Connection device providing a connection between annular elements of an aircraft propulsion unit, with sealing elements, and corresponding turbomachine

Abstract

The present invention relates to a connection device (10) for an aircraft propulsion unit, comprising a first element (11) of a fairing (9) and a second element (12) of a housing (7) centered on a longitudinal axis (X). The second element (12) includes a groove (13) extending about the longitudinal axis and receiving a first sealing element (17). The first element is rotatable relative to the housing between a closed position and an open position and includes a rib (20) that at least partially compresses the first sealing element (17) radially in the closed position. According to the invention, the connection device includes a second sealing element (22) 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 in a direction generally parallel to the longitudinal axis.

Description

Technical Field

[0001] This invention relates to the field of propulsion units, including aircraft turbines. More specifically, this invention relates to a connection device between a first element of a nacelle and a second annular element of a turbine casing surrounded by the nacelle. Background Technology

[0002] An aircraft propulsion unit typically includes a turbine with a casing and a nacelle. The casing, centered on a longitudinal axis, at least surrounds the turbine's combustion chamber, and the nacelle surrounds the casing. The propulsion unit includes a mounting bracket or gantry for suspending or mounting the turbine to the aircraft structure.

[0003] The nacelle may be equipped with a thrust reverser, comprising fairings in the form of half-shells or 360° annular fairings, which are movable relative to the hull and the rest of the nacelle. Each fairing is hinged at one end to a mounting bracket via one or more hinges or one or more sliders, the axis of which extends parallel to the longitudinal axis. The free end of one fairing engages with the free end of another fairing, and each fairing is connected to the hull to transfer aerodynamic forces (particularly axial forces) acting on each fairing to the hull.

[0004] The housing includes an annular groove with a V- or U-shaped cross-section centered on the longitudinal axis, and an O-ring seal is fitted at the bottom of the groove. The nacelle is equipped with ribs or protrusions whose shapes complement the shape of the groove, and are designed to engage with the groove when the fairing or each fairing is locked onto the housing. The ribs compress the O-ring seal, thereby ensuring the tightness of the assembly when the fairing or each fairing is closed and locked. The shape of the ribs also helps guide the closing of the fairing or each fairing. The connection between the groove and the rib is located near a hinge mounted on a mounting bracket. An example of such a propulsion unit is described in patent document FR-A1-2756323 (also published under US number 6032901), in which the connection between the groove and the rib compresses the O-ring seal.

[0005] However, because the nacelle and hull are constructed from different components or fairings, this can compromise sealing and affect the aerodynamic performance of the propulsion unit in multiple locations. In particular, leaks and fire risks can occur at the junction of the hull and nacelle, potentially reducing turbine performance. Furthermore, the complex shapes of the fairing and nacelle require precisely shaped seals to ensure continuous sealing and prevent damage when the fairing is closed.

[0006] Document US-A1-2016 / 017738 describes two elements fixed relative to each other. One element includes a groove in which a rib of the other element is received. A sealing gasket is also fitted in the groove, specifically positioned between the two elements to fill only the space formed between them. The rib does not compress the sealing gasket.

[0007] Document US-A1-2013 / 298524 describes two components with a sealing element disposed between their mating ends. The component does not have a groove for receiving the sealing element. A removable clamp is designed to cover the mating ends of the two components.

[0008] Therefore, it is necessary to address some or all of the aforementioned shortcomings. Summary of the Invention

[0009] The purpose of this invention is to provide a solution to minimize the risk of aerodynamic leakage and fire at the connection between at least one component of the movable fairing of the nacelle (only when the maintenance fairing is opened for maintenance operations) and the fixed component of the turbine housing.

[0010] According to the present invention, this objective is achieved by a connecting device for an aircraft propulsion unit, the connecting device comprising a first element of a fairing and a second element of a housing centered on a longitudinal axis, the second element including a groove extending at least partially around the longitudinal axis, the groove being open outward and having a bottom, the bottom having a first sealing element disposed therein, the first sealing element extending at least partially around the longitudinal axis, the first element being rotatable relative to the housing between a closed position and an open position, and the first element including a rib that, in the closed position, is capable of at least partially radially compressing the first sealing element relative to the longitudinal axis. The connecting device includes a second sealing element disposed between the first sealing element and the first element of the fairing at least in the closed position, the second sealing element being mounted to radially compress the first sealing element in the closed position in a direction generally parallel to the longitudinal axis.

[0011] Therefore, this solution achieves the aforementioned objectives. In particular, the installation of the second sealing element is used to strengthen and optimize the sealing, especially at the connection between the cowling and the housing in the closed position, to avoid increasing drag during turbine operation.

[0012] The connecting device further includes one or more of the following features, which can be used individually or in combination: - The groove includes a first wall and a second wall, which extend radially on one hand and at least partially around a longitudinal axis on the other hand. Each of the first wall and the second wall faces each other and is provided with a notch that extends along the longitudinal axis through the first wall and the second wall and into the groove. A second sealing element extends through the notch in the closed position.

[0013] - The second element includes a partition that extends in a direction generally transverse to the circumferential direction about the longitudinal axis, and the second sealing element is capable of tangentially abutting a contact surface in the closed position, the contact surface being defined in a generally radial plane.

[0014] - The rib includes a cutout extending laterally through the rib, and a second sealing element is mounted in the cutout by means of the complementary shape of the second sealing element and the cutout.

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

[0016] - The second sealing element is attached separately and is distinct from the rib.

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

[0018] The present invention relates to a propulsion unit comprising an aircraft turbine equipped with an annular housing, at least one fairing configured to be movable relative to the housing, a mounting bracket for mounting the turbine to the aircraft, and a connection device as described above.

[0019] An advantageous feature of this propulsion unit is that two second sealing elements extend approximately on both sides of the mounting bracket.

[0020] Another advantageous feature of this propulsion unit is that these second sealing elements are positioned at the 1 o'clock and 11 o'clock positions respectively, in analogy to the face of a clock.

[0021] The present invention also relates to an aircraft equipped with such a propulsion unit. Attached Figure Description

[0022] The invention will be better understood after reading the following detailed description of embodiments given by way of illustrative and non-limiting example only, with reference to the accompanying schematic diagrams, and other objects, details, features, and advantages of the invention will become clearer, wherein: - Figure 1 This is a radial sectional view of an example of a propulsion unit connected to the wing of an aircraft according to the present invention; - Figure 2 A schematic diagram of the connection device between the first element of the nacelle fairing and the second element of the stator housing according to the present invention is shown; - Figure 3This is a top-view transmission view of an example of a connecting device including a sealing element according to the present invention; - Figure 4 yes Figure 3 An axial sectional view of the connecting device shown; - Figure 5 yes Figure 3 The radial sectional view of the connecting device is shown in detail. - Figure 6 yes Figure 3 Front view of the connecting device shown; - Figure 7 This is a perspective view showing an example of the internal structure of a connecting device according to the present invention. Detailed Implementation

[0023] Figure 1 A propulsion unit 1 is shown, intended for arrangement on an aircraft 2 (e.g., an airplane). The propulsion unit 1 includes a turbine 3 having a longitudinal axis X and a nacelle 4 surrounding the turbine 3.

[0024] The propulsion unit 1 preferably includes a mounting frame 5 or pylon, known by the abbreviation "EMS" (i.e., "Engine Mounting Structure"), and is configured to connect the turbine 3 to one of the wings 6 of the aircraft 2. Ideally, the turbine 3 is suspended below the wing 6. In other configurations, the turbine 3 may be located above the wing 6 or at the rear of the fuselage.

[0025] Turbine 3 can be a turboprop engine with a ductless propeller, known by the English terms "open rotor" or "unducted fan" or "open fan," or the turbine can have two ductless, counter-rotating propellers (known by the abbreviation "UDF," meaning "Unducted Dual Fan"), or the turbine can have a single ductless propeller and a ductless rectifier comprising multiple stator blades (known by the abbreviation "USF," meaning "Unducted Single Fan"). Turbine 3 can also be a turbojet engine, particularly a twin-flow, twin-shaft engine, and include a fan.

[0026] This invention is generally applicable to turbines including ducted or unducted fans or propellers.

[0027] In this invention, generally speaking, the terms "upstream," "downstream," "axial," and "axially" are defined relative to the direction of gas flow within the turbine and relative to the longitudinal axis X of the turbine. Similarly, the terms "radial," "radially," "inner," "outer," "internal," and "external" are defined relative to the radial axis Z perpendicular to the longitudinal axis X and relative to the distance from the longitudinal axis X.

[0028] The turbine is equipped with a casing 7, particularly an outer casing, which surrounds and / or structurally supports at least a portion of the compressor assembly (not shown), combustion chamber (not shown), and turbine assembly (not shown) of the turbine 3. The casing 7 is centered on the longitudinal axis X.

[0029] The housing 7 extends downstream via a jet structure (not shown) or a jet nozzle, which is typically one of the components of the nacelle.

[0030] The nacelle 4, centered on the longitudinal axis X, surrounds the shell 7, thus forming an aerodynamic outer surface 8. The nacelle 4 advantageously includes a fairing 9 movable relative to the rest of the nacelle 4. These movable fairings 9 may be fan fairings, thrust reverser fairings, or maintenance fairings, providing access to certain turbine components for maintenance. Advantageously, the maintenance fairing does not have a thrust reverser and does not pivot during turbine operation. The maintenance fairing can be used to define the boundaries of the nacelle and guide secondary airflow (or external airflow). As is known, thrust reversers decelerate the aircraft by deflecting airflow (particularly secondary airflow) upstream.

[0031] In the case that turbine 3 is a turbojet engine, nacelle 4 defines the air inlet leading to the fan and includes, from upstream to downstream, a fan cowling, a thrust reversing device cowling or maintenance cowling, and a jet cowling or secondary jet nozzle.

[0032] The main airflow passes through the compressor assembly, combustion chamber, and turbine assembly via the main airflow channel (not shown). The secondary airflow flows around the main airflow channel.

[0033] Conveniently, each of the movable fairings 9 is shaped as a semi-shell or semi-cylinder. In other words, the fairings 9 are arranged on both sides of a radial plane passing through the mounting bracket 5. Other configurations for mounting the fairings are also possible.

[0034] like Figure 1As shown, each fairing 9 of the nacelle 4 is arranged to pivot about an axis A parallel to the longitudinal axis X between an open position and a closed position. Each fairing 9 includes an end 9a advantageously hinged to the mounting bracket 5. Pivoting can be achieved using a known hinge system (not shown). Each fairing 9 includes a free end 9b, which is advantageously designed to engage with the free end 9b of the opposite fairing 9 when the fairing 9 is closed. Alternatively, each free end 9b of the fairing is locked to the housing 7. For this purpose, a locking mechanism (not shown) is provided, which includes, for example, a latch.

[0035] Figure 2 A connection device 10 is shown between the first element 11 of the fairing 9 of the nacelle 4 and the second element 12 of the housing 7. Advantageously, but not exclusively, a connection device 10 is present between each fairing and the housing 7. Preferably, this connection device 10, or each connection device 10, is arranged close to the mounting bracket 5.

[0036] The second element 12 includes a groove 13 that extends at least partially around a longitudinal axis X. The groove 13 is U-shaped or V-shaped and preferably opens radially outward. Advantageously, the groove 13 includes a first wall 14 and a second wall 15, each of which extends at least partially around the longitudinal axis X on one side and radially on the other. Each first wall 14 and second wall 15 is arranged opposite to each other.

[0037] In one embodiment, the two groove portions ( Figure 2 , Figure 3 , Figure 4 and Figure 7 (Only one of them is shown) extends on both sides of a radial plane containing the longitudinal axis X and in a sector (analogous to a clock face) between 12 o'clock and 6 o'clock. Advantageously, but not exclusively, there are no recessed portions in the sectors at the 6 o'clock and 12 o'clock positions and in the sector between 10° and 20° around the longitudinal axis X. In other words, the recess 13 is not 360° annular. Advantageously, but not exclusively, the mounting bracket 5 separates the two recessed portions 13 around the longitudinal axis X. Each recessed portion includes, for example, a first wall 14 and a second wall 15 extending on both sides of the mounting bracket 5.

[0038] Each recess 13 or a portion thereof includes a bottom 16 in which a first sealing element 17 is disposed. The bottom 16 is connected to a first wall 14 and a second wall 15 rising from the bottom. The first sealing element 17 extends at least partially around a longitudinal axis X.

[0039] Advantageously, each recessed portion is provided with a first sealing element 17. Advantageously, but not exclusively, the length of each first sealing element 17 is approximately equal to the length of the recessed portion.

[0040] In the remainder of this specification, the term “groove” is used to refer to a groove or a portion thereof.

[0041] The first sealing element 17 is preferably an O-ring centered on the longitudinal axis X. The first sealing element is made of, for example, an elastomeric polymer, a thermoplastic polymer, or a thermoplastic elastomer. Ideally, the material should be rubber.

[0042] Preferably, the first sealing element 17 is fixed to the bottom of the groove 13, for example, by adhesive bonding.

[0043] The first element 11 of the fairing 9 is rotatable or pivotable relative to the housing 7 about the longitudinal axis X. The first element 11 advantageously includes a rib 20 (referred to as a "blade") that can be positioned opposite a portion of the first sealing element 17.

[0044] Advantageously, rib 20 extends from the inner surface 21 of the fairing 9. Preferably, when the fairing 9 (or the first element 11) is in the closed position, rib 20 radially compresses the first sealing element 17. For this purpose, rib 20 engages within the groove 13 by virtue of its complementary shape to the groove 13. Advantageously, but not exclusively, rib 20 has a shape complementary to the shape of the groove 13.

[0045] like Figure 2 As shown, the second wall 15 includes a flat inner surface 15a defined in a radial plane, and the flat surface 20a of the rib 20 contacts the inner surface 15a. The first wall 14 includes a flat inner surface 14a, for example defined in a plane inclined relative to the radial axis, and the flat surface 20b of the rib 20 contacts the inner surface 14a.

[0046] The installation of this sealing element 17 and the interlocking of the rib 20 and the groove 13 ensure fluid (especially air) sealing between each fairing 9 and the housing 7, particularly in the closed position.

[0047] refer to Figure 3 and Figure 4 The connecting device 10 includes at least one second sealing element 22, which is configured to provide a continuous seal at the recess. Advantageously, particularly at least in the closed position, the second sealing element is at least partially radially positioned between the first element 11 and the first sealing element 17 of the fairing 9. Advantageously, the second sealing element 22 is mounted to compress the first sealing element 17 in the closed position. In one embodiment, when the first sealing element 17 is compressed, the second sealing element 22 extends at least partially into the recess 13.

[0048] Preferably, the second sealing element 22 extends at least partially in the groove 13 in a direction generally parallel to the longitudinal axis X. In particular, the direction of the second sealing element 22 is parallel to the longitudinal axis X or inclined relative to the longitudinal axis X.

[0049] Each of the first wall 14 and the second wall 15 is provided with a notch 23 extending along the longitudinal axis X through the first and second walls and into the groove 13. Advantageously, but not exclusively, the notch 23 is open outward and opens to the free edges 13a of the first and second walls of the groove 13. A second sealing element 22 extends through the notch 23. Thus, the second sealing element 22 extends continuously along the groove 13, preferably extending on both sides of the groove 13 (along the longitudinal axis X), thereby optimizing the hermetic seal. In particular, the second sealing element 22 is positioned inside the groove 13 only between the notches 23 when the fairing 9 is in the closed position.

[0050] The notch 23 is shaped to allow the second sealing element 22 to pass through, and may be, for example, U-shaped, V-shaped, or C-shaped. Since the second sealing element 22 is continuous here, it can provide a seal in other areas of the nacelle 4 and the shell 7 without compromising the tightness.

[0051] In one embodiment, the second sealing element 22 is continuous and extends on both sides of the mounting bracket 5 between a first end and a second end. The first and second ends are connected to the mounting bracket 5 and extend along the longitudinal axis X. The second sealing element 22 includes a first radial portion connected to the first and second ends, which extends in a radial direction. Each first radial portion is then connected to a second portion extending in a circumferential direction (around the longitudinal axis), which is connected to a third portion passing through the groove 13 along the longitudinal axis X. Each third portion passing through the groove 13 is connected to a fourth arcuate portion extending in a circumferential direction.

[0052] Based on advantageous features, especially Figure 5 and Figure 6 As shown, rib 20 includes a cut 24 that extends from one side to the other and through the wall of rib 20 in a transverse direction relative to the elongation direction of rib 20. The elongation direction of the rib is parallel to the longitudinal X direction in the closed position. A second sealing element 22 is advantageously mounted in the cut 23.

[0053] In this embodiment, the cutout 24 is U-shaped, C-shaped, V-shaped, or any other shape, as long as the shape allows for the installation of the second sealing element 22.

[0054] The second sealing element 22 preferably has a shape that is substantially complementary to the shape of the cutout 24, or has at least a portion of a shape that is substantially complementary to the shape of the cutout.

[0055] Each cut 24 opens inward (especially in the closed position, it opens towards the longitudinal axis X). The opening of the cut 24 leads, for example, to the inner edge 25 of the rib 20.

[0056] The second sealing element 22 has a lower surface 26 flush with the inner edge 25 of the rib 20. The lower surface 26 contacts the first sealing element 17 in the closed position. The inner edge 25 of the rib 20 contacts the first sealing element 17. The second sealing element 22 fills the missing portion (at the cutout 24) and helps to ensure a continuous seal between the rib 20 and the groove 13.

[0057] Advantageously, the second sealing element 22 is made of an elastomeric polymer, a thermoplastic polymer, or a thermoplastic elastomer. Preferably, the second sealing element 22 is made of rubber. This type of material is very economical and can be used to manufacture complex shapes. Alternatively, the second sealing element 22 is made of a composite material. The composite material may contain fibers (e.g., glass fibers) that provide additional properties such as fire resistance. In yet another alternative, the second sealing element 22 is made of a material similar to or compatible with the material of the first sealing element 17.

[0058] In one embodiment, the second sealing element 22 is in the shape of a parallelepiped. This design is easy to manufacture and ensures better contact with the first sealing element 17, thereby achieving a better seal.

[0059] In an advantageous embodiment, the second sealing element 22 is carried by the annular element 11 of the fairing 9. Specifically, the second sealing element 22 is secured to the annular element. This securing can be permanent or removable. The securing of the second sealing element 22 to the fairing 9 is achieved, for example, by gluing, snap-fitting, or molding. Securing the second sealing element 22 to the fairing makes it easier to close the fairing and, particularly, reduces any gaps between the fairing 9 and the second sealing element 22 when the fairing 9 is open.

[0060] 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 installation is easier due to fewer steps required. The materials used for the two integral sealing elements 17, 22 can be different and / or have different properties.

[0061] In another alternative, the second sealing element 22 is separate from the fairing 9 and the first sealing element 17. In other words, the second sealing element 22 is an additional component. This design simplifies the manufacturing process and allows for the replacement of the second sealing element if it is damaged.

[0062] refer to Figure 7The first element 11 of the fairing 9 includes a support 30, which reinforces the retention of the second sealing element 22 as it extends and guides the second sealing element. The support 30 extends laterally from the outer surface 27 of the rib 20 on both sides of the cutout 24. In this embodiment, the support 30 has an L-shaped radial cross-section. The second sealing element 22 is secured to and / or abuts against the support 30. Securing can be achieved, for example, by gluing, molding, or snap-fitting.

[0063] As another advantageous feature, the second element 12 of the housing 7 includes a partition 31 that extends generally transversely to the circumferential direction about the longitudinal axis X. In particular, the partition 31 includes an abutment surface 32 defined in a plane that is radially or inclined relative to the radial axis. The partition 31 also extends along the longitudinal axis X to a considerable extent (e.g., + / - 20°).

[0064] Advantageously, but not exclusively, the second sealing element 22 abuts tangentially against the abutment surface of the first element 11. Ideally, this abutment surface should be the abutment surface of the partition 31. Advantageously, the first side 33 of the second sealing element 22 forms a planar contact connection with the abutment surface 32. In this embodiment example, the first side 33 is opposite to the second side 34, and the second side 34 is integral with the wall of the support member 30.

[0065] The second sealing element 22 ensures a seal in both the radial and tangential directions through contact with the first sealing element 17 and the abutment surface 32. The second sealing element 22 is pressed against the partition 31 and the first sealing element 17.

[0066] In embodiments not shown, the second sealing element 22 may include a flange or extension extending from edge 26 to increase the contact area with the first sealing element 17.

[0067] In one embodiment, analogous to a clock face, the second sealing element 22 is positioned at approximately the 1 o'clock position. This position is, for example, at... Figure 1 The second sealing element is indicated by a dashed circle. Analogous to a clock face, the second sealing element is positioned at the 11 o'clock position (opposite to the position at 2 o'clock). In other words, the recess 13 has notches 23 located at approximately the 1 o'clock and 11 o'clock positions on the clock face.

Claims

1. A connection device (10) for an aircraft propulsion unit, comprising a first element (11) of a fairing (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), opening outward and having a bottom (16) therein 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 the first element comprising a rib (20) capable of at least partially compressing the first sealing element (17) radially relative to the longitudinal axis (X) in the closed position. Its features are, The connecting device (10) includes a second sealing element (22) disposed at least in the closed position between the first sealing element (17) and the first element (11) of the fairing (9), the second sealing element (22) being mounted in the closed position to radially compress the first sealing element (17) in a direction generally parallel to the longitudinal axis (X).

2. The connecting device (10) according to claim 1, characterized in that, The groove (13) includes a first wall (14) and a second wall (15), which extend radially on one hand and at least partially around the longitudinal axis (X) on the other hand. Each of the first wall (14) and the second wall (15) is opposite to each other and is provided with a notch (23) that extends along the longitudinal axis (X) through the first wall and the second wall and into the groove (13). The second sealing element (22) extends through the notch (23) in the closed position.

3. The connecting device (10) according to claim 1 or 2, characterized in that, The second element (12) includes a partition (31) extending in a direction generally transverse to the circumferential direction around the longitudinal axis (X), and the second sealing element (22) is adapted to tangentially abut against an abutment surface (32) in the closed position, the abutment surface being defined in a generally radial plane.

4. The connecting device (10) according to any one of the preceding claims, characterized in that, The rib (20) includes a cutout (24) extending laterally through the rib, and the second sealing element (22) is mounted in the cutout by means of the complementary shape of the second sealing element and the cutout.

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

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

7. The 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 as a single piece.

8. A propulsion unit (1) comprising an aircraft turbine (1) equipped with an annular housing (7), at least one fairing (9) configured to be movable relative to the housing (7), a mounting bracket (5) for mounting the turbine on the aircraft (2), and a connecting device (10) according to any of the preceding claims.

9. The propulsion unit (1) according to the preceding claim, characterized in that, Two second sealing elements (22) extend approximately on both sides of the mounting bracket (5).

10. The propulsion unit (1) according to the preceding claim, characterized in that, These second sealing elements (22) are positioned at the 1 o'clock and 11 o'clock positions respectively, in analogy to the clock face.

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