LINKING DEVICE BETWEEN ANNULAR ELEMENTS OF AN AIRCRAFT PROPULSION ASSEMBLY WITH SEALING ELEMENTS AND CORRESPONDING TURBOMACHINE

Abstract

The invention relates to a linkage device (10) of an aircraft propulsion assembly comprising a first element (11) of a cowling (9) and a second element (12) of a housing (7) centered on the longitudinal axis (X), the second element (12) comprising a groove (13) extending partly around the longitudinal axis, and receiving a first sealing element (17), the first element being rotationally movable relative to the housing between a closed and open position, and comprising a rib (20) compressing at least partly the first sealing element (17), radially, in the closed position.According to the invention, the connecting device comprises a second sealing element (22) which is disposed between the first sealing element and the first element in the closed position, the second sealing element being arranged to radially compress the first sealing element in the closed position and in a direction substantially parallel to the longitudinal axis. Figure for the abstract: Fig. 4.

Description

Title of the invention: CONNECTING DEVICE BETWEEN ANNULAR ELEMENTS OF A PROPULSIVE ASSEMBLY AIRCRAFT WITH SEALING ELEMENTS AND CORRESPONDING TURBOMACHINE Technical field of the invention

[0001] The present invention relates to the field of propulsion assemblies comprising an aircraft turbomachine. More specifically, the invention relates to a connection device between a first element of a nacelle and a second annular element of a turbomachine casing enclosed by the nacelle. Technological background

[0002] An aircraft propulsion system generally comprises a turbomachine with a casing, centered on a longitudinal axis, surrounding at least the combustion chamber of the turbomachine, and a nacelle that encloses the casing. The propulsion system includes a mounting mast or pylon that allows the turbomachine to be suspended or attached to the aircraft structure.

[0003] The nacelle may be equipped with thrust reversers comprising cowlings in the form of half-shells or a 360° annular cowling and movable relative to the housing and the rest of the nacelle. Each cowling is hinged at one end to the mounting mast by means of one or more hinges or one or more slides whose axis extends along the longitudinal axis. The free end of one cowling is locked to a free end of another cowling, and each cowling is connected to the housing in order to transfer the aerodynamic forces, particularly axial forces, experienced by each cowling to the housing.

[0004] The housing includes an annular groove having a V- or U-shaped cross-section, centered on the longitudinal axis, at the bottom of which an O-ring is arranged. The nacelle is equipped with a rib or protrusion having a shape complementary to that of the groove and designed to engage in the groove when the hood or hoods are locked onto the housing. The rib compresses the O-ring, thus ensuring the airtightness of the assembly when the hood or hoods are closed and locked. The shape of the rib also guides the closing of the hood or hoods. The connection between the groove and the rib is arranged near the hinge provided on the mounting mast. Such an example of a propulsion assembly with a connection between the groove and the rib compressing an O-ring is described in patent document FR-A1-2756323.

[0005] However, since the nacelle and the casing are made up of different parts or covers, this can lead to a break in the seal at various points and affect the aerodynamics of the propulsion system. In particular, airflow leaks and fire hazards can occur at the connections between the casing and the nacelle, which can reduce the turbomachine's performance. Furthermore, the complex shapes of the cover(s) and the nacelle require well-defined gasket shapes to ensure continuous sealing and to prevent damage when the covers are closed.

[0006] There is therefore a need to resolve all or part of the aforementioned drawbacks. Summary of the invention

[0007] The objective of the present invention is to provide a solution to minimize the risks of aerodynamic leaks and fire at the connections between a part of at least one movable hood of the nacelle (only when opening the maintenance hood for maintenance operations) and a fixed part of the turbomachine housing.

[0008] We achieve this objective in accordance with the invention by means of a linkage device for an aircraft propulsion assembly comprising a first element of a cowling and a second element of a casing centered on a longitudinal axis, the second element comprising a groove extending at least partially around the longitudinal axis, being open outwards and being provided with a bottom in which is disposed a first sealing element extending at least partially around the longitudinal axis, the first element being rotationally movable relative to the casing between a closed position and an open position, and comprising a rib adapted to compress at least partially the first sealing element, radially relative to the longitudinal axis, in the closed position,

[0009] the connecting device comprising a second sealing element which is disposed between the first sealing element and the first element of the hood at least in the closed position, the second sealing element being arranged so as to radially compress the first sealing element in the closed position and in a direction substantially parallel to the longitudinal axis.

[0010] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, the arrangement of this second sealing element makes it possible to reinforce and optimize the seal at the connection between the hood and the housing, especially in the closed position, to avoid impacting the drag during the operation of the turbomachine.

[0011] The linking device also includes one or more of the following features the following, taken alone or in combination:

[0012] - the throat comprises a first wall and a second wall extending on the one hand radially and on the other hand at least partly around the longitudinal axis, each first wall and second wall being opposite each other and being provided with a through notch along the longitudinal axis and opening into the groove, the second sealing element extending through the notches in the closed position.

[0013] - the second element comprises a partition which rises in a direction sen possibly transverse to a circumferential direction around the longitudinal axis, the second sealing element being able to bear tangentially, in the closed position, against a stop surface defined in a substantially radial plane.

[0014] - the rib includes a cutout passing through it transversely and in which is arranged by complementary shape to the second sealing element.

[0015] - the second sealing element is fixed on the rib.

[0016] - the second sealing element is attached and separate from the rib.

[0017] - the first sealing element and the second sealing element are formed of a single piece.

[0018] The invention relates to a propulsion assembly comprising an aircraft turbomachine equipped with an annular casing, at least one hood mounted movable relative to the casing, a mounting mast for attaching the turbomachine to the aircraft and a linkage device as described above.

[0019] According to an advantageous feature of this propulsion assembly, two second sealing elements extend substantially on either side of the attachment mast.

[0020] According to another advantageous feature of this propulsion assembly, the second sealing elements are arranged by analogy to the dial of a clock at Ih and 1 Ih respectively.

[0021] The invention also relates to an aircraft equipped with such a propulsion system. Brief description of the figures

[0022] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which:

[0023] - Fig. 1 is a radial cross-sectional view of an example of a propulsion assembly connected to an aircraft wing according to the invention;

[0024] - Figure [Fig. 2] schematically represents a linking device between a first element of a nacelle hood and second element of a stator housing according to the invention;

[0025] - Figure 3 is a top and perspective view of an example of a device connection comprising sealing elements according to the invention;

[0026] - The [Fig.4] is an axial cross-sectional view of the linking device according to the [Fig.3];

[0027] - Figure [Fig. 5] is a radial cross-sectional and detailed view of the connecting device according to the [Fig.3];

[0028] - Figure 6 is a front view of the linking device according to Figure 3; and

[0029] - Figure 7 is a perspective and transparency view of an example of a device of connection according to the invention. Detailed description of the invention

[0030] Fig. 1 represents a propulsion unit 1 intended to be mounted on an aircraft 2, such as an airplane. The propulsion unit 1 comprises a turbomachine 3 with longitudinal axis X and a nacelle 4 enclosing the turbomachine 3.

[0031] The propulsion assembly 1 preferably includes a mounting mast 5 or pylon which is known by the English acronym "EMS" for "Engine Mounting Structure" and which is configured to connect the turbomachine 3 to a structure of one of the wings 6 of the aircraft 2. Preferably, the turbomachine 3 is suspended below the wing 6. In other configurations, the turbomachine 3 can be arranged above the wing 6 or behind the fuselage.

[0032] The turbomachine 3 may be a turboprop engine having an unducted propeller, known by the English expression "open rotor" or "unducted fan" or "open fan", or having two unducted and counter-rotating propellers (known by the English acronym "UDF" for "Unducted Dual Fan"), or having a single unducted propeller and an unducted stator comprising several stator blades (known by the English acronym "USF" for "Unducted Single Fan"). The turbomachine 3 may also be a turbojet engine, in particular a twin-spool, turbofan engine, and includes a fan.

[0033] The invention applies generally to a turbomachine which includes a blower or propeller which is shrouded or unshrouded.

[0034] In the present invention, and more generally, the terms "upstream," "downstream," "axial," and "axially" are defined with respect to the gas flow in the turbomachine and with respect to the longitudinal axis X of the turbomachine. Similarly, the terms "radial," "radially," "internal," and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X.

[0035] The turbomachine is equipped with a casing 7, in particular an external one, which surrounds and / or structurally supports at least parts of the compressor assembly (not re shown), the combustion chamber (not shown) and the turbine assembly (not shown) of the turbomachine 3. The casing 7 is centered on the longitudinal axis X.

[0036] The casing 7 is advantageously extended downstream by an ejection structure (not shown) or ejection nozzle which is generally one of the elements of the nacelle.

[0037] The nacelle 4, centered on the longitudinal axis X, surrounds the casing 7, advantageously forming an aerodynamic external surface 8. The nacelle 4 advantageously includes cowlings 9 that are movable relative to the rest of the nacelle 4. These movable cowlings 9 can be fan cowlings, thrust reverser cowlings, or maintenance cowlings that allow access to certain parts of the turbomachine for maintenance. Advantageously, the maintenance cowlings are without thrust reversers and do not pivot when the turbomachine is operating. The maintenance cowlings advantageously delimit the nacelle and channel the secondary airflow (or external airflow). As is known, thrust reversers allow the aircraft to be slowed down by diverting the airflow (in particular the secondary airflow) upstream.

[0038] When the turbomachine 3 is a turbojet, the nacelle 4 delimits an air inlet opening into the fan and includes from upstream to downstream fan cowls, thrust reverser cowls or maintenance cowls, and an ejection cowl or secondary flow ejection nozzle.

[0039] A primary flow advantageously passes through the compressor assembly, the combustion chamber, and the turbine assembly in a primary channel (not shown). The secondary air flow circulates around the primary channel.

[0040] Advantageously, the movable hoods 9 are each in the form of half-shells or half-cylinders. In other words, the hoods 9 are mounted on either side of a radial plane passing through the attachment mast 5. Other hood installation configurations are possible.

[0041] With reference to [Fig. 1], each hood 9 of the nacelle 4 is pivotally mounted about an axis A parallel to the longitudinal axis X between an open position and a closed position. Each hood 9 includes an end 9a advantageously hinged on the mounting mast 5. The pivoting can be achieved using a well-known hinge system (not shown). Each hood 9 includes a free end 9b which is advantageously designed to lock to a free end 9b of the opposite hood 9 when the hood 9 is closed. Alternatively, each free end 9b of a hood is locked to the housing 7. For this purpose, a locking device (not shown) is provided, for example, with latches.

[0042] Figure 2 shows a connecting device 10 between a first element 11 of a hood 9 of the nacelle 4 and a second element 12 of the casing 7. Advantageously, but not limitingly, there is a connecting device 10 between each hood and the casing 7. Preferably, the or each connecting device 10 is located near the attachment mast 5.

[0043] The second element 12 comprises a groove 13 extending at least partially around the longitudinal axis X. The groove 13 has a U- or V-shaped form and is preferably open radially outwards. Advantageously, the groove 13 comprises a first wall 14 and a second wall 15, each extending, on the one hand, at least partially around the longitudinal axis X and, on the other hand, radially. Each first wall 14 and second wall 15 is arranged opposite each other.

[0044] According to one embodiment, two portions of the groove (only one of which is shown in Figures 2, 3, 4, and 7) extend on either side of a radial plane containing the longitudinal axis X and over a sector between 12 o'clock and 6 o'clock (by analogy with the face of a clock). Advantageously, but not limitingly, there is no portion of the groove at 6 o'clock and 12 o'clock, and over a sector that is between 10° and 20° around the longitudinal axis X. In other words, the groove 13 is not annular over 360°. Advantageously, but not limitingly, the attachment mast 5 separates two portions of the groove 13 around the longitudinal axis X. Each portion of the groove comprises a first wall 14 and a second wall 15 which extend, for example, on either side of the attachment mast 5.

[0045] Each groove 13, or portion of a groove, comprises a bottom 16 in which a first sealing element 17 is disposed. The bottom 16 is connected to the first wall 14 and the second wall 15, which rise from it. The first sealing element 17 extends at least partially around the longitudinal axis X.

[0046] Advantageously, there is a first sealing element 17 in each portion of the groove. Advantageously, but not limitingly, each first sealing element 17 has a length substantially equal to a portion of the groove.

[0047] In the remainder of this description, the term "throat" is used for a throat or a portion of a throat.

[0048] The first sealing element 17 is preferably an O-ring centered on the longitudinal axis X. The latter is made, for example, of an elastomeric polymer material, a thermoplastic polymer material, or a thermoplastic elastomer. Preferably, the material is a rubber.

[0049] Preferably, the first sealing element 17 is fixed, for example by gluing, to the bottom of the groove 13.

[0050] The first element 11 of the hood 9 is movable in rotation or pivoting about the longitudinal axis X relative to the housing 7. The first element 11 includes avanta eguously a rib 20 (known as a knife) which is able to position itself opposite a part of the first sealing element 17.

[0051] Advantageously, the rib 20 extends from an inner face 21 of the cover 9. Preferably, the rib 20 radially compresses the first sealing element 17 when the cover 9 (or the first element 11) is in the closed position. For this purpose, the rib 20 engages inside the groove 13 by complementary shape. Advantageously, but not exclusively, the rib 20 has a shape complementary to that of the groove 13.

[0052] Following the example shown in [Fig.2], the second wall 15 includes an internal face 15a which is flat, defined in a radial plane, and against which a flat face 20a of the rib 20 comes into contact. The first wall 14 includes an internal face 14a which is flat, defined for example in a plane inclined with respect to the radial axis and against which a flat face 20b of the rib 20 comes into contact.

[0053] The arrangement of such a sealing element 17 and such an interpenetration of the rib 20 and the groove 13 makes it possible to ensure a seal against fluid, in particular against air, between each hood 9 and the housing 7, especially in the closed position.

[0054] With reference to [Fig. 3] and [Fig. 4], the connecting device 10 comprises at least a second sealing element 22 which is configured to provide continuous sealing at the groove. Advantageously, the second sealing element is arranged, at least partially, radially between the first element 11 of the cover 9 and the first sealing element 17, particularly at least in the closed position. Advantageously, the second sealing element 22 is arranged to compress the first sealing element 17 in the closed position. According to one embodiment, the second sealing element 22 extends at least partially into the groove 13 when the first sealing element 17 is compressed.

[0055] Preferably, the second sealing element 22 extends at least partly in a direction substantially parallel to the longitudinal axis X at the level of the groove 13. In particular, the direction of the second sealing element 22 is parallel to the longitudinal axis X or has an inclination with respect to the longitudinal axis X.

[0056] Each first wall 14 and second wall 15 is provided with a through notch 23 along the longitudinal axis X and opening into the groove 13. Advantageously, but not exclusively, the notches 23 are open outwards and open onto a free edge 13a of the first and second walls of the groove 13. The second sealing element 22 extends through the notches 23. In this way, there is continuity of the second sealing element 22 at the level of the groove 13, preferably on both sides of the groove 13 (along the longitudinal axis X), and an optimization of airtightness. In particular, the second sealing element 22 found inside the groove 13 only between the notches 23 and when the cover 9 is in the closed position.

[0057] The notches 23 have a shape allowing the passage of the second sealing element 22 and can, for example, be U, V or C shaped. The second sealing element 22 being continuous at this point, can provide sealing in other areas of the nacelle 4 and the housing 7 without breaking the seal.

[0058] According to one embodiment, the second sealing element 22 is continuous and extends on either side of the attachment mast 5 between a first end and a second end. The first end and the second end are connected to the attachment mast 5 and extend around the longitudinal axis X. The second sealing element 22 comprises a first radial portion connected to the first end and the second end, and extending in a radial direction. Then, each first radial portion is connected to a second portion extending in a circumferential direction (around the longitudinal axis) and which is connected to a third portion along the longitudinal axis X by passing through the groove 13. Each third portion having passed through the groove 13 is connected to a fourth arc-shaped portion extending in the circumferential direction.

[0059] According to an advantageous feature, shown in particular in Figures 5 and 6, the rib 20 comprises a cutout 24 passing through the wall of the rib 20 on both sides and in a transverse direction relative to the elongation direction of the rib 20. The elongation direction of the rib is parallel to the longitudinal direction X in the closed position. The second sealing element 22 is advantageously installed in the notch 23.

[0060] The cutout 24 has, in this embodiment, a U shape, or C or V shape or another shape provided that it allows the arrangement of the second sealing element 22.

[0061] The second sealing element 22 preferably has a shape or at least a part of a shape substantially complementary to that of the cutout 24.

[0062] Each cutout 24 is open inwards (in particular towards the longitudinal axis X in the closed position). The opening of the cutout 24 leads, for example, to an internal edge 25 of the rib 20.

[0063] The second sealing element 22 has a lower face 26 that is flush with the inner edge 25 of the rib 20. The lower face 26 is in contact with the first sealing element 17 in the closed position. The inner edge 25 of the rib is in contact with the first sealing element 17. The second sealing element 22 completes the missing portion (via the cutout 24) and contributes to the continuous seal between the rib 20 and the groove 13.

[0064] Advantageously, the second sealing element 22 is made of a material The second sealing element 22 is made of a polymer elastomer, a thermoplastic polymer material, or a thermoplastic elastomer. Preferably, the second sealing element 22 is made of rubber. Such a material is very economical and allows for complex shapes. Alternatively, the second sealing element 22 is made of a composite material. The composite material may include fibers (e.g., glass fibers) to provide additional functions such as fire resistance. As yet another alternative, the second sealing element 22 is made of a material similar to that of the first sealing element 17 or of a material compatible with that of the first sealing element 17.

[0065] Following an example embodiment, the second sealing element 22 has a parallelepiped shape. Such a shape is simple to manufacture and allows for better contact and consequently better sealing with the first sealing element 17.

[0066] According to an advantageous feature, the second sealing element 22 is supported by the annular element 11 of the cover 9. In particular, the second sealing element 22 is fixed to the annular element. The fixing may be permanent or removable. The fixing of the second sealing element 22 is, for example, by bonding, clipping, or molding onto the cover 9. By fixing the second sealing element 22 to the cover, closing the cover is simplified and any gaps between the cover 9 and the second sealing element 22 are reduced, particularly when opening the cover 9.

[0067] Alternatively, the second sealing element 22 is formed as a single piece with the first sealing element 17. In this case, the second sealing element 22 and the first sealing element 17 are preferably fixed in the groove 13, and assembly is facilitated by reducing handling. The materials of the two sealing elements 17 and 22, formed as a single piece, may be different and / or have different properties.

[0068] According to yet another alternative, the second sealing element 22 is separate from the cover 9 and the first sealing element 17. In other words, the second sealing element 22 is an added part. Such a configuration simplifies manufacturing and allows the second sealing element 22 to be replaced if it becomes damaged.

[0069] With reference to [Fig. 7], the first element 11 of the cover 9 here includes a support 30 which reinforces the hold of the second sealing element 22 as it elongates and guides the latter. The support 30 extends on either side of the cutout 24 from an external surface 27 of the rib 20, in the transverse direction. In the present embodiment, the support 30 has an L-shaped radial cross-section. The second sealing element 22 is fixed and / or supported against support 30. The fixing can be achieved for example by gluing, molding or clipping.

[0070] According to another advantageous feature, the second element 12 of the housing 7 comprises a partition 31 that extends substantially transversely to the circumferential direction around the longitudinal axis X. In particular, the partition 31 comprises a stop surface 32 defined in a plane that is radial or inclined with respect to the radial axis. The partition 31 also extends substantially (+ / -20° for example) along the longitudinal axis X.

[0071] Advantageously, but not exclusively, the second sealing element 22 is supported tangentially against a buttress surface of the first element 11. Preferably, the buttress surface is that of the partition 31. Advantageously, a first lateral face 33 of the second sealing element 22 provides a planar support connection with the buttress surface 32. In this embodiment, the first lateral face 33 is opposite a second lateral face 34 which is fixed to a wall of the support 30.

[0072] The second sealing element 22, through contact with the first sealing element 17 and the abutment surface 32, provides sealing in two directions, namely radial and tangential. The second sealing element 22 is compressed against the partition 31 and against the first sealing element 17.

[0073] According to an embodiment not shown, the second sealing element 22 may include wings or extensions extending from the edge 26 so as to increase the contact area with the first sealing element 17.

[0074] According to one embodiment, a second sealing element 22 is positioned at approximately 1h by analogy with the face of a clock. This position is represented, for example, by a dashed circle in [Fig. 1]. Another second sealing element would be positioned at 1 1h (opposite the one positioned at 2h) by analogy with the face of this clock. In other words, the groove 13 comprises notches 23 positioned approximately at 1h and 1 1h on the face of a clock.

Claims

Demands

1. A connecting device (10) for an aircraft propulsion assembly comprising a first element (11) of a cowling (9) and a second element (12) of a housing (7) centered on a longitudinal axis (X), the second element (12) comprising a groove (13) extending at least partially around the longitudinal axis (X), being open outwards and having a bottom (16) in which is disposed a first sealing element (17) extending at least partially around the longitudinal axis (X), the first element (11) being rotatable relative to the housing (7) between a closed position and an open position, and comprising a rib (20) adapted to compress at least partially the first sealing element (17), radially relative to the longitudinal axis (X), in the closed position,characterized in that the connecting device (10) comprises a second sealing element (22) which is disposed between the first sealing element (17) and the first element (11) of the hood (9) at least in the closed position, the second sealing element (22) being arranged so as to radially compress the first sealing element (17) in the closed position and in a direction substantially parallel to the longitudinal axis (X).

2. A connecting device (10) according to claim 1, characterized in that the groove (13) comprises a first wall (14) and a second wall (15) extending on the one hand radially and on the other hand at least partly around the longitudinal axis (X), each first wall (14) and second wall (15) being opposite each other and being provided with a notch (23) passing through along the longitudinal axis (X) and opening into the groove (13), the second sealing element (22) extending through the notches (23) in the closed position.

3. A connecting device (10) according to claim 1 or 2, characterized in that the second element (12) comprises a partition (31) which rises in a substantially transverse direction to a circumferential direction around the longitudinal axis (X), the second sealing element (22) being able to bear tangentially, in the closed position, against a stop surface (32) defined in a substantially radial plane.

4. A connecting device (10) according to any one of the preceding claims, characterized in that the rib (20) comprises a cutout (24) crossing it transversely and in which the second sealing element (22) is arranged by complementary form.

5. Connecting device (10) according to any one of claims 1 to 4, characterized in that the second sealing element (22) is fixed on the rib (20).

6. A connecting device (10) according to any one of claims 1 to 4, characterized in that the second sealing element (22) is attached to and separate from the rib (20).

7. A connecting device (10) according to any one of claims 1 to 4, characterized in that the first sealing element (17) and the second sealing element (22) are formed from a single piece.

8. Propulsion assembly (1) comprising an aircraft turbomachine (1) equipped with an annular casing (7), at least one cowling (9) mounted movable relative to the casing (7), a mounting mast (5) for attaching the turbomachine to the aircraft (2) and a linkage device (10) according to any one of the preceding claims.

9. Propulsion assembly (1) according to the preceding claim, characterized in that two second sealing elements (22) extend substantially on either side of the attachment mast (5).

10. Propulsive assembly (1) according to the preceding claim, characterized in that the second sealing elements (22) are arranged by analogy to the dial of a clock at Ih and 1 Ih respectively.

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