An aircraft propulsion assembly including an actuator connected to a structural arm such as an outlet guide vane

Abstract

The invention relates to a propulsion assembly comprising an actuator (40) connected to an outer casing (11) of a turbomachine by a connection structure (45). The connection structure (45) is fastened in line with a structural arm (12) which connects the outer casing (11) to a hub of the turbomachine, preferably by common fastening means (60, 61), so that the arm (12) can be subjected to the load forces of the actuator (40) while lightening the load of the outer casing (11).

Description

Technical Field

[0001] This invention relates to the field of aircraft propulsion assemblies including thrust reversers.

[0002] This invention is particularly applicable to sliding blade reversing devices. Background Technology

[0003] Currently, high-bypass turbines used in the aerospace field typically include a fan casing with an intermediate casing extending axially from the rear of the fan casing.

[0004] As used herein, the term "outer casing" refers to the assembly formed by the fan casing and the intermediate casing, or, when the turbine does not include the intermediate casing, to the fan casing only.

[0005] In a conventional propulsion unit equipped with a sliding blade reversing mechanism (as described in document FR2999239A1), the blades extend around the outer casing when the reversing mechanism is in direct thrust configuration.

[0006] To avoid excessive load on the shroud formed by the housing, the reverser actuator is typically connected to a structural flange formed by the axial ends of the fan housing and / or intermediate housing.

[0007] The known fastening method in the prior art involves mounting such an actuator onto a connecting structure that forms a beam, which is fastened to the front flange of the fan housing on one side and to the rear flange of the fan housing on the other.

[0008] This connection structure proves incompatible with modern propulsion component architectures, which reduce the available space around the outer casing.

[0009] In addition, it is necessary to reduce the load on the housing, especially the mechanical load from the inverter. Summary of the Invention

[0010] The object of the present invention is to provide a propulsion assembly equipped with a reverser having an axially movable structure that is compatible with modern architectures and that enables the reduction or optimization of the load on the housing, particularly when the movable structure of the reverser is axially biased backward.

[0011] Therefore, one object of the present invention is an aircraft propulsion assembly according to the features of claim 1.

[0012] The present invention transmits at least a portion of the force of the actuator directly to at least one arm via a connecting structure and a fastening device, so that at least a portion of the force of the actuator can be supported by at least one arm.

[0013] This reduces the load on the housing, especially when the movable structure is axially offset backward (i.e., in a thrust-reverse configuration) and when the movable structure moves toward that configuration.

[0014] The present invention also enables the overall size of the components of the propulsion assembly (especially the connecting structure) to be reduced around the outer shell.

[0015] Therefore, this invention enables improved propulsion component performance and compatibility with modern high bypass ratio architectures.

[0016] In one embodiment, the arm forms an outlet guide vane (OGV).

[0017] In a preferred embodiment, the actuator is connected to the rear frame of the blade cascade.

[0018] The movable structure preferably includes one or more covers.

[0019] The actuator can be connected to one or more movable covers.

[0020] Preferably, one or more covers are integrated with the rear frame of the blade cascade.

[0021] The actuator is preferably a cylinder.

[0022] In one embodiment, the cylinder is telescopic.

[0023] The actuator can be configured to extend radially below the blade cascade, or alternatively, to extend radially within the thickness of the blade cascade.

[0024] In an alternative embodiment, the housing includes a fan housing and an intermediate housing.

[0025] According to this first alternative embodiment, the arm is preferably fastened to the intermediate housing.

[0026] Alternatively, the arm can be fastened to the fan housing.

[0027] In a second alternative embodiment, the housing includes a fan housing and has no intermediate housing.

[0028] In one embodiment, the fastening device extends radially through the housing's shield.

[0029] Advantageously, the fastening device can be configured to fasten the arm to the housing.

[0030] This, in particular, enables the centralized sharing of fastening devices and improves the transmission of force between the arm and the connecting structure.

[0031] For example, fastening devices may include screws and / or studs and / or other types of fastening components.

[0032] In one embodiment, the connection structure includes a support element integral with the housing.

[0033] The support element can be a connector that is fastened to the housing by the engine manufacturer and configured such that another component of the connection structure (such as an accessory) can be fastened to it. Therefore, the connection structure and other parts of the nacelle can be installed or replaced without affecting the turbine, especially once the turbine has been assembled and tested, by fastening the support element to the turbine.

[0034] The connection structure preferably includes fittings fastened to the support element.

[0035] In one embodiment, the propulsion assembly includes a cardan configured to hinge the actuator to an accessory or to another component formed by a connecting structure.

[0036] In one embodiment, the fitting is fastened to the flange of the housing.

[0037] Therefore, in one embodiment, the accessory can be fastened to the flange of the housing on one hand, and to the support element as described above on the other.

[0038] More generally, the connection structure can be fastened to multiple parts of the housing and / or arm, for example, to distribute the force of the actuator and improve one or more corresponding force paths.

[0039] Connection structures can have many geometric shapes.

[0040] For example, the fittings of this connection structure can form a hinged U-shaped joint that extends in a straight line with the arm.

[0041] In another example, the fittings of the connecting structure can form a longitudinally extending beam.

[0042] In one embodiment, the connection structure includes a connection to the front of the actuator and a connection to the rear of the housing, such that the actuator extends in a cantilever manner.

[0043] Other advantages and features of the invention will become apparent after reading the following detailed, non-limiting description. Attached Figure Description

[0044] The following detailed description refers to the accompanying drawings, in which:

[0045] [ Figure 1 [I] is a schematic longitudinal cross-sectional half-view of a propulsion assembly according to the present invention, the propulsion assembly including a thrust reverser in a direct thrust configuration;

[0046] [ Figure 2 ]yes Figure 1A schematic longitudinal cross-sectional half-view of the propulsion assembly, wherein the reverser is in a thrust reversing configuration;

[0047] [ Figure 3 [Illustrated partial view of a reversing actuator according to the present invention, the reversing actuator including a cylinder and a connecting structure according to a first embodiment, the cylinder being in a retracted position;]

[0048] [ Figure 4 ]yes Figure 3 A partial schematic diagram of the actuation device, in which the cylinder is in the extended position;

[0049] [ Figure 5 ]yes Figure 3 A partial schematic perspective view of the actuation device;

[0050] [ Figure 6 [Illustration] is a partial schematic diagram of a reverser actuation device according to the present invention, which includes a cylinder and a connecting structure according to a second embodiment, wherein the cylinder is in a retracted position;

[0051] [ Figure 6A ]yes Figure 6 A partial schematic transverse cross-sectional view of the actuation device;

[0052] [ Figure 7 [Illustration] is a partial schematic diagram of a reverser actuation device according to the present invention, which includes a cylinder and a connecting structure according to a third embodiment, wherein the cylinder is in a retracted position;

[0053] [ Figure 7A ]yes Figure 7 A partial schematic transverse cross-sectional view of the actuation device. Detailed Implementation

[0054] Figure 1 and Figure 2 The aircraft propulsion system 1 with a central longitudinal axis A1 is shown.

[0055] In the following text, the terms "forward" and "backward" are defined relative to the main direction S1 of the airflow passing through the propulsion assembly along axis A1 when the propulsion assembly 1 generates thrust.

[0056] The propulsion assembly 1 includes a turbine 2, a nacelle 3, and a pylon (not shown) for connecting the propulsion assembly 1 to the wing of the aircraft.

[0057] In this example, turbine 2 is a turbofan engine that includes, from front to back, 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.

[0058] The turbojet engine 2 is equipped with a housing 11 that surrounds the fan 5 and is connected to the hub of the turbojet engine 2 via a structural arm 12 that extends radially through the secondary flow path 21B.

[0059] In a manner known per se, the arms 12 are circumferentially distributed around axis A1, and each of these arms is fastened to the hub by a handle and to the housing 11 by a head, in particular to transmit force between the gas generator and the mounting bracket of the propulsion assembly 1.

[0060] In this example, arm 12 forms an outlet guide vane, which enables the secondary flow 20B to be straightened after fan 5.

[0061] Therefore, each of the arms 12 includes a front end portion 12A forming a leading edge and a rear end portion 12B forming a trailing edge.

[0062] The cabin 3 includes a front section forming an air inlet 13, a middle section including a fan shroud 14 surrounding the outer shell 11, and a rear section 15.

[0063] During operation, the airflow 20 enters the propulsion assembly 1 through the air inlet 13, passes through the fan 5, and then splits into a main flow 20A and a secondary flow 20B. The main flow 20A flows in the main gas flow path 21A that passes through the gas generator. The secondary flow 20B flows in the secondary flow path 21B that surrounds the gas generator.

[0064] The secondary flow path 21B is defined radially inward by the fixed inner shroud 18 surrounding the gas generator and radially outward by the outer shell 11, and... Figure 1 In its construction, it is defined by the reversing shield 33 that forms the rear section 15 of the cabin 3 (see below).

[0065] The cabin 3 includes a thrust reverser 30, which forms a movable structure relative to the turbojet engine 2, and in particular relative to the outer shell 11, wherein the outer shell forms a fixed structure for the propulsion assembly 1.

[0066] In this example, the movable structure of the reverser 30 includes a deflection vane 32, the aforementioned cover 33, an opening and closing baffle 34, and a connecting rod 35.

[0067] Figure 1 The reverser 30 in a direct thrust configuration is shown.

[0068] In this configuration, the shroud 33 is in a closed or forward position, in which the shroud is substantially supported on the rear end of the middle section, and in which the blade shroud 32 is accommodated in a space that is radially defined on one side by the housing 11 and on the other side by the fan shroud 14.

[0069] In the direct thrust configuration, baffle 34 is in the cavity 36 formed by cover 33 (see Figure 2 () retracts inward.

[0070] Therefore, the reverser 30 enables the secondary flow 20B to be directed to the rear of the propulsion unit 1, thereby generating thrust.

[0071] Figure 2 The reverser 30 in the thrust reversing configuration is shown.

[0072] In this configuration, the shroud 33 is in an open or rearward position, in which the shroud is longitudinally removed from the intermediate section to define a radial opening for the secondary flow path 21B. The blade cascade 32 extends through this radial opening.

[0073] In the thrust reversal configuration, the baffle 34 extends radially in the secondary flow path 21B to guide the secondary flow 20B toward the blade cascade 32, which allows the redirected flow to be oriented forward of the propulsion unit 1 to generate reverse thrust.

[0074] More specifically, the present invention relates to the actuation of a movable structure of the inverter 30.

[0075] Figures 3 to 5 An actuation device according to a first embodiment is shown.

[0076] The actuating device includes a cylinder 40, which includes a body 41 and a rod 42, the rod being operable relative to the body 41. Figure 3 The retraction position shown and Figure 4 Move between the indicated extension positions.

[0077] Cylinder 40 is a hydraulic cylinder.

[0078] In this example, cylinder 40 is telescopic, which allows for compensation for deflection and expansion of the movable structure compared to a non-telescopic cylinder. In an alternative embodiment, cylinder 40 may be non-telescopic.

[0079] The actuating device may also include a buckling limiting device (not shown).

[0080] Reference Figure 3 and Figure 4The lever 42 moves between a retracted position and an extended position according to an actuation direction parallel to axis A1. In an alternative embodiment (not shown), the actuation direction may be tilted relative to axis A1.

[0081] The rod 42 of cylinder 40 includes a free end 43, which is connected to a movable structure of reverser 30.

[0082] In this example, the free end 43 of the rod 42 is hinged to the rear frame 32B of the blade cascade 32, which is integral with the cover 33 or one of the covers 33. It should be understood that the reverser 30 may have a conventional C, D or O-shaped structure.

[0083] In this example, the body 41 of cylinder 40 is hinged to connecting structure 45 via universal joint 46 about hinge axis A2, which passes through a plane orthogonal to axis A1 (see...). Figure 5 ).

[0084] In this example, the universal joint 46 is mounted on a portion of the body 41 (located near the front end of the cylinder 40, opposite the free end 43 of the rod 42) to surround the body 41 of the cylinder 40.

[0085] The cylinder 40 extends radially between the inner and outer surfaces of the blade cascade 32, that is, it extends radially within the thickness of the blade cascade.

[0086] In an alternative embodiment not shown, the cylinder 40 extends radially inward relative to this inner surface of the blade cascade 32.

[0087] Universal joint 46 extends in front of vane 32, more precisely, in a position axially forward relative to the front frame 32A of vane 32 (including when cylinder 40 is in the retracted position). Figure 3 (Time) Extension.

[0088] Therefore, the universal joint 46 and the connecting structure 45 are configured to extend outside the volume of the blade cascade 32, which increases the useful deflection surface of the blade cascade.

[0089] Figures 3 to 5 The connection structure 45 includes a fitting 47 and two support elements 48 and 49 for the fitting 47.

[0090] Support elements 48 and 49 are fastened to the outer casing 11.

[0091] In this embodiment, the outer casing 11 includes a fan housing 50 and an intermediate housing 51 forming an axial extension of the fan housing 50.

[0092] In a manner known per se, the fan housing 50 forms a shroud 52, which includes a front flange 53 and a rear flange 54 at its axial ends. Similarly, the intermediate housing 51 forms a shroud 55, which includes a front flange 56 and a rear flange 57 at its axial ends.

[0093] The rear flange 54 of the fan housing 50 and the front flange 56 of the intermediate housing 51 are connected to each other by fastening devices such as bolts or rivets (not shown).

[0094] Reference Figure 3 The head of each arm in the arms 12 (i.e. the radially outward end of the arm relative to axis A1) is arranged radially opposite to the inner surface of the shield 55 formed by the intermediate housing 51 and is fastened to the shield 55 by fastening devices 60 and 61 such as studs or screws.

[0095] Each of the arms 12, along with their leading edge 12A and trailing edge 12B, extends axially between the leading flange 56 and trailing flange 57 of the intermediate housing 51.

[0096] In this example, fastening device 60 forms a first row and is positioned axially close to the leading edge 12A of arm 12. Fastening device 61 forms a second row and is positioned axially rearward relative to fastening device 60 and axially close to the trailing edge 12B of arm 12.

[0097] Each of the fastening devices 60 and 61 extends radially through the shield 55 of the intermediate housing 51.

[0098] In this non-limiting example, each of the arms 12 is thus fastened to the intermediate housing 51 by two fastening devices 60 at the front and by two fastening devices 61 at the rear.

[0099] The support element 49 of the connecting structure 45 is arranged on the outer surface of the cover 55 of the intermediate housing 51.

[0100] In this example, the support element 49 is circumferentially aligned with one of the arms 12 and extends axially between the leading edge 12A and the trailing edge 12B of the head of the arm 12. For the remainder of this specification, reference is made to the arm 12 by default.

[0101] The support element 49 is fastened to the cover 55 by the same fastening device 60 that fixes the arm 12 to the intermediate housing 51.

[0102] In this example, the support element 48 is L-shaped, forming radial lugs and axial lugs.

[0103] The radial lug of the support element 48 is arranged against the front surface of the rear flange 54 of the fan housing 50, and the radial lug of the support element is fastened to the front flange 56 of the intermediate housing 51 and the fan housing by fastening means such as screws or bolts (not shown) that axially pass through these different parts.

[0104] In this example, support elements 48 and 49 form a connection designed to remain integral with the housing 11 during maintenance work on the actuating device. For this purpose, support elements 48 and 49 are configured such that fitting 47 can be detachably fastened to the support elements, potentially damaging the corresponding fastening device (not shown).

[0105] Reference Figure 5 The fitting 47 extends longitudinally to form a double beam, which includes two arms 47A and 47B extending circumferentially on both sides of the cylinder 40 (see...). Figure 5 ).

[0106] The front parts of arms 47A and 47B are hinged to universal joint 46.

[0107] Each of the arms 47A and 47B of accessory 47 forms a surface that is arranged opposite to the axial lug of support element 48. Arms 47A and 47B are secured to the axial lug of support element 48 by fastening means such as screws or bolts (not shown).

[0108] Accessory 47 includes a rear portion forming a rear lug 70 that extends circumferentially to connect arms 47A and 47B to each other (see [link]). Figure 5 ).

[0109] The rear lug 70 of the fitting 47 is arranged on the outer surface of the support element 49 and fastened to the support element 49 by fastening devices such as screws or studs (not shown), which in this example are different from the aforementioned fastening device 60.

[0110] Of course, accessory 47 can have the same Figure 5 The geometry shown is different from the geometry shown, and forms, for example, a beam with a single arm (not shown) extending radially below cylinder 40.

[0111] In this example, the means for fastening the fitting 47 to the support element 49 is arranged axially close to the leading edge 12A of the head of the arm 12 (see [reference]). Figure 3 ).

[0112] Therefore, the connection structure 45 enables the cylinder 40 to be connected to the housing 11, thereby defining the main path through the arm 12. In particular, when the movable structure of the reverser 30 is in a thrust-reversing configuration or moving toward that configuration, the movable structure applies an axial force supported by the arm 12 to the cylinder 40, which is transmitted through the fitting 47, the support element 49, and the fastening device 60.

[0113] Therefore, the present invention enables a reduction in the load on the housing 11, not to mention a reduction in the load on the shroud 52 of the fan housing 50, where the shroud is likely to deform in the event of one or more blades of the fan 5 breaking. In this respect, due to the relative arrangement of the support elements 48 and 49, the body 41 of the cylinder 40 and the fitting 47 are cantilevered onto the fan housing 50 (see...). Figure 3 ).

[0114] Accessory 47 acts as an axial load-bearing beam supported by arm 12.

[0115] Figure 6 and Figure 6A An actuation device according to a second embodiment is shown.

[0116] The second embodiment will be described only in light of the differences between the second embodiment and the first embodiment. In view of these differences, the foregoing description is applied by analogy.

[0117] In this example, the connection structure 45 includes fitting 47 and a single support element 49.

[0118] The support element 49 is fastened to the cover 55 by the same fastening devices 60 and 61 that fix the arm 12 to the intermediate housing 51.

[0119] Fitting 47 of connecting structure 45 has a U-shaped cross-section (see...) Figure 6A The U-shaped cross-section includes a base 80 and two radial lugs 81 and 82.

[0120] The base 80 of accessory 47 is arranged on support element 49 and fastened to support element by fastening device such as screw (not shown).

[0121] Reference Figure 6A , Figure 6A An actuating device is shown along a cross-section of axis A2 that is used to hinge the body 41 of cylinder 40 to fitting 47. Lugs 81 and 82 extend circumferentially on both sides of universal joint 46 and are connected to universal joint 46 such that axis A2 is radially off-center relative to the axis used to actuate cylinder 40, such that fitting 47 extends outside the volume of vane 32.

[0122] Therefore, fitting 47 and more generally connecting structure 45 extend in a straight line with arm 12, so that the main path is substantially shorter than the main path in the first embodiment.

[0123] In this example, the universal joint 46 is mounted to the middle of the body 41 of the cylinder 40, which is close to the center of gravity of the cylinder 40.

[0124] This arrangement allows for improved absorption of forces from cylinder 40 by arm 12.

[0125] This arrangement also reduces the risk of buckling of cylinder 40, thus reducing the size of the cylinder and the mass of the actuator.

[0126] In this example, the retaining structure 90 is fastened to the rear flange 54 of the fan housing 50 to form an axial stop for the cylinder 40, which allows the cylinder to be held in place, for example, in the event of a broken blade of the fan 5.

[0127] Figure 7 and Figure 7A An actuation device according to a third embodiment is shown.

[0128] The third embodiment is described only in light of the differences between the third embodiment and the second embodiment. In view of these differences, the foregoing description applies by analogy.

[0129] In this embodiment, the main body 41 of the cylinder 40 is hinged to the accessory 47 via a bracket-type structure 100.

[0130] Reference Figure 7A , Figure 7A It shows Figure 7 The actuating device along the cross-section of axis A2 for hinged to the body 41 of cylinder 40 to fitting 47, the bracket 100 includes a base 101 and fitting elements 102 and 103 extending on both sides of the body 41 of cylinder 40.

[0131] The base 101 and accessory elements 102 and 103 extend radially below the blade cascade 32, outside the volume defined by the blade cascade, which makes it possible to increase the effective deflection surface of the blade cascade.

[0132] This type of bracket is also better than, for example, 100. Figure 3 and Figure 6A The universal joint 46 shown is more compact.

[0133] The present invention is not limited to the embodiments described above. Thus, for example, the outer casing 11 may not have an intermediate casing 51, the arm 12 may be connected to the fan casing 50, and the connection structure 45 may be connected to the fan casing 50 to transfer the load of the actuating device to one of the arms 12.

[0134] As another example, in each of the embodiments described above, the actuator 40 can be driven by different... Figures 3 to 6A Universal joint 46 and Figure 7A The hinged component of the bracket 100 is connected to the connecting structure 45.

[0135] Very preferably, as previously discussed, especially with reference to Figure 3 The universal joint 46 of the support cylinder is arranged upstream of the blade cascade 32 and the structural arm 12 of the housing.

[0136] Furthermore, the embodiments described above can be combined. For example, in an alternative embodiment not shown, Figure 3 The universal joint 46 of the actuation device can be made of a similar Figure 7A The bracket 100 is replaced, and the geometry of accessory 47 is adjusted accordingly.

[0137] Of course, the actuation device may include a plurality of actuators 40 and corresponding connection structures 45 as described above, each cylinder 40 may be configured to define a main path through the corresponding arm 12 of the propulsion assembly 1.

Claims

1. An aircraft propulsion assembly (1), the aircraft propulsion assembly comprising: Fixed structure Movable thrust reversing structure (32, 33), and A linear actuator (40) is connected to the movable thrust reversing structure (32, 33) to enable the movable thrust reversing structure to translate relative to the fixed structure along the longitudinal axis (A1). The fixing structure includes an outer housing (11) extending around the longitudinal axis (A1), a hub, a structural arm (12) connecting the outer housing (11) to the hub, a connection structure (45) connecting the linear actuator (40) to the outer housing (11), and fastening devices (60, 61) for fastening the connection structure (45) to the outer housing (11). The movable thrust reversing structure (32, 33) includes a deflecting blade cascade (32), characterized in that, The fastening devices (60, 61) are axially positioned between the leading edge (12A) and trailing edge (12B) of the head of the structural arm (12). The connection structure (45) includes a support element (49) and an accessory (47). The support element is integral with the outer shell (11), and the accessory is fastened to the support element (49). The accessory (47) includes: a first accessory arm (47A) and a second accessory arm (47B), which extend circumferentially on both sides of the linear actuator (40); and a rear lug (70), which extends circumferentially and connects the rear ends of the first and second accessory arms. The front ends of the first accessory arm (47A) and the second accessory arm (47B) are hinged to the universal joint (46) on which the linear actuator (40) is mounted.

2. The aircraft propulsion assembly (1) according to claim 1, wherein, The fastening devices (60, 61) extend radially through the shield (55) of the outer casing (11).

3. The aircraft propulsion assembly (1) according to claim 1, wherein, The fastening devices (60, 61) are configured to fasten the structural arm (12) to the housing (11).

4. The aircraft propulsion assembly (1) according to claim 1, wherein, The accessory (47) is fastened to the flange (54) of the outer casing (11).

5. The aircraft propulsion assembly (1) according to claim 1, wherein, The connection structure (45) includes a front portion connected to the linear actuator (40) and a rear portion connected to the housing (11), such that the linear actuator (40) extends in a cantilever manner.

6. The aircraft propulsion assembly (1) according to claim 1, wherein, The structural arm (12) forms the outlet guide vane.

7. The aircraft propulsion assembly (1) according to claim 1, wherein, The outer casing (11) includes a fan housing (50) and an intermediate housing (51), and the structural arm (12) is fastened to the intermediate housing (51).

8. The aircraft propulsion assembly (1) according to claim 1, wherein, The linear actuator (40) is a telescopic cylinder.

Images