AIRCRAFT ENGINE MASTS COMPRISING A MOVABLE SET OF COWLS

Abstract

AIRCRAFT ENGINE PISTON COMPRISING A MOVABLE ASSEMBLY OF COWLS The invention relates to an aircraft (10) engine piston (100) comprising a rear part (303), two rear cowls (204) around the rear part (203), where each rear cowl (204) comprises an upper fixed cowl (204a) and a lower movable cowl (204b) mounted hinged on the rear part (303) where in the closed position, the two lower movable cowls (204b) are brought together, so that their lower edges (312) are joined, where in the open position, the two lower movable cowls (204b) are tilted so that their lower edges (312) are moved away from each other, for each lower movable cowl (204b), a hinge system (320) fixed between the lower movable cowl (204b) and the rear part (303), and at least one locking system (330) which locks the two lower movable covers (204b) together in the closed position.The presence of the lower movable covers ensures, among other things, easy access to the interior of the reactor mast. Fig. 5.

Description

Title of the invention: AIRCRAFT ENGINE MAST COMPRISING A MOVABLE SET OF COWLS Technical field

[0001] The present invention relates to an aircraft engine pylon comprising a movable set of cowls allowing access to the interior of the engine pylon, an aircraft comprising a turbojet engine, a wing, and such an engine pylon for fixing the turbojet engine under the wing, as well as such a movable set of cowls. STATE OF THE PRIOR ART

[0002] An aircraft conventionally comprises a reactor, for example a turbojet, which is fixed under a wing of the aircraft using a reactor mast. The reactor mast consists of a rigid structure which is fixed, on the one hand, to a structure of the wing and, on the other hand, to a structure of the reactor. The reactor mast allows the transmission of the forces generated by the reactor to the structure of the wing, when the reactor is in operation. The reactor mast also allows the passage of systems between the wing and the reactor, such as for example the electrical system, the hydraulic system, pneumatic system etc.

[0003] To limit the drag of the engine pylon, it is covered with an aerodynamic cowling consisting of a set of cowls. The cowls are positioned next to each other to create the smoothest possible surface and are attached either to the structure of the engine pylon or to the structure of the aircraft wing.

[0004] To access the interior of the reactor mast, removable hatches are provided on some of these covers. The hatches are fixed by screw elements or rivets and, after removal, a technician can access the interior of the reactor mast and thus ensure maintenance of the elements present.

[0005] Fixing the cowls requires the presence of a relatively rigid and therefore heavy structure. In addition, due to manufacturing and assembly tolerances, the juxtaposition of several cowls next to each other cannot be done without the appearance of spaces and misalignments between these cowls. These spaces and misalignments can lead to a disturbance of the air flow and the appearance of acoustic phenomena. Finally, the removal of the hatches does not allow easy access to the interior of the engine mast and their presence requires the installation of local structural reinforcement elements. Statement of the invention

[0006] An object of the present invention is thus to provide a reactor mast comprising a movable set of covers. Such a movable set of covers makes it possible to open the reactor mast for easy access to the rear area of the reactor mast and to the systems located therein. included, in particular for maintenance and inspection tasks and to the structure supporting this mobile set of covers which is simplified compared to a structure of the state of the art. In addition, this mobile set of covers can be produced in a reduced number of two covers, distributed on either side of a vertical plane passing through the longitudinal axis of the engine, to reduce disturbances to the air flow and the occurrence of acoustic phenomena.

[0007] For this purpose, a reactor mast of an aircraft is proposed, said reactor mast comprising:

[0008] - a support structure comprising a front part and a rear part and intended to fix between them a reactor and a wing of said aircraft,

[0009] - a front aerodynamic cowling formed from a set of front cowls where the front aerodynamic cowling is attached around the front part of the engine pylon support structure,

[0010] - a rear aerodynamic cowling formed from a set of two rear cowls which are arranged around the rear part of the engine pylon support structure, where each rear cowl takes the form of a triangle with an upper edge intended to run along the wing, a lower edge of which runs along the lower part of the rear part and a front edge of which connects the other two edges to the front of the rear part, where each rear cowl comprises an upper fixed cowl secured to the rear part and a lower movable cowl mounted so as to be hinged on the rear part between an open position and a closed position, where the upper fixed cowl and the lower movable cowl are separated by a separation line generally parallel to the upper edge, where in the closed position, the two lower movable cowls are brought together and towards the rear part so that the lower edges of the two lower movable cowls are joined, where in the open position,the two lower movable covers are tilted so that the lower edges of the two lower movable covers are moved away from each other, ,

[0011] - for each lower movable hood, a hinge system fixed between the hood lower mobile and the rear part, and

[0012] - at least one locking system which locks the two movable hoods in inferior to each other in the closed position.

[0013] The presence of the lower movable covers ensures, among other things, easy access to the interior of the reactor mast.

[0014] Advantageously, the articulation of each lower movable cover is a rotation around an axis of rotation which is generally parallel to the separation line and in the vicinity of the separation line.

[0015] Advantageously, each hinge system comprises at least two fixed fittings secured to the rear part and, for each fixed fitting, a movable swan-neck fitting secured to the lower movable cover.

[0016] Advantageously, the locking system comprises, for each lower movable cover, a boss secured to said lower movable cover and a housing made in the rear part and designed to receive the boss in the closed position, and the locking system comprises a connecting pin which is fixed through a bore which each boss has for this purpose.

[0017] Advantageously, each lower movable cover is made up of a single component.

[0018] The invention also proposes an aircraft comprising a wing, a reactor and a reactor mast according to one of the preceding variants, fixed between the wing and the reactor.

[0019] The invention also provides a rear aerodynamic cowling of a reactor pylon according to one of the preceding variants, where the rear aerodynamic cowling comprises a set of two rear cowls which are intended to be arranged around a rear part of a support structure of the reactor pylon, where each rear cowl takes the form of a triangle of which an upper edge is intended to run along a wing, of which a lower edge is intended to follow along a lower part of the rear part and of which a front edge connects the other two edges to the front of the rear part, where each rear cowl comprises an upper fixed cowl intended to be integral with the rear part and a lower movable cowl intended to be mounted articulated on the rear part between an open position and a closed position, where the upper fixed cowl and the lower movable cowl are separated by a separation line generally parallel to the upper edge,where in the closed position, the two lower movable covers are brought together and towards the rear part so that the lower edges of the two lower movable covers are joined, where in the open position, the two lower movable covers are tilted so that the lower edges of the two lower movable covers are moved away from each other. Brief description of the drawings

[0020] The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the attached drawings, among which:

[0021] [Fig-1] is a side view of an aircraft according to the invention,

[0022] [Fig.2] is a side view of a propulsion unit comprising a reactor mast according to the invention,

[0023] [Fig.3] is a perspective view of a rear aerodynamic cowling of the mast reactor according to the invention with the movable cowls shown in the closed position,

[0024] [Fig.4] is a sectional view along line IV-IV of [Fig.3] at the level of a movable hood locking system, and

[0025] [Fig.5] is a perspective view of the rear aerodynamic cowling of the engine pylon according to the invention with the movable covers shown in the open position.

[0026] DETAILED DESCRIPTION OF EMBODIMENTS

[0027] [Fig.l] shows an aircraft 10 which comprises a reactor 14, for example a turbojet, and a wing 12 under which the reactor 14 is fixed by means of a reactor mast 100 according to the invention.

[0028] In the following description, the terms relating to a position are taken with reference to an aircraft 10 in normal flight position, that is to say as it is shown in [Fig.l] and the “front” and “rear” positions are taken with respect to the front and rear of the reactor 100 and with respect to the direction of advance F of the aircraft 10 when the reactor 100 is operating.

[0029] In the following description, and by convention, X is the longitudinal direction of the reactor 100 which is parallel to the longitudinal axis of said turbojet, Y is the transverse direction which is horizontal when the aircraft 10 is on the ground, and Z is the vertical direction which is vertical when the aircraft 10 is on the ground, these three directions X, Y and Z being orthogonal to each other.

[0030] [Fig.2] shows the wing 12 and the reactor 14 fixed to each other by means of the reactor mast 100 which comprises an aerodynamic cowling 200 comprising a front aerodynamic cowling 201 formed by a set of front cowls 202, 203 and a rear aerodynamic cowling 199 formed by two rear cowls 204.

[0031] In the embodiment of the invention presented here, the front cover assembly comprises a front cover 202 and an intermediate cover 203 disposed to the rear of the front cover 202, but in another embodiment, the front cover 202 and the intermediate cover 203 may constitute a single cover.

[0032] The rear cowls 204 are arranged at the rear, in the extension along the longitudinal direction of said turbojet 100, of the set of front cowls 202, 203.

[0033] Here, the rear cowls 204 are arranged under the wing 12 and at the rear of the reactor 14 and the front cowl 202 is arranged above the reactor 14 and at the front of the wing 12. The intermediate cowl 203 forms the junction between the front cowl 202 and the rear cowl 204. There is an intermediate cowl 203, a front cowl 202 and a rear cowl 204 on each side of the reactor mast 100.

[0034] [Fig.3] shows the engine mast 100 in the closed position of the rear cowls 204 and [Fig.5] shows the engine mast 100 in the open position of the rear cowls 204. It is not obligatory to have both rear cowls 204 open simultaneously.

[0035] The reactor mast 100 comprises a rigid structure, also called primary structure intended to fix between them a structure of the reactor 14 and a structure of the wing 12.

[0036] In addition, the reactor mast 100 comprises a support structure 302 serving as support for the aerodynamic cowling 200. The support structure 302 comprises a front portion (not shown) and a rear portion 303 visible in Figs. 3 to 5.

[0037] The front aerodynamic cowling 201, i.e. the set of front cowls comprising the intermediate cowls 203 and the front cowls 202, is fixed around the front part of the support structure 302.

[0038] The rear covers 204 are fixed around the rear part 303 of the support structure 302 which is itself fixed to the structure of the wing 12 using any suitable means known to those skilled in the art.

[0039] The rear part 303 generally takes the form of a triangular prism whose two triangular bases are in planes perpendicular to the longitudinal direction X, of which an upper triangular face is oriented upwards and is positioned opposite the wing 12 to be fixed there and of which the other two faces are arranged to port and starboard and meet towards the bottom.

[0040] The upper triangular face of the prism constitutes an upper spar 305 whose upper face ensures the junction with the wing 12.

[0041] In the embodiment of the invention shown in Figs. 3 and 5, the upper spar 305 has at its lateral peripheries dropped edges 309 extending downwards as well as transverse stiffeners 307 extending in the transverse direction Y.

[0042] Each triangular base here constitutes a rib 304, 306, but there may be more ribs arranged one behind the other parallel to the longitudinal direction X depending on the desired rigidity and the longitudinal extent of the rear part 303. Each rib 304, 306 thus takes the shape of a triangle, a lower point of which is oriented downwards and a base of which is oriented upwards, that is to say towards the wing 12. Here, each transverse stiffener 307 is positioned in line with a rib 304, 306 and the base of the rib 304, 306 ensures the junction with the transverse stiffener 307 of the upper spar 305.

[0043] The frame also comprises a column 308 which extends along the lower edge of the triangular prism, that is to say here the lower tip of each rib 304, 306. The column 308 is integral with the lower tip of each rib 304, 306 and extends generally parallel to the longitudinal direction X.

[0044] Towards the rear of the engine mast 100, the column 308 rises towards the wing 12.

[0045] Each rear cover 204 takes the form of a triangle with an upper edge 310 runs along the wing 12, a lower edge 312 of which follows the column 308, that is to say along the lower part of the rear part 303 and a front edge 314 of which connects the other two edges 310 and 312 to the front of the rear part 303.

[0046] Each rear cover 204 comprises an upper fixed cover 204a and a lower movable cover 204b separated by a separation line 316 which is generally parallel to the upper edge 310. Each rear cover 204 is thus divided by the separation line 316 between an upper fixed cover 204a which extends along the wing 12 between the separation line 316 and the upper edge 310, a lower movable cover 204b which extends between the separation line 316 and the lower edge 312.

[0047] The upper fixed covers 204a are integral with the rear part 303, and more particularly here with the fallen edges 309 of the upper spar 305 of the rear part 303.

[0048] Each lower movable hood 204b is mounted articulated on the rear part 303, and more particularly here on the upper side member 305 between an open position ([Fig.5]) and a closed position ([Fig.3]) and the articulation is a rotation around an axis of rotation 50.

[0049] In the closed position, the two lower movable cowls 204b are brought closer to each other and to the rear part 303 so that the lower edges 312 of the two lower movable cowls 204b are joined and constitute the trailing edge of the engine pylon 100.

[0050] In the open position, the two lower movable cowls 204b are tilted so that the lower edges 312 of the two lower movable cowls 204b are moved away from each other and so as to open a space allowing access to the interior of the engine mast 100.

[0051] To move from the closed position to the open position, each lower movable cowl 204b lifts towards the outside of the engine mast 100.

[0052] To this end, for each lower movable cowl 204b, the engine mast 100 comprises a hinge system 320 fixed between the lower movable cowl 204b and the rear part 303 and ensuring the articulation between the lower movable cowl 204b and the rear part 303, and more particularly here between the upper spar 305 and the lower movable cowl 204b. There are therefore two hinge systems 320, one per side.

[0053] Each hinge system 320 comprises at least two fixed fittings 323 secured to the upper spar 305, and more generally to the rear part 303, and, for each fixed fitting 323, a movable swan-neck fitting 322 secured to the lower movable cover 204b and allowing ample clearance during rotation while remaining invisible from the outside.

[0054] In the embodiment of the invention shown in Figs. 3 and 5, each movable fitting 322 is positioned opposite a fixed fitting 323 to form a system of yokes having a common alignment of bores to form the axis of rotation 50 of the hinge system 320.

[0055] This axis of rotation 50 is generally parallel to the separation line 316 and in the vicinity of the separation line 316.

[0056] The reactor mast 100 also comprises at least one locking system 330 which locks the two lower movable covers 204b together in the closed position.

[0057] Such a reactor mast 100 with lower movable cowls 204b has a simple, lightweight structure and easy access.

[0058] In the embodiment of the invention presented, there are two locking systems 330 distributed along the lower edges 312. Of course, a different number is possible depending on the length of the lower edge 312 to be locked.

[0059] The locking system 330 comprises, for each lower movable cover 204b, a boss 332 secured to said lower movable cover 204b and a housing 334 made in the rear part 303, here the column 308, and designed to receive the boss 332 in the closed position and thus provide a centering system for correctly positioning the lower movable cover 204b in the closed position.

[0060] The locking system 330 also comprises a connecting pin 336 which is fixed through a bore 335 that each boss 332 has for this purpose. Such a locking system 330 has the advantage of being hidden and it therefore does not disturb the flow of air along the lower movable covers 204b. The connecting pin takes for example the form of a connecting screw.

[0061] The connecting axis 336 comprises a screw 336a with a threaded rod and a head having a recess allowing the screw 336a to be screwed and unscrewed with a suitable tool. In the embodiment of the invention presented here, the head is a hexagon socket head.

[0062] The connecting shaft 336 comprises a nut 336b taking the form of a shouldered, blind nut, and also with a recess allowing the screwing and unscrewing of the nut 336b with a suitable tool. In the embodiment of the invention presented here, the nut 336b is also a hexagonal socket.

[0063] In one embodiment and with the aim of limiting disturbances to the aerodynamic flow, the two ends of the connecting axis 336 could be covered with a plug or a hardening paste such as, for example, mastic.

[0064] Advantageously, each lower movable cover 204b is made up of a single component, for example made by molding, thus limiting the presence of a junction zone that could disturb the air flow. Each rear cover 204 has a single separation line 316 which extends generally parallel to the air flow in flight.

Claims

Claims

1. Engine pylon (100) of an aircraft (10), said engine pylon (100) comprising: - a support structure (302) comprising a front part and a rear part (303) and intended to fix between them a reactor (14) and a wing (12) of said aircraft (10), - a front aerodynamic cowling (201) formed from a set of front cowls (202, 203) where the front aerodynamic cowling (201) is fixed around the front part of the support structure (302) of the engine pylon, - a rear aerodynamic cowling (199) formed by a set of two rear cowls (204) which are arranged around the rear part (203) of the support structure (302) of the engine pylon, where each rear cowl (204) takes the shape of a triangle of which an upper edge (310) is intended to run along the wing (12), of which a lower edge (312) follows along the lower part of the rear part (303) and of which a front edge (314) connects the other two edges (310, 312) to the front of the rear part (303), where each rear cowl (204) comprises an upper fixed cowl (204a) secured to the rear part (203) and a lower movable cowl (204b) mounted hinged on the rear part (303) between an open position and a closed position, where the upper fixed cowl (204a) and the lower movable cowl (204b) are separated by a dividing line (316) generally parallel to the upper edge (310), where in the closed position,the two lower movable covers (204b) are brought together and towards the rear part (303) so that the lower edges (312) of the two lower movable covers (204b) are joined, where in the open position, the two lower movable covers (204b) are tilted so that the lower edges (312) of the two lower movable covers (204b) are moved away from each other, - for each lower movable cover (204b), a hinge system (320) fixed between the lower movable cover (204b) and the rear part (303), and, - at least one locking system (330) which locks the two lower movable covers (204b) together in the closed position and which comprises, for each lower movable cover (204b), a boss (332) integral with said lower movable cover (204b) and a housing (334) made in the rear part (303) and designed to receive the boss (332) in the closed position, and the locking system (330) comprises a connecting pin (336) which is fixed through a bore (335) which each boss (332) has for this purpose.

2. Reactor mast (100) according to claim 1, characterized in that the articulation of each lower movable cowl (204b) is a rotation around an axis of rotation (50) which is generally parallel to the separation line (316) and in the vicinity of the separation line (316).

3. Reactor mast (100) according to one of claims 1 or 2, characterized in that each hinge system (320) comprises at least two fixed fittings (323) secured to the rear part (303) and, for each fixed fitting (323), a movable swan-neck fitting (322) secured to the lower movable cowl (204b).

4. Reactor mast (100) according to one of claims 1 to 3, characterized in that each lower movable cowl (204b) consists of a single component.

5. Aircraft (10) comprising a wing (12), a reactor (14) and a reactor mast (100) according to one of the preceding claims, fixed between the wing (12) and the reactor (14).

6. Rear aerodynamic cowling (199) of a reactor mast (100) according to one of claims 1 to 4, characterized in that the rear aerodynamic cowling (199) comprises a set of two rear cowls (204) which are intended to be arranged around a rear part (203) of a support structure (302) of the reactor mast (100), where each rear cowl (204) takes the form of a triangle of which an upper edge (310) is intended to run along a wing (12), of which a lower edge (312) is intended to follow along a lower part of the rear part (303) and of which a front edge (314) connects the other two edges (310, 312) to the front of the rear part (303), where each rear cowl (204) comprises an upper fixed cowl (204a) intended to be integral with the rear part (303) and a lower movable cover (204b) intended to be mounted articulated on the rear part (303) between an open position and a closed position,where the upper fixed cover (204a) and the lower movable cover (204b) are separated by a separation line (316) generally parallel to the upper edge (310), where in the closed position, the two lower movable covers (204b) are brought closer to each other and to the rear part (303) so that the lower edges of the two lower movable covers (204b) are contiguous, where in the open position, the two lower movable covers (204b) are tilted, such that the lower edges (312) of the two lower movable covers (204b) are spaced apart from each other.

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