Cowl of an aircraft turbine engine comprising a central gripping interface

Abstract

The invention relates to a cowl (1) of an aircraft turbine engine extending about an axis (5) comprising a conical reinforcement (7) centred about the axis (5), an external skin (11) fixed around the reinforcement (7) and a revolution member (13) fixed to the conical reinforcement (7) along the axis (5) and against the external skin (11), the external skin (11) and the revolution member (13) each comprising a hole (14, 15) coaxial with the axis (5), the revolution member (13) being configured to allow the cowl (1) to be gripped by inserting a bar (17) into the hole (15).

Description

[0001] DESCRIPTION

[0002] TITLE: Cowl of an aircraft turbomachine comprising a central gripping interface

[0003] Technical field

[0004] The present invention relates to turbomachine inlet cowls as well as systems for handling such inlet cowls.

[0005] In particular, the present invention relates to means for attaching and fixing a hood to a handling system.

[0006] In general, the invention applies to any conical industrial part requiring lifting with tools, such as turbomachine covers or rear nozzle plugs.

[0007] Previous techniques

[0008] A turbomachine generally includes at the front an inlet cowl having a generally conical shape, the end of which may or may not be rounded.

[0009] The main function of the cowl is to cover the front of the turbomachine's drive shaft while guiding the air flow towards the drive blades of the turbomachine's fan.

[0010] The hood's secondary function is to withstand a bird strike and to provide anti-icing protection.

[0011] The hood is generally heavy, around 20 kg, conical in shape with a circular base, for example with a diameter of around one meter, and a tip which can be rounded.

[0012] The size and mass of the cowl are all the more important for applications in open, unducted engines, where the fan generally has a larger diameter than for ducted engines, and where the inlet cowl is then also more massive.

[0013] The hood usually includes connections, for example air, electrical or hydraulic, for example to perform its anti-icing function.

[0014] The cowl also rotates around its axis, particularly at the speed of the fan blades. All of these mass and design constraints require the use of suitable handling equipment, also known as GSE (Ground Support Equipment). In particular, the cowl must include an interface that facilitates its handling and / or transport for installation on a turbomachine.

[0015] For lifting and handling, it is possible to create interfaces on the hood in order to attach handling tools to it. The interfaces are generally positioned around the outer diameter of the hood. However, this is the part of the hood with the greatest aerodynamic impact, the highest inertia and the greatest impact on the unbalance, the hood being ideally as balanced as possible.

[0016] The hood must be able to rotate, especially during installation, in order to install it in the correct position and therefore requires, in this embodiment, to have numerous lifting interfaces, therefore more mass which could unbalance the hood.

[0017] Statement of the invention

[0018] The present invention therefore aims to overcome the aforementioned drawbacks and to provide a low-mass interface, which does not hinder the balance and aerodynamics of the hood by limiting the rotating masses, and which overcomes the constraints of the angular position of the hood.

[0019] The present invention relates to a cowl for an aircraft turbomachine, extending around an axis, and comprising a conical frame centered around the axis, an external skin fixed around the frame, the cowl further comprising a revolution element fixed to the conical frame along the axis and against the external skin, the external skin and the revolution element each comprising a hole coaxial with the axis, the revolution element being configured to allow the cowl to be gripped by inserting a bar into the holes.

[0020] Thus, the cowl allows operators equipped with suitable handling tools to carry out the transport, maintenance and installation of the cowl more simply, the element of revolution constituting a balanced handling interface with a single fixing point, minimizing mechanical stresses. In particular, no lifting interface is necessary on the outside diameter of the cowl, which contributes to better aerodynamics and an absence of imbalance. The cowl can also be rotated at any angle, unlike the prior art, where rotation is limited by the presence of a sling fixed to the outside diameter of the cowl. This is particularly useful following a shutdown of the turbomachine, in which case the cowl is in a random position and must be able to be gripped in any position. The element of revolution also serves as a reference element during the manufacture of the cowl.

[0021] Advantageously, the hole in the element of revolution passes through the element of revolution.

[0022] In one embodiment, the cowl is a turbomachine fan nose.

[0023] In a particular embodiment, the revolution element comprises a longitudinal locking means, preferably a thread oriented towards the hole.

[0024] In one embodiment, the hole comprises means configured to brake and / or immobilize in rotation around the axis the bar inserted in the hole.

[0025] Advantageously, the revolution element comprises an annular shoulder extending into the hole in the outer skin at the end of the hole in the revolution element.

[0026] Advantageously, the cover comprises a plurality of orifices around the hole, the orifices extending through the outer skin and into the revolution element.

[0027] The invention also relates to an assembly comprising a cover as defined above and a plug for closing the hole.

[0028] Advantageously, the element of revolution and the cap each comprise a thread, these threads cooperating so that the cap is held on the element of revolution. The invention also relates to an aircraft turbomachine comprising an assembly as defined above and a fan rotating in one direction of rotation during its operation, the direction of the threads being reversed relative to the direction of rotation of the fan, the cowl being a fan nose.

[0029] The invention also relates to an aircraft comprising an aircraft turbomachine as defined above.

[0030] Brief description of the drawings

[0031] Other aims, characteristics and advantages of the invention will appear on reading the following description, given solely by way of non-limiting example, and made with reference to the appended drawings in which:

[0032] [Fig 1] is a view of an embodiment of a hood handling tool according to the invention;

[0033] [Fig 2] is a sectional view of a detail of Figure 1;

[0034] [Fig 3] is a sectional view of an assembly comprising a cover and a cap according to the invention;

[0035] [Fig 4] is a view of a particular embodiment of a handling tool according to the invention;

[0036] [Fig 5] is a view of a variant of Figure 4;

[0037] [Fig 6] is a view of an embodiment of a handling tool according to the invention suitable for transporting a hood;

[0038] [Fig 7] is a view of an embodiment of a handling tool comprising lifting handles; [Fig 8] is a view of an embodiment of a handling tool comprising lifting handles and a rotation handwheel;

[0039] [Fig 9] is a view of an embodiment of a handling tool comprising a lifting ring and two rotating handwheels;

[0040] [Fig 10] is a view of an embodiment of a handling tool comprising a forklift;

[0041] [Fig H] is a view of an embodiment of a hood according to the invention;

[0042] [Fig 12] is a view of a detail of an embodiment of a handling tool comprising a flange held against the cover according to the invention; and

[0043] [Fig 13] is a sectional view of the tooling illustrated in Figure 12.

[0044] Detailed description of at least one embodiment

[0045] Figure 1 schematically shows an embodiment of an industrial part of revolution 1 as well as an embodiment of handling tooling 3 configured to allow the lifting of said industrial part of revolution 1.

[0046] An industrial part of revolution is any industrial part comprising an axis around which the industrial part has a symmetry of revolution. The industrial part is for example cylindrical, conical, spherical, etc.

[0047] In the illustrated embodiment, the industrial part is a cover 1 of an aircraft turbomachine. The aircraft turbomachine is for example a turbojet, in particular a double-flow turbojet, or a turboprop.

[0048] Cowl 1 is an inlet cowl, also called a nose (noze spinner in English terms), which corresponds to the central cone upstream of a turbomachine fan. Cowl is also a central rear plug of a turbomachine nozzle.

[0049] The cover 1 illustrated in Figure 1 is an inlet cover of a turbomachine comprising an axis 5. In particular, the axis 5 is coaxial with the axis of symmetry of revolution and is intended to be coaxial and connected with the axis of rotation of the turbomachine.

[0050] Figure 2 shows a sectional view of a detail of Figure 1.

[0051] The cover 1 comprises a conical frame 7 centered around the axis 5, the conical tip 9 of the frame 7 passing through the axis 5.

[0052] Conical means any shape having a circular base wider than the point 9, the point 9 being able to be flattened, as illustrated in figure 1. Conical therefore means any shape of the ogive, cone, dome type, etc.

[0053] The conical frame 7 is made of a material resistant to the pressure conditions subjected upstream of an aircraft turbomachine.

[0054] The hood 1 comprises an outer skin 11 fixed around the conical frame 7, so as to protect the frame 7 and to form a smooth and aerodynamic covering.

[0055] The outer skin 11 comprises, for example, carbon and / or aluminum. The outer skin has a thickness of between 1 and 5 millimeters, preferably 2 millimeters.

[0056] The cover 1 further comprises a revolution element 13 fixed to the conical frame 7 along the axis 5 and against the external skin 11. In particular, the revolution element 13 is positioned at the conical tip 9 of the cover 1. In addition, in the presence of the revolution element 13, the external skin 11 is fixed to the revolution element 13.

[0057] The element of revolution 13 comprises in particular a metallic material, in particular aluminum, and / or a composite material. The material used for the element of revolution 13 is robust and allows the hood 1 to be gripped and lifted by means of said element of revolution 13. For this purpose, the thickness of the element of revolution 13 is between 3 and 25 centimeters. The shape of the element of revolution 13 can be modified, the latter being able to serve as a reserve of material for balancing the hood 1.

[0058] The element of revolution 13, given a positioning at the tip 9 of the cover 1, also makes it possible to represent a good reference for other applications, for example for the manufacture of the cover 1.

[0059] The outer skin 11 and the revolution element 13 each further comprise a hole 14 and a hole 15 respectively. These holes 14 and 15 are aligned with each other and coaxial with the axis 5. Thus, the handling tool 3, which comprises a bar 17, in particular a bar 17 with a diameter less than or equal to that of the holes 14 and 15, allows the cover 1 to be gripped and lifted by inserting said bar 17 into the holes 14 and 15.

[0060] The revolution element 13 thus creates a handling interface. Its positioning in the center of the hood 1 allows better balancing without unbalance and without the need for a plurality of sling rings on the periphery of the hood 1. Handling is facilitated and the aerodynamic performance of the hood 1 is improved.

[0061] In a particular embodiment, the hole 15 passes entirely through the element of revolution 13. Thus, a bar 17 inserted into the hole 15 can emerge from the other side of the element of revolution 13 in order, for example, to fix it and prevent it from disengaging.

[0062] The through holes 14 and 15 also make it possible to carry out endoscopic checks, or to introduce cables or tubes into the cover 1 via the holes 14 and 15, for example to carry out installation or maintenance of a device such as an anti-icing device.

[0063] Holes 14 and 15 allow, in addition to the insertion of handling tools 3, the insertion of holding tools for transporting the hood.

[0064] In a particular embodiment, the element of revolution 13 comprises an annular shoulder 19. More precisely, the hole 15 has a larger diameter at the tip 9 of the cover 1, the diameter of the hole 15 narrowing in the element of revolution 13 so as to form said annular shoulder 19. The shoulder 19 allows the improvement of the recovery of rotational forces.

[0065] Hole 15 may optionally include a simple bore, in other words include a smooth internal surface, in other words not threaded.

[0066] Alternatively, the hole 15 comprises a means for longitudinally locking the bar 17 along the axis 5. For example, the locking means comprises a thread on the internal surface of the hole 15. In other words, the element of revolution 13 comprises a thread oriented towards the hole 15.

[0067] The thread can thus allow better fixing of a threaded bar 17 in the hole 15, although handling tools 3 with an unthreaded bar 17 can still be used.

[0068] Optionally, the hole 15 comprises a means 21 A configured to brake and / or immobilize the bar 17 inserted in the hole 15. In other words, the element of revolution comprises the means 21 A at the hole 15. This means 21 A makes it possible to ensure that the bar 17 is held in the cover 1 during handling in order to avoid any accident at the handling location. The means 21A is for example a cavity 21 A configured to receive and block one or more balls 21 B of a ball pin included in the bar 17 and the radial movement of the balls of which can be activated by a button 21 C positioned outside the hole 15 so as to be accessible by an operator.

[0069] Figure 3 shows a sectional view of a detail of an embodiment of an assembly 23 according to the invention. The assembly comprises a cover 1 as illustrated in Figures 1 and 2, as well as a plug 25 configured to plug the hole 15 when the cover 1 is fixed to an aircraft turbomachine.

[0070] Indeed, the presence of the hole 15 in the cowl 1 can harm the aerodynamics of the aircraft once the cowl 1 is installed on a turbomachine of said aircraft. Furthermore, during flight, air compressed at more than 600 km / h would enter the cowl 1 while on the ground, animals could come and nest in the cowl 1. Thus, the installation of a plug 25 at the end of the hole 15 is advantageous. In particular, the plug 25 can be threaded, just like the hole 15, so as to be screwed into the hole 15. The plug 25 for example rests on the shoulder 19, if applicable.

[0071] In a particular embodiment, the direction of the thread of the hole 15 is reversed relative to the direction of rotation for which the cover 1 is designed, in other words relative to the direction of rotation of the fan when the cover 1 is a fan nose. For example, if the turbomachine in operation for which the cover 1 is intended rotates in a first direction, the thread of the hole 15 must be oriented in the opposite direction. This embodiment makes it possible to prevent the hole 15 from becoming unblocked on its own during the flight of the aircraft. Advantageously, the plug 25 is thus tightened more independently during the flight.

[0072] In the embodiment for which the hole 15 comprises a means 21A configured to brake and / or immobilize the bar 17 in the hole 15, said means 21A can also make it possible to immobilize the plug 25 when the latter is put in place.

[0073] Optionally, the cover 1 comprises a plurality of orifices 27 made around the hole 15, the orifices 27 extending through the outer skin 11 and into the element of revolution 13, for example in the form of threaded sockets normal to the surface of the cover 1. The orifices 27 allow the insertion of screws in order to fix a flange 28 of the handling tool 3 to the cover 1 as illustrated in FIG. 4. The assembly 23 of the cover 1 and the plug 25 also comprises a plurality of shutters (not shown) making it possible to plug the plurality of orifices 27 and to prevent air from entering the cover 1.

[0074] The cover 1 is generally configured to be used with the handling tool 3 described below.

[0075] In the embodiment illustrated in Figure 1, the handling tool 3 comprises a body 29 and a bar 17 such as the bar 17 presented previously. The bar 17 extends along its longitudinal axis from the body 29 distally. The bar 17 is thus configured to be inserted into a hole in an industrial part of revolution such as the hole 15 described previously. For example, the body 29 is connected to the bar 17 via a pivot connection 31 as illustrated in Figure 2. The bar 17 comprises a first end 33 in contact with the pivot connection 31 as well as a second end 35 intended to be inserted into the hole 15. The bar 17 is optionally threaded.

[0076] The tool 3 is configured to allow the rotation of the bar 17 relative to the body 29 and around the longitudinal axis of said bar 17, the longitudinal axis of the bar 17 being intended to be coaxial with the axis 5.

[0077] Optionally, the tool 3 comprises a means 21 B configured to brake and / or immobilize in rotation the bar 17 inserted in the hole 15. This means 21 B makes it possible to guarantee the maintenance of the bar 17 in the cover 1 during handling in order to avoid any accident at the handling location. The means is for example one or more balls 21 B of a ball pin included in the bar 17 and the radial movement of the balls of which can be activated by a button 21 C positioned outside the hole 15 so as to be accessible by an operator. The balls 21 B are configured to be received and blocked in a cavity 21 A of the hole 15.

[0078] Thus, when the bar 17 is inserted into the hole 15, the bar 17 comprising a shoulder bearing on the shoulder 19 if necessary, it can make it possible to lift the industrial part of revolution 1 and in particular makes it possible to rotate the industrial part 1. By way of example, the industrial part illustrated is the cover 1 previously described.

[0079] In the embodiment illustrated in FIG. 1, the tool 3 comprises a lifting ring 37 configured to be attached to a lifting sling and positioned vertically above the center of gravity of the assembly comprising the tool 3 and the cover 1.

[0080] The tool 3 thus makes it possible to lift the cover 1, for example so as to install it on an aircraft turbomachine, and to simultaneously carry out the necessary connections and screwing. Figure 4 shows a particular embodiment of a handling tool 3 as well as a cover 1 as illustrated in Figure 1.

[0081] In Figure 4, the body 29 of the handling tool 3 is not shown.

[0082] The tool 3 comprises a force distribution flange 28 extending radially from the first end 33 of the bar 17 and having a conical shape, more precisely complementary to the shape of the cover 1, in particular complementary to the point 9 of the cone formed by the cover 1. The flange 28 thus makes it possible to distribute the lifting and rotation forces elsewhere than at a level of the bar 17 and the hole 15 by contact between the flange 28 and the cover 1.

[0083] Optionally, the flange 28 comprises screws 39 for fixing the flange 28 to the cover 1. The fixing screws 39 are inserted for example into the orifices 27 of the cover 1. The flange 28 comprises for example three lobes 41, each lobe 41 comprising at least one screw 39 for fixing the flange 28 to the cover 1.

[0084] Figure 5 shows a variant of Figure 4 in which the flange 28 does not include a fixing screw 39, only the contact of the flange 28 with the cover 1 allowing the distribution of force.

[0085] Figure 6 shows a particular embodiment of a handling tool 3, as well as a cover 1 according to Figure 1.

[0086] In this embodiment, the handling tool 3 comprises several rings 43, for example lifting rings, making it possible to attach the cover 1 to a base 44 and to transport it easily, for example using straps 45.

[0087] Figure 7 shows a particular embodiment of the handling tool 3 as well as a cover 1 similar to that of Figure 1.

[0088] The handling equipment 3 includes lifting handles 47 that can be grasped by one or more operators.

[0089] In this embodiment, two operators can support the cover 1 while a third performs installation or maintenance operations. The cover 1 can be rotated about its axis 5, for example by turning it by hand.

[0090] Figure 8 shows a variant of the embodiment of Figure 7.

[0091] In this variant, the tool 3 comprises a member 49 for rotating the bar 17 around its longitudinal axis. The member 49 thus facilitates more precise rotation. The member 49 is, for example, a flywheel.

[0092] Figure 9 shows another embodiment of a handling tool 3 and a cover 1.

[0093] In this embodiment, the tool 3 comprises a lifting ring 37 positioned vertically above the center of gravity of the assembly comprising the tool 3 and the cover 1, a member 49 for rotating the bar 17 around its longitudinal axis, intended to be coaxial with the axis 5, as well as a device 51 for rotating the bar 17 around a second axis 53 orthogonal to the longitudinal axis of the bar 17. The second axis 53 is in particular horizontal when the cover 1 is in position to be installed on the turbomachine.

[0094] The device 51 is for example a steering wheel. In particular, it allows the cover 1 to be moved from a transport position as illustrated in FIG. 6 to an installation position as illustrated in FIG. 9.

[0095] Figure 10 shows another embodiment of the handling tool 3.

[0096] In this embodiment, the handling tool 3 comprises a forklift 55 connected to the body 29 and making it possible to support the body 29. The forklift 55 comprises a means 56 for adjusting the height of the body 29, for example using a crank or a steering wheel, for the purpose of installing or maintaining the cover 1 on the turbomachine for example. The forklift 55 comprises, for example, casters allowing it to be mobile.

[0097] For the purpose of clarification, Figure 11 shows a cover 1 alone. In the embodiment shown, the holes 14 and 15 respectively formed in the outer skin 11 and the revolution element 13 are illustrated. In addition, the cover 1 comprises a plurality of holes for fixing a flange 28.

[0098] Figure 12 also shows a view of a detail of a handling tool 3. The detail illustrates the pivot connection 31 as well as the flange 28 held on the cover 1.

[0099] Figure 13 is a sectional view of the embodiment illustrated in Figure 12 and illustrates a pivot connection 31 at the end of which the bar 17 is positioned, for example made of the same material as the flange 28. All the embodiments previously described are compatible with each other. In particular, the tool 3 may comprise both lifting handles 47, a lifting ring 37 and a forklift 55, as well as one and / or the other of the members and devices 49 and 51.

Claims

CLAIMS 1. Cowl (1) for an aircraft turbomachine, extending around an axis (5), and comprising a conical frame (7) centered around the axis (5), an outer skin (11) fixed around the frame (7), characterized in that it comprises a revolution element (13) fixed to the conical frame (7) along the axis (5) and against the outer skin (11), the outer skin (11) and the revolution element (13) each comprising a hole (14, 15) coaxial with the axis (5), the revolution element (13) being configured to allow the cowl (1) to be gripped by inserting a bar (17) into the holes (14, 15).

2. Hood (1) according to claim 1, wherein the hole (15) of the revolution element passes through the revolution element (13).

3. Cover (1) according to one of claims 1 and 2, the cover (1) being a turbomachine fan nose.

4. Hood (1) according to any one of claims 1 to 3, in which the revolution element (13) comprises a longitudinal locking means, preferably a thread oriented towards the hole (15).

5. Cover (1) according to any one of claims 1 to 4, in which the hole (15) comprises means (21A) configured to brake and / or immobilize in rotation around the axis (5) the bar (17) inserted in the hole (15).

6. Hood (1) according to any one of claims 1 to 5, wherein the revolution element (13) comprises an annular shoulder (19) extending into the hole (14) of the outer skin (11) at the end of the hole (15) of the revolution element (13).

7. Hood (1) according to any one of claims 1 to 6, comprising a plurality of orifices (27) around the hole (15), the orifices (27) extending through the outer skin (11) and into the revolution element (13).

8. Assembly (23) comprising a cover (1) according to any one of claims 1 to 7 and a plug (25) for plugging the hole (15).

9. Assembly (23) according to claim 8, in which the revolution element (13) and the plug (25) each comprise a thread, these threads cooperating so that the cap (25) is held on the revolution element (13).

10. Aircraft turbomachine comprising an assembly (23) according to claim 9 and a fan rotating in one direction of rotation during its operation, the direction of the threads being reversed relative to the direction of rotation of the fan, the cover (1) being a fan nose.

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