REMOVABLE CLOSURE MEMBER FOR A FEMALE PORTION RECEIVED IN AN EXTERNAL OPENING OF AN AIRCRAFT ENGINE NACELLE

Abstract

A removable closure member is configured to close a female portion received in an external opening formed in the external surface of a nacelle for an aircraft engine. The female portion includes at least one air inlet opening. The closure member includes a base that forms the external contour of the member and that extends beyond the external opening of the nacelle so as to move into abutment against the external surface of the nacelle. The closure member further includes at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the air inlet opening.

Claims

1. A removable closure member configured to close a female portion received in an external opening made in an external surface of a nacelle for an aircraft engine, said female portion comprising at least one opening that opens into the nacelle, wherein said closure member comprises a base forming an external contour of said member and configured to extend beyond the external opening of the nacelle so as to move into abutment against the external surface of said nacelle and at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the opening of the female portion.

2. The closure member according to claim 1, further comprising a gripping means extending from the base that projects towards the exterior, on the side opposite to the position retention member.

3. The closure member according to claim 1, further comprising a core made of foam surrounded by a layer of elastomer.

4. The closure member according to claim 1, further comprising two inclined portions each configured to cooperate with a fin of the female portion, the retention member of said closure member being configured to cooperate with at least one of the openings of said female portion.

5. The closure member according to claim 4, wherein the base of said closure member comprises a first portion extending according to a direction normal to the inclined portions and connected to said inclined portions.

6. The closure member according to claim 5, wherein the first portion forms an axis of symmetry of the closure member.

7. The closure member according to claim 5, further comprising two lateral portions extending on either side of the first portion and configured to cooperate with portions of fins of the female portion, each of the lateral portions comprising a plurality of inclined portions.

8. The closure member according to claim 7, wherein each of the lateral portions comprises two inclined portions of ends and at least one central inclined portion, the retention member comprising two end studs configured to each cooperate with an end opening of the female portion and at least one central stud configured to cooperate with a central opening of said female portion.

9. The closure member according to claim 8, wherein at least the studs of ends each comprise a lip that projects from a free end of said stud and extends towards an end inclined of the female portion.

10. The closure member according to claim 1, wherein the position retention member comprises a stud that projects from the base towards the female portion and includes a lip that projects from a free end of said stud and is configured to be inserted into the opening of said female portion.

11. A nacelle for an aircraft engine comprising an external surface including at least one external opening configured to receive a female portion and comprising at least one closure member according to claim 4 and configured to temporarily close said female portion.

12. The nacelle according to claim 11, wherein the female portion is an air ventilation member comprising a fastening portion fastened onto the nacelle, at least two ventilation fins connected to the fastening portion and evacuation openings made between two adjacent fins, the air evacuation member being configured to be closed by the at least one first closure member.

13. The nacelle according to claim 11, wherein the female portion is an air inlet member comprising a fastening portion fastened onto the nacelle, a bottom connected on one side to the fastening portion and a rigid wall connected to a second side of the fastening portion and defining with said bottom an air inlet opening, the air inlet member being configured to be closed by a closure member according to claim 10.

14. The nacelle according to claim 13, comprising at least one first opening, a ventilation member received in said first opening and configured to be temporarily closed by a first closure member, at least one second opening and an air inlet member received in said second opening and configured to be temporarily closed by a second closure member.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Other goals, features and advantages of the invention will appear upon reading the following description, given only as a non-limiting example, and made in reference to the indexed drawings in which:

[0052] FIG. 1 very schematically illustrates a perspective view of a nacelle for an aircraft engine comprising closure members according to two embodiments of the invention;

[0053] FIG. 2

[0054] FIG. 3 show a closure member according to a first embodiment, respectively before and after installation in an external opening of the nacelle of FIG. 1;

[0055] FIG. 4 is a cross-sectional view of the closure member of FIG. 3;

[0056] FIG. 5A

[0057] FIG. 5B are views of details of the closure member of FIG. 4;

[0058] FIG. 6 is a cross-sectional view of the closure member of FIG. 3 according to a cutting plane passing through a central portion;

[0059] FIG. 7

[0060] FIG. 8 show a closure member according to a second embodiment, respectively before and after installation in an external opening of the nacelle of FIG. 1; and

[0061] FIG. 9 is a cross-sectional view of the closure member of FIG. 8.

DETAILED DISCLOSURE OF AT LEAST ONE EMBODIMENT

[0062] FIG. 1 very schematically shows a nacelle 10 for an aircraft engine 2 intended to be connected to the fuselage 4 of an aircraft 6. For reasons of clarity, only the fan of the engine 2 is visible in FIG. 1.

[0063] The nacelle 10 is defined axially by a leading edge 12 and a trailing edge 14, opposite to said leading edge 12, and radially by an external surface 16 and an internal surface 18. In a non-limiting manner, the external surface 16 illustrated is a surface of revolution.

[0064] The leading and trailing edges 12, 14 comprise an opening 12a, 14a, respectively, for the inlet of air and the outlet of the exhaust gases of the engine 2.

[0065] As illustrated in FIG. 1, the nacelle 10 comprises a first opening 16a made in the thickness of the nacelle 10 and opening onto the external surface 16 of said nacelle 10. As illustrated, the first opening 16a is located on a lower portion of the external surface 16 of the nacelle 10. Alternatively, it is possible for the nacelle to comprise a number of first openings greater than one, for example greater than or equal to two. It is also possible for the first opening to be located at a location of the nacelle other than its lower portion.

[0066] The first opening 16a is intended to receive a ventilation member or ventilation grid 20.

[0067] The ventilation grid 20 is visible in details in FIGS. 4 and 6. The ventilation grid 20 is made of a rigid material.

[0068] The ventilation grid 20 comprises a fastening portion 22 fastened onto the nacelle 10, for example here against the internal surface 18 of said nacelle by fastening elements 22a, such as, for example, rivets. Alternatively, the fastening portion 22 could be integrated into the nacelle 10.

[0069] The fastening portion 22 forms a contour of the ventilation grid 20.

[0070] The ventilation grid 20 further comprises a central portion 24, forming an axis of symmetry of said ventilation grid 22 and two portions of fins 26 located on either side of the central portion 24 and each comprising a plurality of ventilation fins 26a, 26b connected to the central portion 24.

[0071] As illustrated in FIG. 4, each portion of fins 26 comprises two end fins 26a and two central fins 26b. Alternatively, there could be a different number of central fins 26b. The fins 26a, 26b form walls inclined according to the same direction and the same angle of inclination.

[0072] Alternatively, there could be walls 26a, 26b inclined according to different angles of inclination.

[0073] The ventilation grid 20 further comprises evacuation openings 28a, 28b made between two adjacent fins.

[0074] More specifically, the grid 20 comprises two end evacuation openings 28a made respectively between the fastening portion 22 and a first end fin 26a and between a second end fin 26a and an adjacent central fin.

[0075] The evacuation openings 28a, 28b open inside the nacelle 10 in order to evacuate air from the engine 2 towards the exterior.

[0076] A removable first closure member 30 is configured to temporarily close the first external opening 16a, for example during a prolonged stoppage of the aircraft on the ground.

[0077] The first closure member 30 is illustrated in details in FIGS. 2 to 6.

[0078] The first closure member 30 comprises a base 31 forming the external contour of said member and a handle 32 extending as a projection from the base 31. The base 31 extends beyond the external opening 16a of the nacelle 10 so as to move into abutment against the external surface 16 of said nacelle.

[0079] The base 31 comprises a first portion 33 and two lateral portions 34 extending on either side of the first portion 33. As illustrated, the first portion 33 extends according to a direction substantially normal to the lateral portions 34 and is connected to said lateral portions 34.

[0080] In a manner that is in no way limiting, the first portion 33 is central and forms an axis of symmetry of the closure member 30.

[0081] The lateral portions 34 are configured to cooperate with the portions of fins 26 of the ventilation grid 20.

[0082] Each of the lateral portions 34 comprises a plurality of inclined portions 34a, 34b each intended to cooperate with a fin 26a, 26b of the ventilation grid 20.

[0083] As illustrated, each lateral portion 34 comprises two inclined portions of ends 34a and two central inclined portions 34b. Alternatively, there could be a different number of central inclined portions 34b. The inclined portions 34a, 34b are inclined according to the same direction and the same angle of inclination.

[0084] Alternatively, there could be portions 34a, 34b inclined according to different angles of inclination.

[0085] Each of the lateral portions 34 further comprises studs 36a, 36b that project from the base 31 towards the ventilation grid 20 and are configured to be inserted into a corresponding evacuation opening 28a, 28b of the ventilation grid 20.

[0086] More specifically, each of the lateral portions 34 comprises two end studs 36a and two central studs 36b, the number of central studs being dependent on the number of central fins 26b.

[0087] The end studs 36a respectively connect the base 31 to a first inclined end portion 34a and the second inclined end portion 34a to an adjacent inclined central portion 36b.

[0088] The studs of ends 36a each comprise a lip 36c or projection that projects from the free end of said stud and extends towards an end inclined fin 26a of the ventilation grid 20.

[0089] The lips 36c are configured to resiliently deform during the installation of the closure member 30 on the ventilation grid 20 and be inserted under the associated fin 26a and thus retain the closure member in place.

[0090] In this case, the lip 36c of the stud is deformed by contact with a rigid inclined wall of the ventilation grid and snaps onto said rigid inclined wall, in the corresponding evacuation opening.

[0091] The end studs 36a, the lips 36c of which grab hold in a rigid wall 26a of the ventilation grid 20, allow to ensure the immobilization of the first closure member 30.

[0092] Alternatively, it is possible for each of the studs 36a,36b to comprise a resiliently deformable lip configured to cooperate with a fin of the ventilation grid 20.

[0093] The first closure member 30 is installed only by a pressure stress of the latter on the ventilation grid 20, resiliently deforming the lip 36c of the corresponding stud 36a.

[0094] The first closure member 30 is symmetrical with respect to its first portion 33.

[0095] As illustrated in details in FIG. 6, the first closure member 30 is a one-piece part made of a composite material from a core 30a made of foam coated with a projected elastomer layer 30b. The core 30a made of foam is, for example, made by injection or extrusion, machined, printed in three dimensions or made by any other means for making a foam.

[0096] As illustrated in FIG. 6, the handle 32 comprises the core 30a made of foam surrounded by the layer 30b of projected elastomer forming the base 31. The base 31 is made in the same phase of projection of elastomer onto a template made via additive manufacturing.

[0097] The layer 30b of elastomer can be, for example, polyurethane.

[0098] In a manner that is in no way limiting, the first closure member 30 comprises an extraction tab 37 fastened to the handle and allowing the unclipping of the closure member from the ventilation grid during an external traction stress on said tab.

[0099] As illustrated in FIG. 1, the nacelle 10 comprises two second openings 16b made in the thickness of the nacelle 10, in particular but not exclusively on its upper portion, and opening onto the external surface 16 of said nacelle 10. Alternatively, it is possible for the nacelle to comprise a number of second openings different than two, for example equal to one, or for example greater than or equal to three. It is also possible for the second openings to be located at a location of the nacelle other than its upper portion.

[0100] Each second opening 16b is intended to receive an air inlet opening or scoop 40 called ventilation scoop.

[0101] The scoop 40 is visible in details in FIGS. 7 and 9. The scoop 40 is made of a rigid material.

[0102] The scoop 40 comprises a fastening portion 42 fastened against the internal surface 18 of the nacelle 10 by fastening elements 42a, such as, for example, rivets.

[0103] The fastening portion 42 forms a contour of the scoop 40.

[0104] The scoop 40 further comprises a bottom 44 connected on one side to the fastening portion 42 and a rigid wall 46 connected to a second side of the fastening portion 42 and defining with said bottom 44 an air inlet opening 48 opening inside the nacelle 10 in order to transport cool air towards the engine 2.

[0105] The rigid wall 46 extends beyond the opening 16b of the nacelle 10.

[0106] Each removable second closure member 50 is configured to temporarily close one of the second external openings 16b, for example during a prolonged stoppage of the aircraft on the ground.

[0107] The second closure member 50 is illustrated in details in FIGS. 7 to 9.

[0108] The second closure member 50 comprises a base 51 forming the external contour of said member and a gripping means, such as a handle 52 extending as a projection from the base 51. The base 51 extends beyond the external opening 16b of the nacelle 10 so as to move into abutment against the external surface 16 of said nacelle.

[0109] The base 51 further comprises a stud 56 that projects from the base 51 towards the scoop 40.

[0110] The stud 56 comprises a lip 56a or projection that projects from the free end of said stud and is configured to be inserted into the air inlet opening 48 of the scoop 40.

[0111] The stud 56 is configured to resiliently deform during the installation of the second closure member 50 on the scoop 40 and its lip 56a is inserted under the rigid wall 46 into the air inlet opening 48 and thus retains in place said closure member 50.

[0112] In other words, the lip 56a of the stud 56 is deformed by contact with a rigid wall of the scoop 40 and snaps onto said rigid wall, in the corresponding air inlet opening.

[0113] The resiliently deformable lip grabs hold in a rigid wall 46 of the scoop 40 allowing to ensure the immobilization of the second closure member 50.

[0114] The second closure member 50 is installed by inserting the stud into the opening of the scoop 40, resiliently deforming its lip 56a.

[0115] The second closure member 50 is symmetrical with respect to its handle 52.

[0116] As illustrated in details in FIG. 9, the second closure member 50 is a one-piece part made of a composite material from a core 50a made of foam coated with a projected elastomer layer 50b. The core 50a made of foam is, for example, made by injection or extrusion, machined, printed in three dimensions or made by any other means for making a foam.

[0117] As illustrated in FIG. 9, the handle 52 comprises the core 50a made of foam surrounded by the layer 50b of projected elastomer forming the base 51. The base 51 is made in the same phase of projection of elastomer onto a template made via additive manufacturing.

[0118] The layer 50b of elastomer can be, for example, polyurethane.

[0119] In a manner that is in no way limiting, the second closure member 50 comprises an extraction tab 57 fastened to the handle and allowing the unclipping of the closure member from the scoop during an external traction stress on said tab.

[0120] In general, the ventilation grid 20 and the scoop 40 form female portions respectively received in an external opening 16a, 16b made on the external surface 16 of revolution of the nacelle 10. The closure members of the female portions 30, 50 must be removed before the phase of flight of the aircraft, in order to leave all of the external openings open.

[0121] In general, the stud(s) of the closure members are resiliently deformable position retention members configured to ensure the retaining in position of the closure member in the associated female portion.

[0122] Via the closure members described, the risk of injury is significantly reduced via the reduction of the weight and via the absence of a projecting rigid part on said member.

[0123] The nacelle is no longer damaged during the installation of the closure member in the associated female portion.

[0124] The closure member is a one-piece part, which considerably reduces the number of parts and the manufacturing time of said member, engendering a significant reduction in the manufacturing and maintenance cost.

[0125] The use of a flexible composite material for the closure member allows to adapt to the dimensional variations of the interfaces.