6 ) is linear, said angle α 3 is constant and included within a range of angles selected from the range delimited by 40° and 65°.

Assignees

• Centre Nat Rech Scient

Inventors

• Jordan Peter
• Cavalieri Andre
• Wolf William
• Piantanida Selene
• Jaunet Vincent
• Huber Jerome

Classifications

• B64D27/18

  within, or attached to, wings · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64C3/14 Primary

  Aerofoil profile · CPC title

• B64C2003/147

  comprising trailing edges of particular shape · CPC title