阅读说明：本技术 配备有突出的密封件的推力反向器门和包括该门的飞行器推进组件 (Thrust reverser door equipped with a projecting seal and aircraft propulsion assembly comprising such a door ) 是由 F·切林 G·克莱尔 G·加林多·费尔南德斯 于 2020-04-23 设计创作，主要内容包括：本发明涉及一种飞行器推进组件的推力反向器门,其包括定位在门的上游边缘(58)处的密封件(64)。该密封件(64)包括相对于门(56)的上游边缘(58)的突出部分(68)以及用于使突出部分(68)变硬的刚性芯(86)。这种配置使得可以减少空气动力干扰。本发明还涉及一种包括上述门的飞行器推进组件。(The invention relates to a thrust reverser door of an aircraft propulsion assembly, comprising a seal (64) positioned at an upstream edge (58) of the door. The seal (64) includes a projection (68) relative to the upstream edge (58) of the door (56) and a rigid core (86) for stiffening the projection (68). This configuration makes it possible to reduce aerodynamic interference. The invention also relates to an aircraft propulsion assembly comprising such a door.)

1. A thrust reverser door of an aircraft propulsion assembly, the door (56) being movable between a folded position in which the door (56) does not deflect airflow and an unfolded position in which the door (56) deflects airflow, the door (56) comprising:

a first face (56.1) in operational contact with the air flow, a second face (56.2) opposite the first face (56.1), and a first edge (58), the first edge (58) being configured to be able to be oriented towards a fixed portion (60) when the door (56) is in the folded position in operation, the door (56) comprising a seal (64) positioned at the level of the first edge (58), the seal (64) having a connecting area (80, 80') connected to the door (56) and a protruding portion (68) offset forward with respect to the first edge (58) when the door (56) is in the folded position, the protruding portion (68) extending the first face (56.1) of the door (56), characterized in that the seal (64) comprises a rigid core (86), the rigid core (86) being used to stiffen the protruding portion (68), the protruding portion (68) extends beyond the first edge (58) of the door (56).

2. The thrust reverser door according to claim 1, wherein the rigid core (86) comprises a first region (90.1) positioned in the protruding portion (68) of the seal (64) and a second region (90.2) positioned in the connecting region (80, 80') of the seal (64).

3. The thrust reverser door according to claim 1 or 2, wherein the rigid core (86) has a length and at least one non-constant structural feature over its entire length.

4. Thrust reverser door according to the preceding claim, wherein the rigid core (86) has at least one notch (96) extending from an upstream edge (88.1) of the rigid core (86).

5. The thrust reverser door according to the preceding claim, wherein the notches (96) have dimensions adjusted to vary the non-constant structural features of the rigid core (86).

6. The thrust reverser door according to one of claims 3 to 5, wherein the rigid core (86) has dimensions that are adjusted to vary the non-constant structural features of the rigid core (86).

7. The thrust reverser door according to any one of the preceding claims, wherein the seal (64) has a V-shaped segment with a tip (76), the V-shaped segment being formed by first and second branches (70,71), the first and second branches (70,71) having an engagement region (74), the engagement region (74) being offset upstream relative to the first edge (58) when the door (56) is in the folded position.

8. The thrust reverser door according to the preceding claim, wherein the first branch (70) comprises: a first portion (80) substantially linearly pressed against a second face (56.2) of the door (56), a second portion (82) substantially linearly over the extension of the door (56), a third portion (84) interposed between the second portion (82) and the tip (76) of the V-shaped segment.

9. The thrust reverser door according to the preceding claim, wherein the rigid core (86) does not extend at the bend of the second branch (71) and of the third portion (84) of the first branch (70).

10. The thrust reverser door according to anyone of claims 7 to 9, wherein the first branch (70) has a recess (78) for receiving a portion of the door (56) such that a first face (70.1) of the first branch (70) is in extension of the first face (56.1) of the door (56).

11. The thrust reverser door according to any one of the preceding claims, wherein the seal (64) is made of an elastomer and is molded on the rigid core (86).

12. A propulsion assembly comprising the thrust reverser door according to any one of the preceding claims.

Technical Field

The present application relates to a thrust reverser door equipped with a protruding seal and a propulsion assembly comprising the door.

Background

According to the embodiment visible in fig. 1 to 6, the aircraft 10 comprises a plurality of propulsion assemblies 12, these propulsion assemblies 12 being positioned below each wing 14 of the aircraft 10 and being connected with the wings of the aircraft 10 by wing struts 16. Each propulsion assembly 12 comprises an engine positioned as a turbojet engine. Inside the nacelle 18, the turbojet engine is connected to the wing strut 16 by engine accessories and comprises a jet engine 20 and a blower 22.

In the remainder of this description, the longitudinal direction is parallel to the axis of rotation a22 of the fan 22, while the radial direction is perpendicular to the axis of rotation a 22. The longitudinal plane is the plane containing the axis of rotation a22, while the transverse plane is the plane perpendicular to the axis of rotation a 22. The concepts forward/upstream and aft/downstream refer to the direction of airflow in the nacelle 18, which flows from forward (upstream) to aft (downstream).

The nacelle 18 has an approximately tubular shape and defines, with the jet engine 20, an annular duct 24. The nacelle 18 includes: an upstream segment 26, the upstream segment 26 being referred to as an air inlet and being positioned in front of the blower 22; an intermediate section 28, in which intermediate section 28 blower 22 is positioned; a downstream segment 30, having a trailing edge 32.

The nacelle 18 comprises a thrust reverser 34, which thrust reverser 34 is positioned at the level of the downstream section 30 and is configured to have an activated condition, in which the thrust reverser 34 deflects at least a portion of the airflow circulating in the annular duct 24 outside and before the nacelle 18, and an inactivated condition, in which the thrust reverser 34 partially deflects the airflow circulating in the annular duct 24.

The thrust reverser 34 comprises at least one movable portion 36, the movable portion 36 making it possible to create at least one lateral opening 38 (visible in fig. 4 and 6), the deflected airflow being directed towards this lateral opening 38.

According to one embodiment, the movable portion 36 is a tubular O-shaped cover that longitudinally translates between a closed position (visible in fig. 3 and 5) in which the movable portion 36 is in contact with the intermediate segment 28 when the thrust reverser 34 is in the inactive state, and an open position (visible in fig. 4 and 6). In the open position, the movable portion 36 moves away from the intermediate segment 28 when the thrust reverser 34 is in the activated state, thereby creating the lateral opening(s). The movable portion 36 includes an outer wall 40 and an inner wall 42 connected at the trailing edge 32, the inner and outer walls 40, 42 defining therebetween a cavity 44 that opens in the direction of the intermediate segment 28.

The thrust reverser 34 also includes: a door 46 configured to divert at least a portion of the airflow circulating in the annular duct 24 in the direction of the lateral opening 38; and a plurality of cascades 48 positioned at the level of the lateral openings 38 when the mobile portion 36 is in the open position and in the cavity 44 when the mobile portion 36 is in the closed position. The cascades 48 are distributed over the circumference of the nacelle 18 and are configured to control the direction of flow deflected by the door(s) 46.

Each door 46 is movable between a folded position (visible in fig. 5) in which the door 46 is pressed against the movable part when the thrust reverser is in the inactive condition and the movable part 36 is in the closed position, the door 46 extending through the toroidal tube 24 when the thrust reverser is in the active condition and the movable part 36 is in the open position, so that the unfolded position is visible in fig. 6. Deflecting at least a portion of the airflow circulating therein toward the lateral opening 38.

As shown in fig. 5 and 7, the intermediate segment 28 includes an inner wall 50 defining the annular duct 24 and having a trailing edge 50.1 with a double curvature, a first curvature in a transverse plane and a second curvature in a longitudinal plane (as shown in fig. 5-7). The rear edge 50.1 is configured to direct the airflow deflected by the door 46 towards the cascade 48.

Each door 46 provides some continuity between the inner wall 50 of the intermediate segment 28 and the inner wall 42 of the movable portion 36 when the doors 46 are in the folded position. The door 46 includes: a first face 46.1 oriented forward when the door 46 is in the deployed position and oriented toward the jet engine 20 when the door 46 is in the folded position, and a second face 46.2 oriented rearward when the door 46 is in the deployed position and oriented toward the active portion when the door 46 is in the folded position. The door 46 further comprises a first edge 46.3, the first edge 46.3 being oriented towards the front in the folded position and towards the movable portion 36 in the unfolded position.

Given the kinematics of the door 46 between the folded and unfolded positions in order to limit the risk of friction between the door 46 and the rear edge 50.1 of the intermediate section 28, the first edge 46.3 of the door and the rear edge 50.1 of the intermediate section 28 are spaced apart in the radial direction by a gap J when the door 46 is in the folded position, as shown in fig. 7. To reduce the gap J, the first edge 46.3 of the door 46 is slightly curved towards the outside of the nacelle 18.

In order to prevent the passage of the air flow between the door 46 and the movable portion 36, the door 46 comprises a seal 52 made of elastomer, which seal 52 is positioned against the second face 46.2 at the level of the first edge 46.3. In the transverse plane, the seal 52 has a U-shaped cross-section and comprises: a first leg 52.1 which is pressed against and fixed on the second face 46.2 of the door 46, a second leg 52.2 which contacts the rear edge 50.1 of the intermediate segment 28 when the door 46 is in the folded position, and a base 52.3 are oriented forwardly, set back with respect to the first edge 46.3 of the door.

This configuration of the first edge 46.3 of the door and the seal 52 produces a hollow shape 54 (delimited by a broken line in fig. 7) which extends over the entire circumference of the annular duct 24 and which generates aerodynamic disturbances which affect the fuel consumption of the aircraft.

According to one embodiment described in document GB2395175, the door of the thrust reverser comprises, at the level of its front edge, an element extending towards the front door. The element comprises a first region connected to the door and a second region in contact with the rear edge of the inner wall of the nacelle when the door is in the folded position. Even if this solution eliminates the hollow shape, it is not entirely satisfactory, since the seal must have a reduced length (dimension taken in the longitudinal direction). Therefore, the front edge of the door must be very close to the rear edge of the inner wall of the nacelle, which imposes a specific shape and/or kinematics on the door and the inner wall.

The present invention aims to remedy all or part of the disadvantages of the prior art.

Disclosure of Invention

To this end, the invention relates to a thrust reverser door for an aircraft propulsion assembly, the door being movable between a folded position, in which the door does not deflect an airflow, and an unfolded position, in which the door deflects an airflow, the door comprising: a first face in contact with the airflow in operation, a second face opposite the first face, and a first edge configured to be oriented towards the fixed portion when the door is in the folded position in operation, the door including a seal positioned at the level of the first edge, the seal having a connection region connected to the door and a protruding portion offset forward relative to the first edge when the door is in the folded position, the protruding portion extending the first face of the door.

According to the invention, the seal comprises a rigid core for stiffening the projecting portion, which extends partly beyond the first edge of the door.

The protruding portion of the seal may limit aerodynamic interference. In addition, the rigid core stiffens the protruding part of the seal, so that the first edge of the door can be spaced more from the fixed part than in prior art solutions.

According to another feature, the rigid core comprises a first zone positioned in the protruding portion of the seal and a second zone positioned in the connection zone of the seal.

According to another feature, the rigid core has a length and at least one non-constant structural feature over its entire length.

According to another feature, the rigid core has at least one notch extending from an upstream edge of the rigid core.

According to another feature, the recess has dimensions adjusted to vary the non-constant structural features of the rigid core.

According to another feature, the rigid core has dimensions that are adjusted to change the non-constant structural features of the rigid core.

According to another feature, the seal has a V-shaped segment with a tip, the V-shaped segment being formed by a first branch and a second branch, the first branch and the second branch having an engagement region that is offset upstream with respect to the first edge when the door is in the folded position.

According to another feature, the first branch comprises: a first portion substantially linearly pressed against the second face of the door, a second portion substantially linearly on the extension of the door, a third portion interposed between the second portion and the tip of the V-shaped segment.

According to another feature, the rigid core does not extend at the bend of the third portion of the second branch and the first branch.

According to another feature, the first branch has a recess for receiving a portion of the door, so that the first face of the first branch is in extension of the first face of the door.

According to another feature, the seal is made of elastomer and is moulded on the rigid core.

The invention also relates to a propulsion assembly comprising a thrust reverser door according to any one of the preceding features.

Drawings

Further features and advantages will emerge from the following description of the invention, given by way of example only and with reference to the accompanying drawings, in which:

figure 1 is a perspective view of an aircraft,

figure 2 is a perspective view of the propulsion assembly,

figure 3 is a side view of a propulsion assembly equipped with a thrust reverser in an inactive state,

fig. 4 is a side view of the propulsion assembly seen in fig. 3, with the thrust reverser in an activated state,

Fig. 5 is a longitudinal cross-section of a portion of the propulsion assembly visible in fig. 3, the thrust reverser being in an inactive state,

fig. 6 is a longitudinal cross-section of a portion of the propulsion assembly seen in fig. 3, the thrust reverser in an activated state,

fig. 7 is a longitudinal cross-section of a portion of the door of the thrust reverser visible in fig. 5, showing one embodiment of the prior art,

fig. 8 is a front view of a portion of the door of the thrust reverser visible in fig. 5, illustrating one embodiment of the invention,

fig. 9 is a longitudinal cross-section of a portion of the door of the thrust reverser visible in fig. 5, showing one embodiment of the invention,

fig. 10 is a cross-section of a seal of a thrust reverser door, illustrating one embodiment of the invention,

figure 11 is a rear view of the propulsion assembly of the aircraft,

fig. 12 is a perspective view of two doors and two rigid cores, respectively, of the thrust reverser, showing one embodiment,

FIG. 13 is a perspective view of a rigid core illustrating one embodiment of the present invention

FIG. 14 is a top view of a rigid core, illustrating one embodiment of the invention, an

FIG. 15 is a cross-section of a seal of a thrust reverser door illustrating another embodiment of the invention.

Detailed Description

In fig. 11, several doors 56 of the thrust reverser of the propulsion assembly of an aircraft are shown, which doors are distributed over the circumference of the propulsion assembly. According to the configuration visible in fig. 12, the doors may differ from each other according to their position in the circumferential direction of the propulsion assembly.

In fig. 8 and 9, a portion of the door 56 of the thrust reverser of the propulsion assembly has been shown. Other elements of the propulsion assembly are not described as they may be the same as prior art elements.

The door 56 includes: a first face 56.1, facing forward when the door 56 is in the deployed position, and facing the jet engine 20 when the door is in the folded position; and a second face 56.2 opposite the first face 56.1, oriented towards the rear when the door 46 is in the deployed position, and oriented towards the active portion when the door 46 is in the folded position. In operation, the first face 56.1 is in contact with the gas flow.

The door 46 also includes a first edge 58, the first edge 58 facing forward when it is in the folded position and facing the active portion when it is in the unfolded position.

According to one embodiment, the door 56 is in the form of a plate 59 having a thickness E at the level of the first edge 58.

When the door 56 is in the folded position, the first edge 58 is only slightly spaced from a fixed portion 60 having a double curvature, a first curvature in a transverse plane and a second curvature in a longitudinal plane (as shown in fig. 9). The fixed portion 60 corresponds to a rear edge of the middle section of the propulsion assembly and is configured to direct airflow deflected by the door 56 towards the cascade.

Given the kinematics of the door 56 between the folded position and the unfolded position in order to limit the risk of friction between the door 56 and the fixed portion 60, when the door is in the folded position as shown in fig. 9, the first edge 58 of the door 56 and the fixed portion 60 are radially spaced apart by a gap J and define a hollow shape 62 upstream of the door 56.

The door 56 includes a seal 64 positioned at the first edge 58 and connected to the door 56 by a fastening element 66. According to the configuration visible in fig. 8, the seal 64 extends over the entire length of the first edge 58 of the door 56.

The seal 64 includes a tab 68, the tab 68 being forwardly offset relative to the first edge 58 when the door 56 is in the folded position so as to extend the first face 56.1 of the door 56, the tab 68 being configured to at least fill the hollow shape 62 defined in part by the fixed portion 60 and the door 56. Thus, the protruding portion 68 makes it possible to limit the aerodynamic disturbances generated by the hollow shape 62 without the seal 64. The seal 64 reduces the gap between the door 56 and the cascade when the door 56 is in the deployed position.

According to the embodiment visible in fig. 9 and 10, the seal 64 has a V-shaped segment with a first branch 70 and a second branch 71, the first branch 70 being pressed against and fixed on the second face 56.2 of the door 56, the second branch 71 forming a contact area 72 with the fixed portion 60 when the door 56 is in the folded position. When the door 56 is in the folded position, the first and second branches 70, 71 have a junction area 74 that is offset forward relative to the first edge 58.

The V-shaped segment projection 68 has a pointed end 76.

The first branch 70 has a recess 78 configured to receive a portion of the door 56, more precisely the plate 59 of the door 56. Thus, the first leg 70 includes an outer surface 70.1 in the extension of the first face 56.1 of the door 56. This configuration may limit aerodynamic interference.

According to one configuration, at the level of the projecting portion 68, the first branch 70 comprises a first portion 80 substantially linearly pressed against the second face 56.2 of the door 56, a second portion 82 substantially linearly in the extension direction of the door 56 and a curved third portion 84 interposed between the second portion 82 and the tip 76 of the V-shaped segment, with a curvature towards the outside of the nacelle 18. This configuration may limit the risk of leakage between the seal 64 and the stationary portion 60.

To give an order of magnitude, the width L80 of the first portion 80 is substantially equal to the sum of the widths L82, L84 of the second and third portions 82, 84, and the width L82 of the second portion 82 is substantially equal to twice the width L84 of the third portion 84.

The present invention is not limited to V-shaped segments for the seal 64.

According to another embodiment, visible in fig. 15, the seal 64 is substantially flat and comprises: a connecting zone 80 'superimposed and connected to the door, and a projecting portion 68 having a contact zone 72' in contact with the fixed portion 60 when the door 56 is in the folded position.

Thus, regardless of the embodiment, the seal 64 includes a connection region 80, 80 'configured to connect to the door 56 and a projection 68 having a contact region 72, 72' that contacts the fixed member 60 when the door 56 is in the folded position.

According to another feature of the present invention, the seal 64 includes a rigid core 86 configured to stiffen the projection 68. According to one embodiment, the rigid core 86 is a metal blade (or foil) inserted in the first portion 70 and having a thickness of between 0.2mm and 1mm, preferably in the order of 2mm and 1mm, preferably 0.3 mm. According to one configuration, the rigid core 86 is embedded in the seal 64.

The rigid core 86 extends beyond the first edge 58 of the door 56 and makes it possible to increase the rigidity of the projection 68 of the seal 64. Thus, the first edge 58 of the door 56 may be spaced further from the fixed part 60 than in prior art solutions.

According to the embodiment visible in fig. 9 and 10, a rigid core 86 is inserted in the first branch 70 and extends over the first portion 80 and the second portion 82. The absence of the rigid core 86 in the second branch 71 and the third portion 84 allows the seal 64 to retain its ability to deform to match the geometry of the fixed portion 60.

According to the embodiment visible in fig. 15, the rigid core 86 is inserted in the connection zone 80' and in the protruding portion 68.

Regardless of the embodiment, the rigid core 86 is positioned in the protruding portion 68. According to certain embodiments, the rigid core 86 may extend at the level of the connection regions 80, 80'.

Each rigid core 86 includes an upstream edge 88.1 approximately perpendicular to the longitudinal direction and a downstream edge 88.2 approximately parallel to the upstream edge 88.1. In operation, the upstream edge 88.1 is oriented towards the fixed portion 60.

According to the configuration visible in fig. 13, the rigid core 86 comprises a first region 90.1, extending from the upstream edge 88.1, positioned in the protruding portion 68 of the seal 64, and a second region 90.2, extending from the downstream edge 88.2, positioned in the connecting region 80, 80' of the seal 64. The rigid core 86 has two fold lines 92, 92' which are substantially parallel to the upstream edge 88.1 and the downstream edge 88.2, separating the first region 90.1 and the second region 90.2, so that the rigid core 86 follows the contour of the seal 64.

According to one embodiment, the seal 64 is made of an elastomer and is molded over the rigid core 86.

In the rest of the description, the width of an element corresponds to the dimension of the element taken in the longitudinal direction, while the length of the element corresponds to the dimension taken in the circumferential direction.

According to an embodiment not shown, the rigid cores 86 of the seals 64 of different doors 56 are all identical.

According to another embodiment, visible in fig. 12, the first rigid core 86 of the first door 56 is different from the second rigid core 86 'of the second door 56'.

According to one embodiment, the rigid core 86 includes at least one feature that is not constant over its length. Thus, the rigid core 86 includes at least a first region 94.1 having at least one characteristic different from a characteristic of a second region 94.2, the first and second regions 94.1, 94.2 being offset lengthwise. According to one embodiment, the rigid core 86 has a curvature that may vary over its length.

According to the embodiment visible in fig. 12 to 14, the rigid core 86 comprises at least one notch 96 extending over a portion of the width of the rigid core 86. Each notch 96 extends in the longitudinal direction from the upstream edge 88.1.

Each notch 96 has a first dimension D1, D1 'taken along the width of the rigid core 86 and a second dimension D2, D2' taken along the length of the rigid core 86. Two consecutive notches 96 are separated by a third dimension D3, D3'.

Thus, the bending of the rigid core 86 can be adjusted by changing at least one of the first, second, and third dimensions of the notch 96. Of course, the present invention is not limited to this mode. This embodiment is used to vary the bending of the rigid core 86. Thus, the bending of the rigid core 86 may be adjusted by varying at least one dimension of the rigid core 86, in particular its width La, La' (as shown in fig. 14) or thickness E (as shown in fig. 13).

The fact that at least one characteristic of the rigid core 86 can be adjusted along its length enables at least one characteristic of the seal 64, in particular its flexibility, to be adjusted over its entire length.