A thrust reverser comprising at least one deployable membrane and a membrane deployment member arranged in a cavity of a movable blocker door

Abstract

The present invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a movable structure (29) including at least one reverser housing (33) having a cavity (54) open in an upstream direction and defined between a radially outer wall (50) and a radially inner wall (52) of the reverser housing (33). The reverser further includes a membrane (58) for blocking a secondary flow channel (21B) and a membrane deployment member (62) connected to the membrane (58), the membrane deployment member being designed to be at least partially disposed in the secondary flow channel (21B) when the movable structure occupies its retracted thrust reverse position. According to the invention, when the movable structure (29) occupies its forward direct thrust position, the membrane deployment member (62) is at least partially accommodated in the cavity (54) of the movable reverser housing (33).

Description

Technical Field

[0001] This invention relates to the field of pods and thrust reversers for aircraft propulsion components, and more specifically, to thrust reversers equipped with deployable membranes to block secondary flow channels. Background Technology

[0002] A thrust reverser is a device that deflects airflow through the propulsion assembly forward, thereby shortening the landing distance and limiting the load on the brakes on the landing gear.

[0003] Currently, blade-type thrust reversers used in the aerospace industry include deflecting blades integrated into a fixed or movable structure of the reverser. The movable structure of the reverser includes one or more movable reverser shrouds, and is translated relative to the fixed structure between an advancing direct thrust position and a retracted thrust reversing position.

[0004] In the retracted thrust-reversing position, in order to deflect at least a portion of the secondary flow toward the cascade, the reverser is typically equipped with a baffle that, when deployed, at least partially blocks the secondary flow path. In a known manner, this forces air from the secondary flow radially outward toward the cascade, thereby generating a forward reverse thrust flow.

[0005] These baffles are typically pivotally mounted on the radially inner wall of a movable reverser housing that defines the secondary flow path radially outward. Therefore, grooves are provided in the radially inner wall of the reverser housing to accommodate the flow-restricting baffles in the retracted position, as is used in direct injection. However, in direct injection, the presence of these grooves and baffles is a source of aerodynamic interference on the secondary flow. Furthermore, this presence locally limits the mounting of acoustic panels on the radially inner wall of the reverser housing.

[0006] To provide technical solutions to these problems, it has been proposed to replace these baffles with one or more deployable membranes for blocking secondary flow channels. Such a design is known, for example, from document FR3076864A1.

[0007] However, it is necessary to optimize the design methods that allow the deployment of the blocking film in the secondary flow channel. In practice, the main idea is to use a connecting rod for film deployment, which is hinged to the internal radial boundary wall of the secondary flow channel, thus creating disturbances in the secondary flow in a direct injection configuration. Summary of the Invention

[0008] To at least partially satisfy the above-mentioned requirements, a first object of the present invention is to provide a thrust reverser for an aircraft propulsion assembly, the reverser comprising a fixed structure equipped with a radially inner wall for defining a secondary flow path through which a secondary flow passes, the reverser further comprising a movable structure including at least one reverser shroud having an upstream opening and a cavity defined between a radially outer wall and a radially inner wall of the reverser shroud, the movable structure being translatable relative to the fixed structure along the longitudinal central axis of the reverser between an advancing direct thrust position and a retracted thrust reverse position, in which the retracted thrust reverse position exposes an upstream channel opening of the reverser shroud toward a secondary flow path of an airflow deflection member, the reverser further comprising a membrane for blocking the secondary flow path, and a membrane deployment member connected to the membrane, the membrane deployment member being designed to be at least partially disposed in the secondary flow path when the movable structure occupies its retracted thrust reverse position. According to the invention, when the movable structure occupies the direct thrust position of its forward movement, the membrane deployment member in the form of a linkage is at least partially housed in the cavity of the movable reversing cover.

[0009] Utilizing this unique design of the present invention, in the direct injection configuration, the secondary flow is no longer subject to aerodynamic interference from membrane deployment components, such as linkages, because these components are housed within a movable reversing shroud. This results in a significant improvement in the overall performance of the propulsion system, corresponding to technological research aimed at significantly enhancing aircraft performance, and in this sense, contributing to reducing the environmental impact (decarbonization) of these aircraft.

[0010] The present invention preferably provides at least one of the following optional technical features, which may be used alone or in combination.

[0011] Preferably, the reverser is designed such that when the movable structure moves from its forward direct thrust position to its retracted thrust reverse position, the membrane deployment member is extracted from the cavity through the upstream opening of the cavity.

[0012] Preferably, the membrane unfolding member is a connecting rod, and the connecting rod is selected from:

[0013] - Straight connecting rod;

[0014] - Bent connecting rods, such as roughly C-shaped or S-shaped;

[0015] - A telescopic rod, preferably associated with a control system including an actuating spring and a control cable for deploying the spring.

[0016] Preferably, the membrane deployment member includes an end, which is hinged to the fixing structure of the reversing device, and preferably hinged to the rear support frame of the airflow deflection member.

[0017] Preferably, the membrane deployment member is connected to the upstream end of the radially inner wall and is hinged to the upstream end via at least one connector. Preferably, the deployment member is slidably mounted on the connector along a hinge axis having a tangential or substantially tangential orientation, preferably via a guide rail-shaped portion that mates with the connector. The combination of the two movements allowed by the aforementioned member ensures that the deployment member is drawn upstream from the cavity of the movable cover and extends radially inward into the secondary flow channel.

[0018] According to another possibility, the reverser includes a guiding system for the linkage deployment member, which includes a radially inward guide, preferably mounted on the radially inner wall of the movable reverser housing, and a radially outward guide, preferably mounted on the radially outer wall of the movable reverser housing, with the radially inner guide preferably positioned upstream of the radially outer guide. In this solution, it is precisely these two guides, through their positioning and the fact that they follow the movement of the movable housing, that enable the deployment member to be forced out of the cavity of the movable housing while tilting to extend radially inward into the secondary flow channel.

[0019] Preferably, the reversing device includes at least one spring for assisting the movement of the membrane deployment member in the flow channel, and / or, it includes at least one displacement-end damping spring for damping the deployment member (62) when the movable structure moves from its forward direct thrust position to its retracted thrust reverse position. The type and location of these springs can vary, for example, they can be disposed on the movable structure or a fixed structure, such as on the rear frame of the blade support.

[0020] Preferably, the airflow deflector includes a membrane that can be deployed via a link, and the reverser includes a stop for the link, which is preferably arranged on the radial outer wall of the movable reverser cover, or for example, on the rear support frame of the airflow deflector.

[0021] Preferably, the reverser includes a stop for the membrane unfolding member, which is preferably arranged on the radial outer wall of the movable reverser cover.

[0022] Finally, the present invention relates to a pod for an aircraft propulsion assembly, comprising at least one fan shroud and a thrust reverser as described above.

[0023] Other advantages and features of the invention will become apparent in the following non-limiting detailed description. Attached Figure Description

[0024] The following detailed description refers to the accompanying drawings, in which:

[0025] Figure 1 This is a schematic semi-longitudinal sectional view of a propulsion assembly, which includes a thrust reverser shown in a direct thrust configuration;

[0026] Figure 2 According to a preferred embodiment of the present invention, it is equipped with Figure 1 A schematic half-longitudinal sectional view of the reverser of the propulsion assembly shown, wherein the reverser is shown in a direct thrust configuration;

[0027] Figure 2A yes Figure 2 A three-dimensional view of a portion of the inverter shown;

[0028] Figure 3 Is with Figure 2 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in an intermediate configuration between a direct thrust configuration and a reverse thrust configuration;

[0029] Figure 3A yes Figure 3 A three-dimensional view of a portion of the inverter shown;

[0030] Figure 4 Is with Figure 2 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in a thrust-reversing configuration;

[0031] Figure 4A yes Figure 4 A three-dimensional view of a portion of the inverter shown;

[0032] Figure 5 yes Figure 2A An enlarged 3D view of a portion of the inverter shown;

[0033] Figure 6 This is an enlarged perspective view of the connecting rod used to deploy the secondary flow channel blocking membrane in the aforementioned reverser shown in the attached figure.

[0034] Figure 7 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is in the form of an alternative embodiment;

[0035] Figure 7A Is with Figure 7 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in an intermediate configuration between a direct thrust configuration and a reverse thrust configuration;

[0036] Figure 8 Is with Figure 3 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is in the form of an alternative embodiment;

[0037] Figure 9 Is with Figure 8 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is in the form of an alternative embodiment;

[0038] Figure 10 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is in the form of an alternative embodiment;

[0039] Figure 10A Is with Figure 10 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in an intermediate configuration between a direct thrust configuration and a reverse thrust configuration;

[0040] Figure 11 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is in the form of an alternative embodiment;

[0041] Figure 11A Is with Figure 11 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in a thrust-reversing configuration;

[0042] Figure 12 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is another preferred embodiment of the invention;

[0043] Figure 12A Is with Figure 12 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in a thrust-reversing configuration;

[0044] Figure 13 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is another preferred embodiment of the invention;

[0045] Figure 13A Is with Figure 13 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in an intermediate configuration between a direct thrust configuration and a reverse thrust configuration;

[0046] Figure 14 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is another preferred embodiment of the invention;

[0047] Figure 14A Is with Figure 14 A schematic half-longitudinal sectional view of a similar reverser, wherein the reverser is shown in a thrust-reversing configuration;

[0048] Figure 15 Is with Figure 2 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is another preferred embodiment of the invention;

[0049] Figure 16 Is with Figure 15 A schematic half-longitudinal sectional view of a similar inverter, wherein the inverter is another embodiment. Detailed Implementation

[0050] Figure 1 The image shows the aircraft propulsion assembly 1, which has a longitudinal central axis A1.

[0051] Next, the terms "upstream" and "downstream" are defined relative to the overall flow direction S1 of the gas along axis A1 through propulsion assembly 1 when generating thrust. These terms "upstream" and "downstream" can be replaced by the terms "front" and "rear," respectively, with the same meaning.

[0052] The propulsion assembly 1 includes a turbine 2, a pod 3, and a pylon (not shown) designed to connect the propulsion assembly 1 to the wing (not shown) of the aircraft.

[0053] In this example, turbine 2 is a ducted twin-rotor turbojet engine, comprising, from front to rear, a fan 5, a low-pressure compressor 6, a high-pressure compressor 7, a combustion chamber 8, a high-pressure turbine 9, and a low-pressure turbine 10. Compressors 6 and 7, combustion chamber 8, and turbines 9 and 10 form a gas generator. Turbojet engine 2 is provided with a fan casing 11 connected to the gas generator via a structural arm 12.

[0054] The pod 3 includes a front section forming an air inlet 13, a middle section including two fan shrouds 14 surrounding the fan casing 11, and a rear section 15.

[0055] During operation, airflow 20 enters the propulsion assembly 1 through inlet 13, passes through fan 5, and then splits into a main flow 20A and a secondary flow 20B. Main flow 20A flows into the main flow circulation channel 21A passing through the gas generator. Secondary flow 20B flows into the secondary flow channel 21B surrounding the gas generator. The secondary flow channel 21B is defined radially inward by a fixed inner shroud surrounding the gas generator. In this example, the fixed inner shroud includes a first segment 17 belonging to the middle segment 14 and a second segment 18 extending rearward from the first segment 17 to form part of the rear segment 15. The second segment 18 is part of the fixed structure of the thrust reverser, which will be described below. The same segment is hereinafter referred to as the radial inner wall 18 defining the secondary flow channel 21B.

[0056] Radially outward, the secondary flow channel 21B is defined by the fan casing 11, and... Figure 1In this configuration, one or more movable inverter covers 33, which will be described later, define the rear section 15 of the pod 3. More specifically, a housing 40 of an intermediate housing 42 is disposed between the fan housing 11 and the inverter covers 33, the latter including the aforementioned structural arm 12, the radially outer end of which is attached to the housing 40. Thus, the latter also participates in radially outwardly defining the secondary flow channel 21B by being configured as an axial extension downstream of the fan housing 11.

[0057] Therefore, the pod 3 includes a thrust reverser 30 centered on axis A1, and on one hand includes a fixed structure 31 integral with the fan casing 11, and on the other hand includes a structure 29 movable relative to the fixed structure 31. For example, the fixed structure 31 includes a front frame 46 that securely connects the fixed structure 31 to the fan casing 11, preferably via a knife-edge assembly located downstream of the casing 11. The front frame 46 includes a contoured aerodynamic portion called a deflection edge 46B, which guides the reverse jet flow.

[0058] Here, the fixed structure 31 also includes a plurality of deflecting vanes 32 arranged adjacent to each other around axis A1 and along the circumferential direction of the reverser 30 and the propulsion assembly 1. Thus, these vanes 32 form airflow deflection members for generating reverse thrust. In this respect, it should be noted that this airflow reversing function can be performed alternatively or simultaneously using flexible structures such as membranes / fabrics, as will be described later in other preferred embodiments of the invention.

[0059] Furthermore, the movable structure 29 includes the aforementioned movable reverser cover 33, for example, two covers 33, each extending to cover an angular amplitude of approximately 180°. This configuration with two covers 33 is particularly suitable for pod designs where the cover / wall 18 is also hinged, and the reverser 30 has a so-called "D-duct" structure. In this structure, the covers 18 and 33 are connected to allow simultaneous opening / closing during engine maintenance operations. However, other structures are also possible, such as the so-called "C-duct" or "O-duct" structures.

[0060] Each movable reverser housing 33 includes a radially outer wall 50 that forms the external aerodynamic surface of the thrust reverser and pod, which is in close contact with the outside air. Each housing 33 also includes a radially inner wall 52 that participates in defining the secondary flow path 21B radially outward. This wall 52 is located in the downstream continuation of the outer shell 40 of the intermediate casing. The two walls 50, 52 define a cavity 54, which preferably opens axially at the upstream end of the reverser housing 33.

[0061] Figure 1The reverser 30 is shown in a forward direct thrust configuration, referred to as "direct injection," which corresponds to the standard flight configuration. In this configuration, the shrouds 33 of the movable structure 29 are in a closed position, referred to as the forward thrust or "direct injection" position, in which the reverser shrouds 33 abut against the fixed structure 31, particularly against the deflection edge 46B that forms an integral part of the latter. In fact, in the direct thrust configuration, the upstream end 52a of the radial inner wall 52 of each shroud 33 axially abuts against the deflection edge 46B, thereby isolating the cavity 54 from the secondary flow path.

[0062] The retention of the movable cover 33 in the forward direct thrust position is ensured by means of a device for locking the cover onto the fixed structure 31 of the reverser. These controlled locking devices (not shown) are conventional and will not be described further. As an example, an active latch capable of unlocking under load can be used to counteract the compressive force of the seal between the movable structure and the deflection edge. This type of latch can over-compress the seal, allowing unlocking to be controlled.

[0063] Therefore, the movable structure 29 relative to the fixed structure 31 along the axis A1 of the inverter is as follows: Figure 1 The forward direct thrust position shown is translatably movable between the retracted thrust reversal position, which will be described below. When the movable structure 29 is in the forward direct thrust position, the deflector cascade 32 is arranged in the cavity 54 of the reverser shroud 33, isolated from the secondary flow channel 21B by the radial inner wall 52 of these sliding reverser shrouds 29. This wall 52 forms the outer wall of the secondary flow channel, also referred to as the acoustic inner plate.

[0064] This direct thrust configuration also Figure 2 and Figure 2A As shown, the retraction thrust of the movable structure 29 is in the opposite position. Figure 4 and Figure 4A As shown in the image. Figure 3 and Figure 3A The movable structure is shown in an intermediate position between the forward direct thrust position and the retracted thrust reverse position.

[0065] exist Figure 4The diagram shows the retracted internal acoustic panel 52 of the reverser shroud exposing, upstream, a channel opening 56 of the secondary flow channel 21B toward the deflector cascade 32. Thus, the opening 56 is also defined upstream by a deflection edge 46B that flares radially outward toward the rear to guide airflow intended to pass through the cascade 32 when the movable system is in the retracted thrust-reversed position. In other words, the deflection edge 46B gradually moves away from axis A1 as it moves rearward to guide / deflect airflow toward the cascade 32 in the thrust-reversed configuration. Downstream, the channel opening 56 is specifically defined by the upstream end 52a of the radially inner wall 52.

[0066] To deflect at least a portion of the secondary flow 20B toward a channel opening 56 axially defined between the deflection edge 46B and the upstream end 52a of the radial inner wall 52 of each shroud 33, the reverser 30 includes one or more blocking membranes 58. An embodiment will now be described in which a single membrane 58 is associated with each reverser shroud 33 having the same or similar angular amplitude; however, it is still possible to consider multiple circumferentially adjacent membranes associated with each shroud 33. Similarly, the fit between the membrane 58 and its associated shroud 33 will be described below only, and it should be understood that such fit is the same or similar for all shrouds 33 of the reverser. However, it should be noted that in addition to the possibility of providing multiple membranes 58, one or more more conventional rigid flow-blocking baffles, such as those alternating in the circumferential direction, can also be provided in combination with this / these membranes.

[0067] Membrane 58 can be made from materials known to those skilled in the art for such applications. For example, it can be an unimpregnated fabric, such as aramid fibers. Membrane 58 can also be made from composite materials with a particularly flexible matrix, such as aliphatic polyurethane, which allows for use under varying temperature conditions, particularly at lower temperatures in the case of aliphatic polyurethane membranes than in the case of silicone membranes. The matrix provides low flexural strength, and the resulting structure behaves exactly like a membrane. One of the key characteristics of membrane 58 is that it can be folded in a fully reversible manner (elastically or by fiber sliding) with a very small radius of curvature relative to its surface, and it has a very small thickness, for example, in the range of 0.1 mm to 3 mm. For reference, the behavior of membrane 58 under pressure is observed to resemble that of a sail or parachute / wing.

[0068] It should be noted that in conventional blade-type reversers, the movable structure slides relative to the fixed structure via a track / sliding system. During the reverser's opening phase, the movable structure is guided from front to back, and during the closing phase, it is guided from back to front. Therefore, the rearward force applied to the movable structure of the reverser causes it to move rearward relative to the fixed structure. This force is typically generated by conventional actuators such as cylinders or ball screws.

[0069] Still referring to the preferred embodiments of the present invention Figures 1 to 4A The membrane 58 has two opposing ends: a first end 58a connected to one or more deployment members 62 near the rear frame 60 supporting the blade cascade 32, and a second end 58b also connected to the deployment members 62 and positioned near the wall 18 in a thrust reversal configuration. In this respect, it should be noted that the membrane 58 may be attached to each deployment member 62 only at its two ends 58a, 58b, or may be attached to the member 62 in a point-like or continuous manner along the entire length of the membrane. Alternatively, the first end 58a of the membrane 58 may be connected to the rear frame 60 supporting the blade cascade 32 without departing from the scope of the invention. The support is annular, or in the form of annular segments, effectively connecting the rear ends of multiple adjacent blade cascades.

[0070] In this preferred embodiment, the deploying element 62, which is at least partially arranged in the secondary channel 21B in the thrust reversal configuration, takes the form of a linkage, here a simple, preferably straight linkage. As previously described, the linkages 62 are circumferentially spaced apart from each other within the secondary channel 21B, and the number of linkages associated with the same membrane 58 can vary, for example, from two to ten.

[0071] One feature of the present invention is that when the movable structure 29 occupies Figure 2 and Figure 2A When the direct thrust position is shown, each link 62 is at least partially, and preferably completely, housed within the cavity 54 of the movable housing 33. As a result, the link 62 does not generate drag in the direct thrust configuration, which improves the performance of the propulsion unit.

[0072] Each link 62 includes a first end 62a connected to a second end 58b of the membrane. The second end 62b, opposite the first end, is hinged to the reversing device's mounting structure, preferably mounted on the rear frame 60 supporting the blade cascade 32 along a hinge axis having a tangential or substantially tangential orientation.

[0073] like Figure 1 , Figure 2 and Figure 2A As shown, when the movable structure 29 occupies its forward direct thrust position, at least a portion, preferably all, of the blocking membrane 58 is arranged radially within the cavity 54 between the deflector cascade 32 and the radially inner wall 52 of the reverser shroud 33. The latter is closed by abutting the deflection edge 46B at the upstream end 52a of the wall 52, such that in the direct thrust configuration, no part of the membrane is exposed to the secondary flow, nor is the connecting rod 62 exposed to the secondary flow.

[0074] It should also be noted that in this forward direct thrust position, each link 62 has an axial or approximately axial orientation, and a small radial offset can indeed be observed between the two link ends 62a, 62b, with the upstream first end 62a being slightly closer to axis A1 than the downstream second end 62b.

[0075] As can be clearly seen below, the reverser is designed such that when the movable structure 29 moves from its forward direct thrust position to its retracted thrust reverse position, each link 62 is pulled out of the cavity 54 through the upstream opening 54' of the cavity, while simultaneously pivoting about its second end 62b so that its first end 62a extends radially inward.

[0076] When the movable structure 29 reaches its retracted thrust-reversed position, each link 62 has fully pivoted about its second end 62b, such that its first end 62a is located near the wall 18, and preferably downstream of the second end 62b. Each link 62 also partially abuts against its upstream end 52a of the radially inner wall 52 of the movable cover, thus corresponding to the acoustic panel. This abutment allows for the cessation of the deployment and rotation of the links 62 driven by the pressure applied to the diaphragm 58.

[0077] like Figure 4A As shown, between two directly continuous links 62, the membrane 58 may be planar or generally planar, but it is preferably curved due to the deformation exerted on the membrane by the upstream airflow.

[0078] In this configuration, the radially outward portion of the membrane 58 abutting against the connecting rod 62 on the wall 52 blocks a portion of the upstream axial opening 54' of the cavity 54. Another radially inward portion blocks at least a portion of the secondary flow channel 21B, thereby deflecting at least a portion of the secondary flow 20B toward the channel opening 56 toward the blade cascade 32.

[0079] Another possibility, not shown, is to fix the radial outer side of the membrane 58 to the radial outer wall 50 of the sliding cover 33.

[0080] To enable the combined pull-out and extension movement of each link 62 during the opening of the movable cover 33, it is preferable that the links 62 are connected to the upstream end 52a of the radial inner wall 52 via at least one connector 64, here two connectors are provided. Each connector 64, as... Figure 5 As shown, the hinge is installed at the upstream end 52a, preferably hinged along a hinge axis 66 having a tangential or substantially tangential orientation. Here, the two hinge axes 66 are the same.

[0081] Furthermore, each link 62 is slidably mounted on each of the two connectors 64, preferably via a guide rail having two portions 68, each portion engaging with its associated connector 64. Therefore, utilizing such... Figure 6 The two back-to-back guide rails 68 shown are preferably shared by the same central core. The connecting rod 62 may have two opposing T-shaped cross sections, share the same central base, and each of the two T-shaped heads has two opposing curved ends to ensure the retention of the slider-shaped connector 64.

[0082] These two mechanical connections allow combined movements of the link 62 relative to the radial inner wall 52 of the movable housing, corresponding to translation / sliding along the link 62 and rotation along an axis orthogonal or substantially orthogonal to the previous displacement axis. This combined movement is ideal for achieving the desired extraction of the link 62 from the cavity 54, as well as the pivoting that causes the first end 62a of the link to extend radially inward.

[0083] It should be noted that this combined movement of the links 62 occurs automatically and passively when the reverser is opened, particularly due to the air pressure applied to the diaphragm 58, which pushes each link 62 to extend in the desired kinematic direction. Furthermore, when the reverser is closed, the combined movement of the links 62 operates in the opposite direction, again automatically and passively moving upstream with the movable cover 33, the upstream end 52a of which abuts against each link 62.

[0084] To further facilitate the deployment of each link 62, particularly in the initial stage of the reverser opening, the latter may include at least one spring 70 to aid the movement of the link 62 within the secondary flow channel 21B. Such a solution... Figure 7 and Figure 7A As shown, the spring 70, in the form of a compressed helical spring, is arranged in the fixed structure of the reverser, for example near the deflection edge 46B and the connecting rod 62, for example near its first end 62a. Here, the spring 70 is preferably arranged radially or substantially radially.

[0085] Similarly, when the movable structure 29 moves from its forward direct thrust position to its retracted thrust reverse position, a spring 72 can be provided for the displacement end of the damping link 62. Figure 8 An example is shown, illustrating such a tension helical spring 72, which is arranged in a fixed structure, preferably behind or near the support frame 60, between the element and the link 62, preferably between its second end 62b.

[0086] Another embodiment is in Figure 9As shown, a compression coil spring 72 is arranged between the radial outer wall 50 of the movable structure 29, preferably the movable cover, and the connecting rod 62, preferably extending beyond the connecting rod to the hinged extension 76 of the rear support frame 60.

[0087] These two springs 70 and 72 can, of course, be implemented within the same inverter to achieve the two desired functions respectively.

[0088] For the spring 70 that helps move the connecting rod 62 in the secondary flow channel 21B, a leaf spring could also be considered, such as... Figure 10 and Figure 10A As shown. The leaf spring 70 is attached here to the radial outer wall 50 of the movable reversing cover 33 and is arranged inside the cavity 54. It abuts against the radial outer surface of the connecting rod 62 to ensure its deployment.

[0089] In the latter example, link 62 is no longer straight but curved, here taking on a generally open C-shape. In the direct thrust configuration, the recess of the C is oriented radially inward to facilitate the exit motion when link 62 unfolds outside cavity 54 in secondary flow channel 21B. This particular shape and orientation of link 62 does indeed allow it to better bypass deflection edge 46B during the combined exit motion of the link. Of course, this curved shape of link 62 can be employed with or without springs 70, 72.

[0090] Other bending shapes can also be considered for connecting rod 62, such as a roughly S-shape, in a direct thrust configuration, where the upstream concave portion is oriented radially inward and the downstream concave portion is oriented radially outward. This embodiment... Figure 11 and Figure 11A As shown in the diagram. The orientation of the upstream recess allows for better bypassing of the deflection edge 46B during the combined disengagement motion of the connecting rod 62, as with the aforementioned C-shaped connecting rod. Furthermore, the opposite orientation of the downstream cavity allows for guiding the air in the secondary flow path to have an upstream component before passing through the blade cascade 32 when the connecting rod 62 and the membrane 58 along its profile are in a thrust-opposite configuration, as shown in the diagram. Figure 11A As shown by the arrow in the image.

[0091] Figure 12 and Figure 12A Another preferred embodiment of the invention is shown, wherein the link 62 has a telescopic characteristic, which allows for a reduced overall size when retracted into the cavity 54. To this end, a control system for the telescopic link 62 is provided, comprising a drive spring 80 and a cable 82 for controlling the deployment of the spring. More precisely, the control system is passively designed such that, when the reverser is opened, the link 62 is allowed to automatically deploy during its exit movement. Similarly, the control system allows the link 62 to automatically retract during its extension movement into the cavity 54 when the reverser is closed.

[0092] These functions are achieved, for example, by attaching one end of cable 82 to spring 80 and the other end of cable to upstream end 52a of radial inner wall 52 of movable reverser cover 33, and ensuring that cable 82 passes around the second end 62b of link.

[0093] Therefore, when the movable cover 33 is opened, the end of the cable 82 attached to the movable cover approaches the second end 62b of the connecting rod, resulting in the spring 80 relaxing, which in turn forces the sliding portion of the connecting rod to unfold, thereby increasing its length. When the movable cover 33 is closed, the end of the cable 82 attached to the movable cover moves away from the second end 62b of the connecting rod, resulting in the spring 80 compressing, which in turn causes the sliding portion of the telescopic connecting rod to retract, thereby reducing the length of the connecting rod, which then re-extends into the cavity 54 of the movable reversing cover.

[0094] Another preferred embodiment of the present invention is as follows: Figure 13 and Figure 13A As shown in the diagram, it implements another guiding system that allows the link 62 to tilt within the secondary flow channel 21B when the reverser is opened. For this purpose, the guiding system for the link 62 includes a radially inner guide 86a, such as a slider or roller permanently abutting against the radially inner surface of the link. Preferably, the guide 86a, located in the cavity 54, is mounted on the radially inner wall 52 of the movable reverser housing, located at or near its upstream end 52a. Similarly, the guiding system for the link 62 includes another radially outer guide 86b, such as a slider or roller permanently abutting against the radially outer surface of the link. Preferably, the guide 86b, also located in the cavity 54, is mounted on the radially outer wall 50 of the movable reverser housing, located at or near its upstream end 50a.

[0095] The radially inner guide 86a is not only radially offset from the radially outer guide 86b, but is also positioned upstream of it. Therefore, throughout the movement of the movable cover 33 during its opening, the link 62 pivots about its end 62b while being forced to remain in contact with each of the two components 86a, 86b due to the action of the blocking membrane, which itself is subjected to air pressure in the secondary flow channel. Thus, as the movable cover 33 retracts, the first end 62a of the link gradually extends into the secondary flow channel 21B, the movement of which is controlled by the two components 86a, 86b. The opposite phenomenon is observed when the reverser is closed, during which the link 62 gradually re-enters the cavity 54.

[0096] Figure 14 and Figure 14AAnother preferred embodiment of the invention is shown, wherein the airflow deflection member 32 is no longer a cascade, but comprises a membrane deployable using a link 88. The airflow redirection membrane 32 is then preferably of the same type as the blocking membrane 58. It is also housed in the cavity 54 in a direct thrust configuration, and the rear end of the link 88 carrying the membrane 32 is hinged to a fixed structure, such as a rear support frame 60, with the second end 62b of the link also hinged to the rear support frame 60.

[0097] As the movable cover 33 moves rearward, the pivoting of the connecting rods 88 can be observed, and their deployment can be stopped by a stop device 90, which is, for example, arranged on the rear support frame 60. Figure 14A As shown. Another possibility is to attach the stop device 90 to the radial outer wall 50 of the movable reverser cover 33, or even to the extension of the connecting rod 62 arranged in pairs in the same plane as these connecting rods 88, without departing from the scope of the invention.

[0098] Figure 15 and Figure 16 Another preferred embodiment of the invention is shown, wherein the reverser includes stop devices 92 that restrict the deployment of the links 62. These stop devices 92 are preferably arranged on the radial outer wall 50 of the movable reverser cover 33, for example, located at or near the upstream end 50a. They are configured to preferably contact an extension 76 of each link 62 that extends beyond the hinged connection of the link to the rear support frame 60.

[0099] Therefore, in such Figure 15 In the thrust-reversed position shown, on either side of its hinged connection, the connecting rod 62 contacts the two upstream ends 50a, 52a of the movable cover 33. The axial forces applied by the connecting rod 62 at these two ends 50a, 52a are in opposite directions, thus advantageously balancing and limiting the load on the actuator of the reverser.

[0100] according to Figure 16 In the alternative form shown, it can even be considered that the connecting rod 62 no longer contacts the upstream end 52a of the radial inner wall 52 of the cover 33, but only contacts the upstream end 50a of the radial outer wall 50 through its extension 76. Furthermore, it should be noted that in this alternative form, in the thrust-reversing configuration, the first end 62a of the connecting rod remains upstream of the hinged second end 62b of the connecting rod.

[0101] Those skilled in the art can make various modifications to the invention just described, which are merely non-limiting examples, and the scope of the invention is defined by the appended claims. For example, the thrust reverser 30 may alternatively have a "C-duct" or "O-duct" structure. Furthermore, the specific membrane of the invention can coexist with conventional blade cascades within the reverser. Additionally, all the features disclosed above in the various preferred embodiments and their alternatives can be combined together. Furthermore, it should be noted that in all the above figures, elements with the same reference numerals correspond to the same or similar elements.

Claims

1. A thrust reverser (30) for an aircraft propulsion assembly, the reverser comprising a fixed structure (31) equipped with a radially inner wall (18) defining a secondary flow channel (21B) of the propulsion assembly, the secondary flow channel being intended for a secondary flow (20B) to pass through, the reverser further comprising a movable structure (29) including at least one reverser shroud (33) having an upstream-opening cavity (54) defined between a radially outer wall (50) and a radially inner wall (52) of the reverser shroud (33), the movable structure being relative to the fixed structure along the... The longitudinal central axis (A1) of the reverser translates between an advancing direct thrust position and a retracted thrust-reversing position, in which the retracted thrust-reversing position exposes, upstream, the retracted radial inner wall (52) of the reverser housing, a channel opening (56) of the secondary flow channel (21B) toward the airflow deflector (32). The reverser also includes a membrane (58) for blocking the secondary flow channel (21B) and a membrane deployment member (62) connected to the membrane (58), the membrane deployment member being designed to be at least partially arranged in the secondary flow channel (21B) when the movable structure occupies its retracted thrust-reversing position. Its features are, When the movable structure (29) occupies its forward direct thrust position, the membrane deployment member (62), which is in the form of a linkage, is at least partially housed in the cavity (54) of the movable reversing cover (33).

2. The inverter according to claim 1, characterized in that, The reverser is designed such that when the movable structure (29) moves from its forward direct thrust position to its retracted thrust reverse position, the membrane deployment member (62) is extracted from the cavity (54) through the upstream opening (54') of the cavity.

3. The inverter according to claim 1 or 2, characterized in that, The membrane unfolding member (62) is a connecting rod, selected from: - Straight connecting rod; - Bent connecting rods, such as roughly C-shaped or S-shaped; - The telescopic rod is preferably associated with a control system including an actuating spring (80) and a cable (82) for controlling the deployment of the spring (80).

4. The inverter according to any one of the preceding claims, characterized in that, The membrane deployment member (62) includes an end (62b) which is hinged to the fixing structure (31) of the reverser, preferably hinged to the rear frame (60) for supporting the airflow deflection member (32).

5. The inverter according to any one of the preceding claims, characterized in that, The membrane unfolding member (62) is connected to the upstream end (52a) of the radial inner wall (52) via at least one connector (64), the connector (64) being hinged to the upstream end (52a), preferably along a hinge axis (66) having a tangential or substantially tangential orientation, the unfolding member (62) being slidably mounted on the connector (64), preferably via a guide rail-shaped portion (68) cooperating with the connector (64).

6. The inverter according to any one of claims 1 to 4, characterized in that, The reverser includes a guiding system for the connecting rod deployment member, the guiding system including a radially inner guide (86a) preferably mounted on the radially inner wall (52) of the movable reverser cover, and a radially outer guide (86b) preferably mounted on the radially outer wall (50) of the movable reverser cover, the radially inner guide (86a) preferably being arranged upstream of the radially outer guide (86b).

7. The inverter according to any one of the preceding claims, characterized in that, The reverser includes at least one spring (70) for assisting the membrane deployment member (62) in moving within the flow channel (21B), and / or the reverser includes at least one displacement-end damping spring (72) for damping the deployment member (62) as the movable structure (29) moves from its forward direct thrust position to its retracted thrust reverse position.

8. The inverter according to any one of the preceding claims, characterized in that, The airflow deflector (32) includes a membrane that can be deployed by a link (88), and the reverser includes a stop (90) for the link (88), the stop being preferably disposed on the radial outer wall (50) of the movable reverser cover (33).

9. The inverter according to any one of the preceding claims, characterized in that, The reverser includes a stop device (92) for the membrane unfolding member (62), the stop device preferably being arranged on the radial outer wall (50) of the movable reverser cover (33).

10. A pod (3) for an aircraft propulsion assembly, comprising at least one fan shroud (14) and a thrust reverser (30) according to any one of the preceding claims.

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