Removable closure member for a concave portion received in an external opening of a nacelle of an aircraft engine

Abstract

A removable closure member (50) configured to close a concave portion (40) received in an external opening (16b) made in an external surface (16) of a nacelle (10) for an aircraft engine, the concave portion (40) comprising at least one air inlet opening (48). The closure member (50) comprises a base (51) forming the outer contour of the member and extending beyond the external opening (16b) of the nacelle (10) so as to be moved against the external surface (16) of the nacelle, and at least one elastically deformable position retaining member (56) protruding from the base (51) and configured to be inserted into the air inlet opening (48).

Description

Technical Field

[0001] This invention relates to the field of aircraft, and more particularly to the field of the fairing of an aircraft engine, known as a "nacelle".

[0002] More particularly, the present invention relates to a sealing member configured to close external openings of an aircraft engine, particularly external openings formed in the nacelle of an aircraft engine. Background Technology

[0003] The aircraft nacelle allows the engine to be connected to the aircraft fuselage, and also allows the engine's internal temperature to be controlled through one or more air inlet openings designed to cool the engine.

[0004] For this purpose, the nacelle includes one or more external openings, such as air inlet components or scoops (referred to as "ventilation scoops"), which are configured to bring cool air into certain areas of the engine, particularly areas with high temperatures, and the nacelle includes one or more ventilation components or ventilation grilles that allow hot air from the engine to be exhausted toward the outside of the nacelle in order to prevent hot spots from forming on engine components or to relieve potential overpressure in the engine.

[0005] During long-term parking of an aircraft, it is known to seal the external openings of the engine nacelles in order to protect these external openings from the intrusion of foreign objects such as dust, animals or plants.

[0006] The components used to close the external openings of the nacelle are placed in place using ground support equipment (GSE). Therefore, the interface between the closing components and the nacelle imposes design constraints on the ground support equipment.

[0007] In fact, the complex shape of the nacelle exerts very high control over the design and shape of the enclosure components, which requires the components to have very low manufacturing tolerances.

[0008] It is known that components used to seal air inlets or evacuation openings, which are complex, rigid mechanical parts, consist of metal plates drawn to conform to the shape of the opening to be sealed. The sealing plate is secured to the nacelle using metal fastening lugs projecting outwards from the nacelle. A disadvantage of this type of sealing plate is that it is particularly heavy and sensitive to impacts and drops, thus posing a danger to personnel moving around the aircraft, as well as to other vehicles or equipment on the ground.

[0009] Furthermore, the fastening lugs pose a danger to personnel moving around the aircraft because they are made of rigid metal and protrude relative to the enclosure. There is also a risk of damaging the nacelle while the fastening lugs are being fastened to it. The rigidity of this enclosure requires very low manufacturing tolerances to ensure its functionality. Summary of the Invention

[0010] Therefore, the objective of this invention is to overcome the disadvantages of the aforementioned sealing components and to propose a component for sealing the external opening of a nacelle for an aircraft engine, which is capable of adapting to geometric changes in the opening while ensuring better protection of the nacelle during the fastening of the sealing component to the nacelle, and better protection of personnel and / or physical components on the ground during the fall of the sealing component.

[0011] Therefore, the objective of this invention is to provide an easy and low-cost closure for the external opening of a nacelle for an aircraft engine.

[0012] Therefore, the object of the present invention is a removable closure member configured to close a female portion of an external opening, such as an air inlet or ventilation component, formed in the external surface of an aircraft engine nacelle. The female portion includes at least one opening leading to the nacelle.

[0013] The closure member includes a base that forms the outer contour of the member and is intended to extend beyond the outer opening of the nacelle to move into contact with the outer surface of the nacelle, and the closure member includes at least one elastically deformable position-holding member configured to insert into the opening of the concave portion.

[0014] The elastically deformable position-holding member allows for ensuring that the closed member remains in place within the associated concave portion.

[0015] Therefore, the closure member can adapt to geometric changes in the opening while ensuring better protection of the nacelle during fastening of the member to the nacelle, because fastening is performed by deformation of the deformable portion of the member.

[0016] The retaining component can protrude from the base.

[0017] A nacelle is a casing or fairing surrounding an aircraft engine and forming the propulsion assembly together with the engine. The engine can specifically be a turbojet engine or a turboprop engine.

[0018] Elastically deformable refers to any component that can be reversibly deformed under external stress and return to its initial shape when the stress is removed.

[0019] Advantageously, the closure member includes a gripping device that extends from an outwardly projecting base on the side opposite to the position-holding member. For example, the gripping device can be a handle, ring, loop, cord, or any other manipulating member capable of manipulating the closure member. For example, the closure member includes a core made of foam, surrounded by an elastomeric layer, for example, by protrusions.

[0020] Therefore, the low mass of the component reduces the risk of damage to personnel and / or physical structures on the ground during a fall. Furthermore, the enclosure is easy to manufacture and inexpensive.

[0021] According to one embodiment, the closure member includes two inclined portions, each inclined portion being designed to engage with a fin of a concave portion, and a retaining member of the closure member is configured to engage with at least one opening in the opening of the concave portion.

[0022] Advantageously, the base of the closing member includes at least one first portion that extends in a direction substantially perpendicular to the inclined portion and is connected to the inclined portion.

[0023] In a non-restrictive manner, the first part forms the axis of symmetry of the closed member.

[0024] Advantageously, the closure member includes two lateral portions that extend on both sides of the first portion and are configured to partially engage with the fins of the concave portion, each of the lateral portions including a plurality of inclined portions.

[0025] For example, each of these lateral portions includes two end-sloping portions and at least one central-sloping portion, the retaining member includes two end studs configured to engage with the end openings of the concave portion, and the retaining member includes at least one central stud configured to engage with the central opening of the concave portion.

[0026] At least each end post may include a lip that protrudes from the free end of the post and extends toward the end of the concave portion with inclined fins.

[0027] According to another embodiment, the position holding member includes a stud protruding from the base toward the concave portion, and includes a lip protruding from the free end of the stud and configured to be inserted into the opening of the concave portion.

[0028] According to a second aspect, the present invention relates to a nacelle for an aircraft engine, the nacelle comprising a rotatable outer surface including at least one external opening for receiving a concave portion, and including at least one closure member as defined above, configured to temporarily close the concave portion, for example, during an extended period of time when the aircraft remains on the ground. The closure member is intended to be removed prior to the flight phase of the aircraft.

[0029] External openings are formed within the thickness of the nacelle and lead to the outer surface of the nacelle.

[0030] According to one embodiment, the concave portion is a ventilation member or ventilation grille, comprising: a fastening portion fastened to a nacelle, the fastening portion being fastened to the nacelle abutting against an inner surface of the nacelle, for example by a fastening element (such as a rivet); at least two ventilation fins connected to the fastening portion; and an exhaust opening formed between two adjacent fins. The ventilation grille is configured to be closed by a first sealing member, the first sealing member comprising two inclined portions, each of the two inclined portions being designed to mate with a fin of the ventilation grille.

[0031] The retaining member of the first closing member is configured to engage with at least one discharge opening of the grille.

[0032] Advantageously, the ventilation grille includes: a portion, such as a central portion, forming an axis of symmetry of the ventilation grille; and two fin portions positioned on either side of the central portion, each fin portion including a plurality of ventilation fins connected to the central portion. The base of the first closure member includes a first portion, and two lateral portions extending on either side of the first portion and configured to engage with the fin portions of the ventilation grille, each of these lateral portions including a plurality of inclined portions, each inclined portion intended to engage with the fins of the ventilation grille.

[0033] For example, each fin portion includes two end fins, at least one central fin, two end discharge openings formed between the fastening portion and the first end fin, and between the second end fin and the adjacent central fin, respectively, and at least one discharge opening formed between the first end fin and the central fin. Each lateral portion of the first closure member includes two end inclined portions and at least one central inclined portion. The retaining member of the first closure member on the ventilation grille includes two end studs and at least one central stud, the two end studs being configured to engage with the end discharge openings respectively, and the at least one central stud being configured to engage with the central discharge opening.

[0034] Alternatively, there can be a different number of center fins. The fins form walls that are inclined in the same direction and at the same angle.

[0035] Alternatively, there can be walls that are tilted at different angles.

[0036] Ventilation openings are located inside the nacelle to direct air toward the engine.

[0037] The ventilation grille is made of rigid material.

[0038] Alternatively, there can be a different number of centrally inclined sections. The inclined sections are inclined in the same direction and at the same angle.

[0039] Alternatively, there can be sections that are tilted at different angles.

[0040] The end posts connect the base to the first inclined end portion and the second inclined end portion to the adjacent inclined center portion, respectively.

[0041] Advantageously, at least each end post includes a lip or protrusion that protrudes from the free end of the post and extends at an angle toward the end fin of the ventilation grille.

[0042] The lip of the closure member is configured to elastically deform during installation on the ventilation grille and to be inserted below the associated fins, thus holding the closure member in place.

[0043] According to another embodiment, the concave portion is an air inlet member or a spoon-shaped portion (referred to as a ventilation spoon-shaped portion), which includes: a fastening portion fastened to the nacelle, the fastening portion being fastened to the nacelle against the inner surface of the nacelle, for example by fastening elements (such as rivets); a bottom of the fastening portion connected on one side; and a rigid wall connected to a second side of the fastening portion and defining an air inlet opening together with the bottom.

[0044] The spoon-shaped portion is configured to be closed by a second sealing member. The base of the second sealing member also includes a stud that protrudes from the base toward the spoon-shaped portion and includes a lip or protrusion that protrudes from the free end of the stud and is configured to be inserted into the air inlet opening of the spoon-shaped portion.

[0045] The stud is configured to elastically deform during the mounting of the second sealing member onto the spoon-shaped portion, and the lip of the stud is inserted into the air inlet opening below the rigid wall, thus holding the sealing member in place.

[0046] The second sealing member is installed by inserting the stud into the opening of the spoon-shaped part, thereby causing the lip of the stud to deform elastically.

[0047] The air inlet opening is open inside the nacelle to direct air toward the engine.

[0048] The fastening part forms the outline of the spoon-shaped portion.

[0049] The rigid wall extends beyond the nacelle opening.

[0050] The spoon-shaped part is made of a rigid material.

[0051] For example, the nacelle includes at least one first opening, a ventilation member, at least one second opening, and an air inlet member, the ventilation member being received in the first opening and configured to be closed by a first sealing member, and the air inlet member being received in the second opening and configured to be closed by a second sealing member.

[0052] The first and second closing components are structurally different. Attached Figure Description

[0053] Other objects, features, and advantages of the invention will become apparent upon reading the following description, given only by way of non-limiting example and with reference to the accompanying drawings, in which:

[0054] Figure 1 A perspective view of a nacelle for an aircraft engine is shown in a very schematic manner, the nacelle including a closing member according to two embodiments of the present invention;

[0055] Figure 2 and Figure 3 The enclosure component according to the first embodiment is shown installed on... Figure 1 Before and after the external opening of the nacelle;

[0056] Figure 4 for Figure 3 A cross-sectional view of the closed component;

[0057] Figure 5A and Figure 5B for Figure 4 Detailed view of the closed component;

[0058] Figure 6 for Figure 3 The closed component is based on the cross-sectional view of the cutting plane passing through the central part;

[0059] Figure 7 and Figure 8 The enclosure component according to the second embodiment is shown installed on... Figure 1 Before and after the external opening of the nacelle; and

[0060] Figure 9 for Figure 8 A cross-sectional view of the closed component. Detailed Implementation

[0061] Figure 1The nacelle 10 for the aircraft engine 2 is shown schematically; this nacelle is intended to connect to the fuselage 4 of the aircraft 6. For clarity, only the fan of engine 2 is shown. Figure 1 As can be seen in the text.

[0062] The nacelle 10 is axially defined by a leading edge 12 and a trailing edge 14 opposite to the leading edge 12, and radially defined by an outer surface 16 and an inner surface 18. In a non-limiting manner, the outer surface 16 shown is a surface of revolution.

[0063] The leading edge 12 and the trailing edge 14 include openings 12a and 14a for the air inlet and exhaust outlet of the engine 2, respectively.

[0064] like Figure 1 As shown, the nacelle 10 includes a first opening 16a formed in the thickness of the nacelle 10 and leading to an outer surface 16 of the nacelle 10. As illustrated, the first opening 16a is located on the lower portion of the outer surface 16 of the nacelle 10. Alternatively, the nacelle may include a number of first openings, greater than one, for example, greater than or equal to two. The first openings may also be located at locations other than the lower portion of the nacelle.

[0065] The first opening 16a is intended to receive a ventilation component or ventilation grille 20.

[0066] Ventilation grille 20 Figure 4 and Figure 6 Details can be seen in the image. The ventilation grille 20 is made of a rigid material.

[0067] The ventilation grille 20 includes a fastening portion 22 fastened to the nacelle 10, which is fastened to the nacelle by, for example, fastening elements 22a (such as rivets) abutting against the inner surface 18 of the nacelle. Alternatively, the fastening portion 22 may be integrated into the nacelle 10.

[0068] The fastening part 22 forms the outline of the ventilation grille 20.

[0069] The ventilation grille 20 also includes a central portion 24 that forms the axis of symmetry of the ventilation grille 22, and the ventilation grille includes two fin portions 26 positioned on both sides of the central portion 24, each fin portion including a plurality of ventilation fins 26a, 26b connected to the central portion 24.

[0070] like Figure 4 As shown, each fin portion 26 includes two end fins 26a and two center fins 26b. Alternatively, there may be a different number of center fins 26b. The fins 26a and 26b form walls that are inclined in the same direction and at the same angle.

[0071] Alternatively, walls 26a and 26b may be inclined at different angles.

[0072] The ventilation grille 20 also includes discharge openings 28a, 28b formed between two adjacent fins.

[0073] More specifically, the ventilation grille 20 includes two end discharge openings 28a formed between the fastening portion 22 and the first end fin 26a, and between the second end fin 26a and the adjacent central fin.

[0074] Exhaust openings 28a and 28b are open inside the nacelle 10 to allow air to be exhausted from the engine 2 to the outside.

[0075] The removable first closure member 30 is configured to temporarily close the first external opening 16a, for example, to close the first external opening while the aircraft is stationary on the ground for an extended period of time.

[0076] The first closing member 30 is in Figures 2 to 6 It is shown in detail in the middle.

[0077] The first closure member 30 includes a base 31 forming the outer contour of the member and a handle 32 extending from the base 31 as a protrusion. The base 31 extends beyond the external opening 16a of the nacelle 10 so as to move against the outer surface 16 of the nacelle.

[0078] The base 31 includes a first portion 33 and two lateral portions 34 extending on both sides of the first portion 33. As shown, the first portion 33 extends in a direction substantially perpendicular to the lateral portions 34 and is connected to the lateral portions 34.

[0079] In a non-restrictive manner, the first part 33 is central and forms the axis of symmetry of the first closed member 30.

[0080] The lateral portion 34 is configured to partially engage with the fins 26 of the ventilation grille 20.

[0081] Each side portion 34 includes multiple inclined portions 34a, 34b, each inclined portion being designed to mate with the fins 26a, 26b of the ventilation grille 20.

[0082] As shown, each lateral portion 34 includes two end inclined portions 34a and two central inclined portions 34b. Alternatively, there may be a different number of central inclined portions 34b. The inclined portions 34a and 34b are inclined in the same direction and at the same angle.

[0083] Alternatively, there may be inclined portions 34a and 34b that are inclined at different angles.

[0084] Each of the lateral portions 34 also includes studs 36a, 36b that protrude from the base 31 toward the ventilation grille 20 and are configured to be inserted into corresponding exhaust openings 28a, 28b of the ventilation grille 20.

[0085] More specifically, each of the lateral portions 34 includes two end studs 36a and two central studs 36b, the number of which depends on the number of central fins 26b.

[0086] These end posts 36a respectively connect the base 31 to the first inclined end portion 34a and the second inclined end portion 34a to the adjacent central inclined portion 34b.

[0087] Each end post 36a includes a lip 36c or a protrusion that protrudes from the free end of the post and extends toward the end inclined fin 26a of the ventilation grille 20.

[0088] The lip 36c is configured to elastically deform during the mounting of the first closure member 30 onto the ventilation grille 20 and to be inserted below the associated fin 26a, thus holding the closure member in place.

[0089] In this case, the lip 36c of the stud deforms by contacting the rigid inclined wall of the ventilation grille and snaps into the rigid inclined wall in the corresponding discharge opening.

[0090] The end post 36a (the lip 36c of the end post grips the rigid wall 26a of the ventilation grille 20) allows the first closure member 30 to be fixed in place.

[0091] Alternatively, each of the studs 36a, 36b may include an elastically deformable lip configured to engage with the fins of the ventilation grille 20.

[0092] The first sealing member 30 is mounted on the ventilation grille 20 solely by its compressive stress, thereby causing the lip 36c of the corresponding stud 36a to deform elastically.

[0093] The first closing member 30 is symmetrical with respect to its first part 33.

[0094] like Figure 6 As shown in detail, the first enclosed member 30 is a one-piece component made of a composite material and formed from a core 30a, which is made of foam and coated with a protruding elastomer layer 30b. The foam core 30a is made, for example, by injection or extrusion, machining, 3D printing, or by any other means used to manufacture foam.

[0095] like Figure 6 As shown, the handle 32 includes a core 30a made of foam and surrounded by an elastomer layer 30b that protrudes to form a base 31. The base 31 is formed in the same stage where the elastomer protrudes onto a template made by additive manufacturing.

[0096] The elastomer layer 30b can be, for example, polyurethane.

[0097] In a non-limiting manner, the first closure member 30 includes an extraction tab 37 that is secured to the handle and allows the closure member to detach from the ventilation grille during external traction stress on the tab.

[0098] like Figure 1 As shown, the nacelle 10 includes two second openings 16b formed in the thickness of the nacelle 10, particularly but not only in the upper part of the nacelle, and leading to the outer surface 16 of the nacelle 10. Alternatively, the nacelle may include a number of second openings, which is not two, but for example equal to one, or for example greater than or equal to three.

[0099] The second opening can also be located in a position other than the upper part of the nacelle.

[0100] Each second opening 16b is designed to receive an air inlet opening or spoon-shaped portion 40, referred to as a ventilation spoon.

[0101] Spoon-shaped part 40 in Figure 7 and Figure 9 See details below. The spoon-shaped part 40 is made of a rigid material.

[0102] The spoon-shaped portion 40 includes a fastening portion 42, which is fastened to the inner surface 18 of the nacelle 10 by a fastening element 42a (such as a rivet).

[0103] The fastening portion 42 forms the outline of the spoon-shaped portion 40.

[0104] The spoon-shaped portion 40 also includes a bottom 44 connected to the fastening portion 42 on one side and a rigid wall 46 connected to a second side of the fastening portion 42, the rigid wall together with the bottom 44 defining an air inlet opening 48 in the interior opening of the nacelle 10 for delivering cold air toward 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 external openings of the second external opening 16b, for example, to close one of the external openings of the second external openings while the aircraft is stationary on the ground for an extended period of time.

[0107] The second closing member 50 is in Figures 7 to 9 It is shown in detail in the middle.

[0108] The second closure member 50 includes a base 51 and a gripping device, the base forming the outer contour of the member, the gripping device being, for example, a handle 52 extending from the base 51 as a protrusion. The base 51 extends beyond the external opening 16b of the nacelle 10 so as to move to abut against the external surface 16 of the nacelle.

[0109] The base 51 also includes a stud 56 that protrudes from the base 51 toward the spoon-shaped portion 40.

[0110] The stud 56 includes a lip 56a or protrusion that protrudes from the free end of the stud and is configured to be inserted into the air inlet opening 48 of the spoon-shaped portion 40.

[0111] The stud 56 is configured to elastically deform during the mounting of the second sealing member 50 onto the spoon-shaped portion 40, and the lip 56a of the stud is inserted into the air inlet opening 48 below the rigid wall 46, thus holding the second sealing member 50 in place.

[0112] In other words, the lip 56a of the stud 56 deforms by contacting the rigid wall of the spoon-shaped portion 40 and snaps into the rigid wall in the corresponding air inlet opening.

[0113] The elastically deformable lip grips the rigid wall 46 of the spoon-shaped portion 40, thereby allowing the second closing member 50 to remain fixed.

[0114] The second closing member 50 is installed by inserting the stud into the opening of the spoon-shaped part 40, thereby causing the lip 56a of the stud to deform elastically.

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

[0116] like Figure 9 As shown in detail, the second closure member 50 is a one-piece component made of a composite material and formed from a core 50a, which is made of foam and coated with a protruding elastomer layer 50b. The foam core 50a is made, for example, by injection or extrusion, machining, 3D printing, or by any other means used to manufacture foam.

[0117] like Figure 9 As shown, the handle 52 includes a core 50a made of foam and surrounded by an elastomer layer 50b that protrudes to form a base 51. The base 51 is formed in the same stage where the elastomer protrudes onto a template made by additive manufacturing.

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

[0119] In a non-limiting manner, the second closure member 50 includes an extraction tab 57 that is fastened to the handle and allows the closure member to disengage from the spoon-shaped portion during external traction stress on the tab.

[0120] Typically, the ventilation grille 20 and the spoon-shaped portion 40 form concave portions that are received in external openings 16a and 16b, respectively, which are formed on the rotating external surface 16 of the nacelle 10. The closure members 30 and 50 of the concave portions must be removed before the aircraft enters the flight phase to allow all external openings to open.

[0121] Typically, the closure member's studs are elastically deformable position-holding members configured to ensure that the closure member remains in place within the associated concave portion.

[0122] With the described enclosed component, the risk of damage is significantly reduced by the reduction in weight and by the absence of protruding rigid parts on the component.

[0123] The nacelle is no longer damaged during the installation of the enclosure component in the associated concave section.

[0124] The enclosed component is a one-piece part, which greatly reduces the number of parts and the manufacturing time of the component, thereby significantly reducing manufacturing and maintenance costs.

[0125] The use of flexible composite materials for enclosed components allows for adaptation to changes in interface dimensions.

Claims

1. A removable closing member (30, 50) configured to close a concave portion (20, 40) received in an external opening (16a, 16b) formed in an external surface (16) of a nacelle (10) for an aircraft engine (2), said concave portion (20, 40) comprising at least one opening (28a, 28b, 48) leading to said nacelle (10), characterized in that, The closing member (30, 50) comprises a base (31, 51) forming the outer profile of the member and intended to extend beyond the outer openings (16a, 16b) of the nacelle (10) so as to move into abutment against the outer surface (16) of the nacelle, and at least one elastically deformable position-keeping member projecting from the base (31, 51) and configured to be interposed into the openings (28a, 28b, 48) of the concave portion (20, 40).

2. Closing member (30, 50) according to claim 1, comprising a gripping device (32, 52) extending from the base (31, 51) projecting towards the outside on the side opposite the position-keeping member.

3. Closing member (30, 50) according to claim 1 or 2, comprising a core (30a, 50a) made of foam surrounded by an elastomer layer (30b, 50b).

4. Closing member (30) according to claim 1 or 2, comprising two inclined portions (34a, 34b) each intended to cooperate with a fin (26a, 26b) of the concave portion (20), the position-keeping member of the closing member (30) being configured to cooperate with at least one of the openings (28a, 28b) of the concave portion (20).

5. The closure member (30) according to claim 4, wherein The base (31) of the closing member (30) comprises a first portion (33) extending according to a direction substantially perpendicular to the inclined portions (34a, 34b) and connected to the inclined portions (34a, 34b).

6. The closure member (30) according to claim 5, wherein The first portion (33) forms an axis of symmetry of the closing member (30).

7. Closing member (30) according to claim 5 or 6, comprising two lateral portions (34) extending on either side of the first portion (33) and configured to cooperate with portions of fins (26) of the concave portion (20), each of the lateral portions (34) comprising a plurality of inclined portions (34a, 34b).

8. The closure member (30) according to claim 7, wherein Each of the lateral portions (34) comprises two end inclined portions (34a) and at least one central inclined portion (34b), the position-keeping member comprising two end pegs (36a) configured to each cooperate with an end opening (28a) of the concave portion (20) and at least one central peg (36b) configured to cooperate with a central opening (28b) of the concave portion (20).

9. The closure member (30) according to claim 8, wherein At least the end pegs (36a) each comprise a lip (36c) projecting from the free end of the peg and extending towards an end inclined fin (26a) of the concave portion (20).

10. The closure member (50) according to claim 1 or 2, wherein Said position-keeping member comprises a peg (56) protruding from said base (51) towards said concave portion (40) and comprising a lip (56a) protruding from a free end of said peg (56) and configured to be inserted into said opening (48) of said concave portion (40).

11. A nacelle (10) for an aircraft engine, said nacelle comprising an outer surface (16) comprising at least one outer opening (16a, 16b) intended to receive a concave portion (20, 40) and said nacelle comprising at least one closing member (30, 50) according to any one of claims 1 to 10, said closing member being configured to temporarily close said concave portion (20, 40).

12. The nacelle of claim 11, wherein, Said concave portion (20) is an air venting member comprising a fastening portion (22) fastened to said nacelle (10), at least two venting fins (26a, 26b) connected to said fastening portion (22) and a discharge opening (28a, 28b) formed between two adjacent fins, said air venting member being configured to be closed by a closing member (30) according to any one of claims 4 to 9.

13. The nacelle of claim 11, wherein, Said concave portion (40) is an air inlet member comprising a fastening portion (42) fastened to said nacelle (10), a bottom (44) connected to said fastening portion (42) on one side and a rigid wall (46) connected to a second side of said fastening portion (42), said rigid wall defining, with said bottom (44), an air inlet opening (48), said air inlet member (40) being configured to be closed by a closing member (50) according to claim 10.

14. The nacelle according to any one of claims 11 to 13, comprising at least one first opening (16a), a venting member (20) received in said first opening (16a) and configured to be temporarily closed by a first closing member (30), at least one second opening (16b) and an air inlet member (40) received in said second opening (16b) and configured to be temporarily closed by a second closing member (50).

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