Assembly for an aircraft nacelle comprising a support panel, a thermal protection element and a fastening system

Abstract

The present invention relates to an assembly comprising a support panel (208) with an internally fixed structure, a thermal protection element (210), and a plurality of fastening systems (212). Each fastening system (212) comprises: a recess (302) fixed to the support panel (208), the recess having a rounded shoulder (304) therein; and a protrusion (306) comprising a sleeve (308) pierced through a main hole, a slider (310) movable within the main hole, and a plurality of balls (314), wherein for each ball (314), the sleeve (308) has a secondary hole (316), and each ball (314) is movable along said secondary hole (316) between a locked position and an unlocked position, and wherein the slider (310) is movable between a blocked position and a non-blocked position. Such an assembly enables the thermal protection element to be fastened to the support panel in a simple and quick manner, and also allows for easy removal if necessary.

Description

Technical Field

[0001] This invention relates to an assembly for an aircraft engine nacelle, comprising a support panel, a thermal protection element, and a fastening system for securing the thermal protection element to the support panel. The invention also relates to an aircraft engine nacelle including at least one such assembly, and to an aircraft including at least one such nacelle. Background Technology

[0002] Aircraft typically include at least one turbofan engine, which forms the core housed in a nacelle. The nacelle includes an internal fixed structure (IFS) surrounding the engine and an outer fairing arranged around the internal fixed structure.

[0003] The internal structure and the external fairing define a secondary duct between them, in which the secondary airflow from the air intake located at the front of the nacelle circulates, while the main airflow circulates in the engine.

[0004] Because of its proximity to the engine, the internal structure is subjected to extremely high temperatures, so thermal protection components need to be secured there. Summary of the Invention

[0005] One object of the present invention is to provide an assembly for an aircraft engine nacelle, the assembly comprising a support panel such as a panel of an internal structure, a thermal protection element, and a fastening system for fastening the thermal protection element to the support panel, wherein fastening is achieved in a simple and quick manner.

[0006] To address this, a component is proposed, comprising:

[0007] - The support panel of the internal fixed structure of the turbofan engine nacelle;

[0008] - A thermal protection element that contacts the support panel at its contact surface; and

[0009] - Multiple fastening systems that removably fasten the thermal protection element to the support panel;

[0010] For each fastening system, the thermal protection element has a hole through it;

[0011] Each fastening system includes:

[0012] - A recess, which is received in a corresponding hole, and has a base and a cylindrical wall, the base being fixed to a support panel, the cylindrical wall defining a free and open space in a direction away from the support panel, wherein the cylindrical wall has a rounded shoulder projecting toward the interior of the cylindrical wall; and

[0013] - A protrusion comprising a sleeve inserted into a cylindrical wall and piercing a main hole, a slider movable within the main hole, and a plurality of balls, wherein, for each ball, the sleeve has a secondary hole perpendicular to the main hole, the secondary hole opening into the main hole on a first side and opening to the outside of the sleeve on a second side, wherein each ball is placed in a corresponding secondary hole and is movable along the secondary hole between a locked position and an unlocked position, in the locked position the ball protrudes on the second side, and in the unlocked position the ball does not protrude on the second side. In the embodiment, for each sphere, the slider includes a hemispherical cavity, and the slider is translatably movable between a blocking position and a non-blocking position. In the blocking position, the slider is positioned such that the cavity is not opposite to the sphere and the sphere is forced into a locked position. In the non-blocking position, the slider is positioned such that the cavity is opposite to the sphere, thereby allowing the sphere to enter an unlocked position. The protrusion includes a cover fixed to the sleeve, the cover bearing a surface abutting against a thermal protection element on a side opposite to the contact surface.

[0014] Such components allow for the simple and quick fastening of the thermal protection element to the support panel, and also allow for easy removal if needed.

[0015] Advantageously, passage from the blocking position to the non-blocking position of the slider includes: pressing down the slider in the sleeve, the slider carrying the stop, and the sleeve having a chamber in which the stop moves, the face of the chamber forming a counter-stop, the stop bearing against the counter-stop in the blocking position, and the slider having an end extending beyond the cover in the blocking position, an orifice passing through the end, and a locking device inserted into the orifice.

[0016] According to a specific embodiment, for each recess, the assembly includes a cylindrical washer that fits snugly into the recess to fill the space between the support panel and the thermal protection element at the hole.

[0017] According to a specific embodiment, for each recess, the assembly includes a loop positioned along the edge of the corresponding hole of the thermal protection element, the loop fitting tightly onto the corresponding cylindrical wall and bearing against the base.

[0018] According to a specific embodiment, each protrusion is fixed to a thermal protection element.

[0019] According to a specific embodiment, for each recess, the assembly includes a cylindrical washer that fits tightly into the recess to fill the space between the support panel and the thermal protection element at the hole. The thermal protection element includes a support plate bonded to the face of its orientation against the cover, and the cover is fastened to the grommets and the support plate.

[0020] According to a specific embodiment, the thermal protection element includes a support plate bonded to the face of its orientation against the cover, and the cover is fastened to the support plate.

[0021] Advantageously, the protrusion includes a return mechanism for pushing the slider into the locked position.

[0022] The present invention also proposes a nacelle for a turbofan engine, the nacelle comprising an internal fixed structure and an assembly according to one of the aforementioned variations, wherein the support panel is a panel of the internal fixed structure.

[0023] The present invention also proposes an aircraft comprising at least one nacelle according to the aforementioned variant. Attached Figure Description

[0024] The above and other features of the invention will become more apparent from the following description of exemplary embodiments given with reference to the accompanying drawings, in which:

[0025] Figure 1 This is a side view of the aircraft according to the present invention;

[0026] Figure 2 This is a perspective view of a portion of the nacelle according to the present invention;

[0027] Figure 3 This is a cross-sectional view of the components according to the first embodiment of the present invention in the assembled position;

[0028] Figure 4 It is similar to Figure 3 The view is in the unlocked position;

[0029] Figure 5 It is similar to Figure 3 The view shows the disassembly position;

[0030] Figure 6 This is similar to the second embodiment of the present invention. Figure 3 The view;

[0031] Figure 7 This is similar to the third embodiment of the present invention. Figure 3 The view;

[0032] Figure 8 This is similar to the fourth embodiment of the present invention. Figure 3 The view;

[0033] Figure 9 It is similar to the variant of this invention. Figure 3 The view;

[0034] Figure 10 It is a sectional view based on the recess of the first variant; and

[0035] Figure 11 It is a cross-sectional view based on the concave portion of the second variant. Detailed Implementation

[0036] In the following description, terms related to location are referenced. Figure 1 The direction in which the aircraft is moving forward is indicated by arrow 107.

[0037] Figure 1 An aircraft 10 with a fuselage 12 is shown, with wings 14 fastened to each side of the fuselage. Each wing 14 carries at least one turbofan engine 16, which is supported by a pylon 18 that secures the turbofan engine 16 to the underside of the wing 14.

[0038] In the following description, and by convention, X denotes the longitudinal axis of the turbofan engine 16, which is parallel to the longitudinal axis of the aircraft 10 and oriented positively toward the front of the aircraft 10; Y denotes the lateral axis, which is horizontal when the aircraft 10 is on the ground; and Z denotes the vertical axis when the aircraft 10 is on the ground. These three axes X, Y and Z are orthogonal to each other.

[0039] The turbofan engine 16 includes a nacelle 100 and an engine forming the core, which is housed within the nacelle 100. The nacelle conventionally includes two modules fastened to pylons 18 on either side of a vertical midplane XZ.

[0040] Figure 2 The module 200 of the nacelle 100 is shown schematically. The module 200 includes, in particular, an internal fixed structure (IFS) 202 surrounding the engine and an outer fairing 204 arranged around the internal fixed structure 202.

[0041] The internal structure 202 and the outer fairing 204 define a secondary duct 206 between them, in which a secondary airflow from an air intake located at the front of the nacelle 100 circulates.

[0042] The internal structure 202 includes, in particular, a support panel 208 that surrounds the engine and withstands high temperatures. In the context of this invention, the support panel 208 is protected by a thermal protection element 210.

[0043] In the embodiments of the invention presented herein, a single thermal protection element 210 is shown, but multiple such thermal protection elements 210 are fastened to cover the surface of the support panel 208 to be protected.

[0044] Each thermal protection element 210 takes the form of an additional panel, which is fastened to a support panel 208 by means of multiple fastening systems 212 and is made of thermally insulating material.

[0045] Figures 3 to 5The first embodiment of the invention is shown in various assembly positions. The thermal protection element 210 and the support panel 208 contact each other at the contact surface 209.

[0046] The fastening system 212 includes a recess (female part) 302, which in this case is a portion that exhibits rotational symmetry about an axis of rotation perpendicular to the support panel 208, and has a cylindrical wall 252 defining free space and a base 250 fixed to the support panel 208 and the cylindrical wall 252. The cylindrical wall 252 exhibits rotational symmetry about the axis of rotation and has an opening oriented in a direction away from the support panel 208. The cylindrical wall 252 has a circular shoulder 304 inside it about the axis of rotation, which protrudes toward the interior of the cylindrical wall 252.

[0047] As will be explained below, the shoulder 304 is configured to allow the sphere to be positioned behind the opening relative to the shoulder 304. Therefore, the shoulder 304 is a certain distance from the bottom of the recess 302 corresponding to the base 250.

[0048] In order to allow each recess 302 to be placed in place, the thermal protection element 210 has a hole 307 passing through it parallel to the axis of rotation.

[0049] The fastening system 212 includes a male part 306, which in this case also exhibits rotational symmetry about the axis of rotation.

[0050] The protrusion 306 includes a sleeve 308 that inserts into the recess 302, and more specifically, into the free space defined by the cylindrical wall 252, to secure the thermal protection element 210 to the support panel 208. The sleeve 308 is pierced by a main bore 254 coaxial with the axis of rotation, and the protrusion 306 includes a slider 310 movable within the main bore 254. The protrusion 306 also includes a cap 312 secured to the sleeve 308 and supporting the face of the thermal protection element 210 on the opposite side of the contact surface 209.

[0051] The protrusion 306 also includes a plurality of spheres 314 distributed at an angle around the axis of rotation.

[0052] For each ball 314, the sleeve 308 has a secondary hole 316 perpendicular to the main hole 254, opening into the main hole 254 on a first side and opening to the outside of the sleeve 308 on a second side. Each ball 314 is placed in the corresponding secondary hole 316 and thus can be in a locked position along the secondary hole 316. Figure 3 ) and unlock location ( Figure 4 and Figure 5The ball 314 moves between the two sides. In the locked position, the ball 314 protrudes on the second side and thus protrudes relative to the sleeve 308. In the unlocked position, the ball 314 does not protrude on the second side and thus retracts into the sleeve 308.

[0053] To prevent the ball 314 on the second side from being lost, the diameter of the secondary hole 316 on the second side is smaller than the diameter of the ball 314, while still ensuring that a portion of the ball 314 can leave the sleeve 308.

[0054] For each sphere 314, the slider 310 includes a hemispherical cavity 318 recessed into the slider 310.

[0055] The slider 310 can translate between a blocked position and a non-blocked position. In the blocked position ( Figure 3 In the position where the cavity 318 is not opposite the ball 314, the slider 310 is positioned such that the cavity 318 is not opposite the ball 314. Then, the ball 314 abuts against the slider 310, thereby forcing the ball 314 into the locked position, while in the non-blocking position... Figure 4 and Figure 5 In the process, the slider 310 is positioned such that the cavity 318 is opposite the ball 314, thereby allowing the ball 314 to enter the unlocked position.

[0056] The principle of positioning the fastening system 212 includes placing the thermal protection element 210 against the support panel 208 when the recess 302 is in the hole 307.

[0057] When the slider 310 is in the unblocked position and the ball 314 is in the unlocked position, the protrusion 306 moves toward the recess 302. Figure 5 The sleeve 308 is introduced through the opening in the cylindrical wall 252 until the sphere 314 is below the shoulder 304. Figure 4 Finally, the slider 310 moves to the blocking position. Figure 3 This forces the ball 314 into a locked position below the shoulder 304, thereby preventing the protrusion 306 from moving.

[0058] In this case, passage from the unblocked position to the blocked position is achieved by retracting the slider 310 to a limited extent on the side of the cover 312.

[0059] Meanwhile, the cover 312 carries the face of the thermal protection element 210 on the opposite side of the contact surface 209, thereby securing the thermal protection element 210 to the support panel 208 by clamping the thermal protection element 210 between the cover 312 and the support panel 208.

[0060] Conversely, the removal includes removal from both the locked position and the blocking position. Figure 5To begin, move slider 310 (in this case, press it down) to the non-blocking position. Figure 4 This releases the sphere 314, which has freely entered the unlocked position, and then retracts the protrusion 306 by pulling it. Figure 5 ).

[0061] Therefore, the installation and removal of thermal protection components are relatively simple and quick.

[0062] The components constituting part of the nacelle 100 according to the invention thus include a support panel 208, a thermal protection element 210, and a plurality of fastening systems 212.

[0063] exist Figures 3 to 5 In one embodiment, the passage of the slider 310 from the blocked position to the non-blocked position includes pressing the slider 310 in the sleeve 308; conversely, the passage of the slider 310 from the non-blocked position to the blocked position includes the slider 310 leaving the sleeve 308 at the cover 312.

[0064] To prevent the slider 310 from leaving the blocking position, the slider 310 carries the stop 320, and the sleeve 308 has a chamber in which the stop 320 moves. One face of the chamber forms an anti-stop 322, and the stop 320 carries against the anti-stop 322 in the blocking position.

[0065] To prevent the slider 310 from being undesirably pressed down, the slider 310 has an end extending beyond the cover 312 in the blocked position, through which an opening 324 passes, into which a locking device 326, such as a pin, is inserted. Access to the unblocked position then requires the locking device 326 to be retracted beforehand.

[0066] exist Figures 3 to 5 In one embodiment, the assembly further includes a cylindrical washer 328 with a central hole to allow a tight fit on the recess 302, particularly on the cylindrical wall 252, to fill the space between the support panel 208 and the thermal protection element 210 at the hole 307. The washer 328 is made of a thermally insulating material. In this case, the washer 328 takes the form of a truncated cone with a central hole.

[0067] exist Figure 6 In the second embodiment of the invention shown, for each recess 302, the assembly includes a grommet 602 positioned along the edge of the corresponding hole 307 of the thermal protection element 210. The grommet 602 fits snugly onto the corresponding cylindrical wall 252 and bears bearing against the base 250. The grommet 602 includes two flanges arranged on both sides of the thermal protection element 210 and a cylinder securely connecting the two flanges.

[0068] exist Figure 7 The third embodiment of the present invention shown is... Figure 8 In the fourth embodiment of the invention shown, each protrusion 306 is fixed to the thermal protection element 210. In this case, a secure attachment is achieved by means of rivets 706.

[0069] exist Figure 7 In the third embodiment of the invention shown, for each recess 302, the assembly includes a loop 702 positioned along the edge of the corresponding central hole of the washer 328. As described above, the loop 702 fits snugly onto the corresponding cylindrical wall 252 and bears abutment against the base 250.

[0070] In addition, the thermal protection element 210 includes a metal plate type support plate 704 on its face oriented to abut the cover 312, which is bonded to the face.

[0071] The cover 312 is fastened to the cable ring 702 and the support plate 704.

[0072] In the embodiment of the invention shown here, the thermal protection element 210 includes another support plate 708 of the metal plate type on its face oriented to abut against the support panel 208, which is bonded to the face.

[0073] exist Figure 8 In the fourth embodiment of the present invention shown, the thermal protection element 210 includes a metal plate type support plate 804 bonded to the face of its orientation against the cover 312, and the cover 312 is fastened to the support plate 804.

[0074] In the embodiment of the invention shown here, the thermal protection element 210 includes another support plate 808 of the metal plate type on its face oriented to abut against the support panel 208, which is bonded to the face.

[0075] exist Figure 9 In the illustrated variant of the invention, the protrusion 306 includes a return device 902, in this case a helical spring, which pushes the slider 310 into a blocking position. The return device 902 also facilitates the disengagement of the slider 310.

[0076] In the embodiment of the invention shown here, the return device 902 is housed in a chamber that carries the anti-stop 322 and is constrained between the wall of the chamber and an element of the slider 310, in this case, the stud 904.

[0077] Although the return device 902 is shown on a particular component, it is applicable to the various embodiments described above.

[0078] The cover 312 also includes a retaining hole 906, which allows the locking device 326 to be attached when it is not received in the opening 324, thereby preventing its loss and allowing the locking device 326 to be used to pull the cover 312.

[0079] Although the retaining hole 906 is shown on a particular component, it is applicable to the various embodiments described above.

[0080] exist Figures 3 to 9 In one embodiment, the recess 302 is a one-piece component made of a single material, such as metal or composite material.

[0081] Figure 10 and Figure 11 Two variant embodiments of the recess 302 are shown, in which the cylindrical wall 252 and shoulder 304 are implemented by a metal insert 1002, while the base 250 is implemented by a base 1004 made of composite material.

[0082] exist Figure 10 In one embodiment, the base 1004 is molded around the insert 1002 to ensure the insert 1002 is securely fastened.

[0083] exist Figure 11 In one embodiment, the insert 1002 has a collar portion 1006 that extends to the outside of the insert 1002 and is embedded in the base 1004 to ensure the fastening of the insert 1002.

[0084] In each of the above embodiments, the base 250 is secured, for example, by bonding to the composite panel 208.

Claims

1. Components, including: - Support panel (208) of the internal fixed structure (202) of the nacelle (100) of the turbofan engine (106); - A thermal protection element (210) that contacts the support panel (208) at a contact surface (209); as well as - Multiple fastening systems (212) that removably fasten the thermal protection element (210) to the support panel (208); In each of the fastening systems (212), the thermal protection element (210) has a hole (307) passing through it; Each of the fastening systems (212) includes: - A recess (302) received in a corresponding hole (307) and having a base (250) and a cylindrical wall (252), the base being fixed to the support panel (208), the cylindrical wall defining a free and open space in a direction away from the support panel (208), wherein the cylindrical wall (252) has a rounded shoulder (304) projecting toward the interior of the cylindrical wall (252); and - A protrusion (306) comprising a sleeve (308) inserted into the cylindrical wall (252) and pierced by a main hole (254), a slider (310) translatably movable within the main hole (254), and a plurality of spheres (314), wherein, for each sphere (314), the sleeve (308) has a secondary hole (316) perpendicular to the main hole (254), the secondary hole leading to the main hole (254) on a first side and to the outside of the sleeve (308) on a second side, wherein each sphere (314) is placed in a corresponding secondary hole (316) and is translatably movable along the secondary hole (316) between a locked position and an unlocked position, wherein, in the locked position, the sphere (314) protrudes on the second side, and in the unlocked position, the sphere (314) does not protrude on the second side, wherein For each of the spheres (314), the slider (310) includes a hemispherical cavity (318), and wherein the slider (310) is translatably movable between a blocking position and a non-blocking position, in which the slider (310) is positioned such that the cavity (318) is not opposite to the sphere (314) and the sphere (314) is forced into the locking position, and in the non-blocking position, the slider (310) is positioned such that the cavity (318) is opposite to the sphere (314) thereby allowing the sphere (314) to enter the unlocking position, and wherein the protrusion (306) includes a cover (312) fixed to the sleeve (308), the cover bearing a face of the thermal protection element (210) on a side opposite to the contact surface (209).

2. The assembly of claim 1, wherein, The passage of the slider (310) from the blocked position to the unblocked position includes: pressing down the slider (310) in the sleeve (308), wherein the slider (310) carries a stop (320), and the sleeve (308) has a chamber in which the stop (320) moves, the face of the chamber forming a counter-stop (322), the stop (320) bearing abutment against the counter-stop in the blocked position, and wherein the slider (310) has an end in the blocked position extending beyond the cover (312), an orifice (324) passing through the end, and a locking device (326) inserted into the orifice.

3. The component according to claim 1, characterized in that, For each of the recesses (302), the assembly includes a cylindrical washer (328) that fits tightly onto the recess (302) to fill the space between the support panel (208) and the thermal protection element (210) at the hole (307).

4. The component according to claim 1, characterized in that, For each of the recesses (302), the assembly includes a loop (602) positioned along the edge of the corresponding hole (307) of the thermal protection element (210), the loop fitting tightly against the corresponding cylindrical wall (252) and bearing against the base (250).

5. The component according to claim 1, characterized in that, Each of the protrusions (306) is fixed to the thermal protection element (210).

6. The component according to claim 5, characterized in that, For each of the recesses (302), the assembly includes a cylindrical washer (328) that fits tightly onto the recess (302) to fill the space between the support panel (208) and the thermal protection element (210) at the hole (307), wherein the thermal protection element (210) includes a support plate (704) bonded to the face of its face oriented to abut against the cover (312), and wherein the cover (312) is fastened to the grommets (702) and the support plate (704).

7. The component according to claim 5, characterized in that, The thermal protection element (210) includes a support plate (804) bonded to the face of its orientation against the cover (312), wherein the cover (312) is fastened to the support plate (804).

8. The component according to claim 1, characterized in that, The protrusion (306) includes a return device (902) that pushes the slider (310) into the blocking position.

9. A nacelle (100) of a turbofan engine (106), the nacelle (100) comprising an internal fixing structure (202) and the assembly according to claim 1, wherein the support panel (208) is a panel of the internal fixing structure (202).

10. An aircraft (10) comprising at least one nacelle (100) according to claim 9.

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