Includes a movable blade stack thrust reverser with a multi-functional fixed structure.

Abstract

The present invention relates to a movable blade thrust reverser including a multifunctional annular fixing structure (31) configured to be rigidly connected to a fan housing or intermediate housing of a turbine engine, the intermediate housing being fixed to the fan housing.

Description

Technical Field

[0001] This invention relates to the field of thrust reversers for aircraft propulsion units, and more particularly to movable cascade reversers. Background Technology

[0002] Currently, blade reversing devices used in the aviation field include a front frame, which, together with the blades, forms a fixed part of the reversing device designed to be attached to the turbine engine casing.

[0003] Over the past decade, technological advancements have made it possible to develop movable blade cascade reversers, as described in documents FR2981989A1, FR2999239A1, FR3002785A1, and FR3073572A1.

[0004] Compared to traditional fixed-blade reversing systems, the mobility of the blades allows for a reduction in the length of the nacelle, thereby reducing its mass and the resulting drag.

[0005] Known movable vane reversers in the prior art do not include a front frame, and several functions of these reversers, such as vane guidance, deflection of flow in the opposite direction to the front of the vane, or radial cylinder liner guidance, are performed by components fastened to the turbine engine.

[0006] This resulted in a relatively complex and large architecture. Summary of the Invention

[0007] The object of this invention is to provide a movable cascade reverser with a simplified and / or more compact architecture.

[0008] Another objective of this invention is to reduce the mass and cost of the movable blade reversing device.

[0009] Therefore, the present invention relates to a thrust reverser for an aircraft propulsion unit according to the features of claim 1.

[0010] This fixed structure allows for easy connection of the reverser to the propulsion unit turbine engine, while reducing the overall size of the reverser.

[0011] This fixed structure also allows for the centralization of several functions of the inverter and simplifies the overall architecture of the inverter, particularly by further functionalizing the fixed structure that now integrates the deflection edge.

[0012] Therefore, the present invention enables a reduction in the mass and cost of the inverter.

[0013] It should be noted that this mobility of the cover is particularly seen in inverters with a so-called "D" architecture (called "D-shaped pipe").

[0014] The fixed structure preferably includes an upper beam configured to engage with the shroud to transfer loads from the shroud to the turbine engine housing and / or from the shroud to the propulsion unit mast.

[0015] In one embodiment, the fixing structure includes elements for guiding the leaf cascade between a forward position and a retracted position.

[0016] When the fixed structure includes the aforementioned upper beam, the upper beam can support at least one of the guiding elements.

[0017] According to an alternative embodiment, the lower beam may support at least one of the aforementioned guide elements.

[0018] In one embodiment, the fixing structure includes a member that forms a radial and / or tangential and / or axial stop for the blade cascade.

[0019] The fixing structure of the present invention can obviously form or support other components or elements besides those described above, in order to perform additional or supplementary functions of the reverser or propulsion unit.

[0020] The present invention also relates to a propulsion unit for an aircraft, comprising a turbine engine and a reversing device as defined above.

[0021] In one embodiment, the housing is formed by the fan housing of a turbine engine or by an intermediate housing extending axially to the rear of the fan housing.

[0022] Other advantages and features of the invention will become apparent from the following detailed, non-limiting description. Attached Figure Description

[0023] The following detailed description refers to the accompanying drawings, in which:

[0024] [ Figure 1 [Illustrated longitudinal half-sectional view of a propulsion unit including a reverser according to the invention, in a forward thrust configuration.]

[0025] [ Figure 2 [This refers to the reverser being in the reverse thrust configuration.] Figure 1 A schematic longitudinal half-sectional view of the propulsion unit.

[0026] [ Figure 3 ] is similar to Figure 1 A schematic perspective view of a portion of the propulsion unit, showing the fixed structure of the turbine engine, mast, and reverser according to the invention.

[0027] [ Figure 4 ]yes Figure 3 A schematic perspective view of a portion of the propulsion unit, showing the shroud and blades of the reverser;

[0028] [ Figure 5 ]yes Figure 3 A schematic exploded perspective view of the reverser of the propulsion unit;

[0029] [ Figure 6 ]yes Figure 3 A schematic three-dimensional view of the fixed structure of the reverser of the propulsion unit;

[0030] [ Figure 7 ]yes Figure 3 A schematic perspective view and longitudinal sectional view of the fan housing, intermediate housing, and the fixing structure of the reverser of the propulsion unit;

[0031] [ Figure 8 ]yes Figure 3 A schematic 3D view of the lower 6 o'clock position of the propulsion unit;

[0032] [ Figure 9 ]yes Figure 3 A schematic three-dimensional view of the upper beam of the fixed structure of the reverser of the propulsion unit;

[0033] [ Figure 10 ]yes Figure 3 A schematic 3D view of the upper 12 o'clock position of the propulsion unit;

[0034] [ Figure 11 ]yes Figure 3 A schematic perspective view of a portion of the propulsion unit, showing the blade guide rails;

[0035] [ Figure 12 ]yes Figure 3 A schematic perspective view of a portion of the housing of the propulsion unit, showing the radial blade cascade positioning stop;

[0036] [ Figure 13 ]yes Figure 3 A schematic longitudinal half-sectional view of a portion of the propulsion unit, showing the axial and radial blade cascade positioning stops in the reverse thrust configuration. Detailed Implementation

[0037] Figure 1 and Figure 2 The image shows the propulsion unit 1 of an aircraft, which has a longitudinal central axis A1.

[0038] In the following text, the terms “front” and “rear” are defined relative to the direction S1 of the airflow passing through the unit along the longitudinal central axis A1 when the propulsion unit 1 generates thrust.

[0039] Propulsion unit 1 includes turbine engine 2, nacelle 3, and mast—in Figure 1 and Figure 2Not seen in China (see also) Figure 3 and Figure 4 The mast 4 in the middle is designed to connect the propulsion unit 1 to the wing of the aircraft (not shown).

[0040] In this example, turbine engine 2 is a turbofan engine, comprising, from upstream to downstream: fan 5, low-pressure compressor 6, high-pressure compressor 7, combustion chamber 8, high-pressure turbine 9, and low-pressure turbine 10. Compressors 6 and 7, combustion chamber 8, and turbines 9 and 10 form a gas generator.

[0041] The turbojet engine 2 is equipped with a fan housing 11 that is connected to the gas generator via a structural arm 12.

[0042] The nacelle 3 includes a front portion forming an air inlet 13, a middle portion including a fan shroud 14 covering a fan housing 11, and a rear portion 15.

[0043] During operation, the airflow 20 enters the propulsion unit 1 through the air inlet 13, passes through the fan 5, and is then divided 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 into the secondary flow path 21B that surrounds the gas generator.

[0044] The secondary flow path 21B is defined radially inward by a fixed internal shroud covering the gas generator. In this example, the fixed internal shroud includes a first segment 17 belonging to the intermediate portion 14 (see...). Figure 1 and Figure 3 ) and the second paragraph 18 extending from the first paragraph 17 to the rear (see Figure 1 , Figure 4 and Figure 5 ), thus forming part of the rear portion 15.

[0045] Radially outward, the secondary flow path 21B is defined by the fan housing 11, and... Figure 1 In its construction, it is defined by the movable cover that forms the rear portion 15 of the nacelle 3 (see further below).

[0046] The nacelle 3 includes a thrust reverser 30, which includes, on the one hand, a fixed structure 31 fixed to the fan housing 11 according to the principles detailed below, and on the other hand, a movable structure relative to the fixed structure 31.

[0047] The movable structure of the reverser 30 includes a deflection blade 32, the aforementioned movable cover 33, a shutter flap 34, and a pull rod 35.

[0048] Figure 1 The reverser 30 is shown in a direct thrust configuration.

[0049] In this configuration, the movable shields 33 are in a closed or forward position, wherein they are substantially supported on the fixed structure 31, and wherein the blades 32 are accommodated in a space that is radially defined on one side by the fan housing 11 and on the other side by the fan shroud 14.

[0050] In the forward thrust configuration, the baffle 34 is retracted into the cavity 36 formed by the movable cover 33 (see...). Figure 2 ).

[0051] Therefore, the reverser 30 enables the secondary stream 20B to be directed to the rear of the propulsion unit 1 in order to generate thrust.

[0052] exist Figure 1 In the structure, the fixed blade cascade 32 and the movable cover 33 are in the so-called positive thrust position.

[0053] Figure 2 The reverser 30 is shown in a reverse thrust configuration.

[0054] In this configuration, the movable shields 33 are in an open or retracted position, wherein they are longitudinally removed from the fixed structure 31 to define a radial opening in the secondary flow path 21B. The blade cascade 32 extends through this radial opening.

[0055] In the reverse thrust configuration, the baffle 34 is radially deployed in the secondary flow path 21B to guide the secondary flow 20B toward the blade cascade 32, which allows the flow to be redirected to the front of the propulsion unit 1 to generate reverse thrust.

[0056] exist Figure 2 In the configuration, the blade cascade 32 and the movable cover 33 are in the so-called reverse thrust position.

[0057] More specifically, the present invention relates to the fixing structure 31 of the reverser 30.

[0058] refer to Figure 6 The illustration shows a non-limiting embodiment of the invention, in which the fixing structure 31 has an overall annular shape extending around axis A1.

[0059] In this example, the fixed structure 31 has a closed curved shape and thus forms a ring.

[0060] In embodiments not shown, the fixing structure may have an unclosed, curved shape, for example, to form part of a ring, or may have several parts configured together to have an overall annular shape.

[0061] Figure 6The fixed structure 31 includes: an upper beam 40 extending at 12 o'clock (i.e., at the mast 4 of the propulsion unit 1 in the circumferential direction); a lower beam 41 extending at 6 o'clock (i.e., opposite to the mast); and two circumferential sections 42 that connect the upper beam 40 and the lower beam 41 to each other.

[0062] Each circumferential segment 42 includes a front end 43 forming a radial flange and a portion 44 extending axially from the front end 43 to form a rear end 45 of the corresponding circumferential segment 42.

[0063] refer to Figures 6 to 8 The radial flange 43 formed by the circumferential segment 42 is configured to be supported on the radial flange 50, which in this example is formed by the rear end of the intermediate housing 11A, which extends the fan housing 11 of the turbine engine 2 so as to secure the fixing structure 31 of the reverser 30 to the housing 11A along a rigid connection.

[0064] Alternatively, the turbine engine 2 may be without the intermediate housing 11A, in which case the fixing structure 31 may be directly connected to the fan housing 11 (not shown) in a similar manner. The following description applies by analogy to such an alternative.

[0065] By definition, a rigid connection is a connection that, under normal operating conditions, regardless of the nature and intensity of the external stress, ensures that the assembled components have a defined relative position and remain constant over time.

[0066] The fixing structure 31 of the reverser 30 is therefore fixed to the fan housing 11 of the turbine engine 2 by means of translation and rotation about axis A1.

[0067] In this example, radial flanges 43 and 50 are connected to each other by riveting.

[0068] Radial flanges 43 and 50 can be connected to each other by other types of connecting devices (e.g., by bolts).

[0069] refer to Figure 3 , Figure 7 and Figure 8 The fixing structure 31 of the reverser 30 thus forms an axial extension of the housing 11A.

[0070] In this example, a portion 44 of the circumferential section 42 forms an inner surface 46, which defines a section of the secondary flow path 21B when the reverser 30 is in the reverse thrust configuration.

[0071] In this example, the inner surface 46 of the circumferential section 42 is radially open, that is, it gradually moves away from the axis A1 from the radial flange 43 to the rear end 45 and forms a deflection edge.

[0072] The curved shape of the deflection edge 46 allows the Coanda effect to initiate a change in the direction of the flow through the blade cascade 32 for thrust reversal.

[0073] refer to Figure 9 and Figure 10 The upper beam 40 includes circumferentially extending grid modules 60 that extend to both sides of the mast 4.

[0074] The upper beam 40 also includes two radial flanges 61 forming its rear end.

[0075] The radial flange 61 is designed to connect the fixing structure 31 to beams (not shown), which are fixed to the mast 4 and each beam extends on both sides of the mast 4. These beams and the radial flange 61 are specifically configured to support the movable cover 33 of the reverser 30.

[0076] The module 60 of the upper beam 40 forms a front end 62, which extends circumferentially along the radial flange 43 of the circumferential section 42 to mate with the radial flange 50 of the housing 11A.

[0077] Therefore, the upper beam 40 serves as an interface and structural connection with the mast 4, the housing 11A and the movable cover 33.

[0078] The upper beam 40 also enables the implementation of sealing, utility wiring, and fireproof and ventilation area isolation functions.

[0079] In this example, the fixed inner fairing 17 includes connecting arms 19 located at 12 o'clock and 6 o'clock in a manner known per se (see [reference needed]). Figure 3 ).

[0080] The circumferential section 42 of the fixed structure 31 is circumferentially continuous, and the upper beam 40 defines the corresponding part of the secondary flow path 21B on both sides of the connecting arm 19 at the 12 o'clock position.

[0081] Furthermore, in this example, the reverser 30 has a D-shaped pipe structure well known in the art of the invention, with the movable cover 33 hinged to the beam fixed to the mast 4 so as to be able to move in a butterfly manner between the closed flight position and the open maintenance position.

[0082] like Figure 3 , Figure 6 and Figure 8 As seen, the lower beam 41 of the fixed structure 31 has particular benefits for this D-shaped pipe structure.

[0083] Specifically, the lower beam 41 includes a component 65 for connecting and positioning the movable cover 33 in the flight position. Figure 3 and Figure 8 ).

[0084] The lower beam 41 also includes a fastening element 66 for securing the lower beam 41 to the housing 11A. Figure 3 and Figure 6 ).

[0085] Therefore, the lower beam 41 serves as an interface and structural connection with the housing 11A and the movable cover 33.

[0086] Similar to the upper beam 40, the lower beam 41 defines the corresponding portions of the secondary flow path 21B on both sides of the connecting arm 19 at the 6 o'clock position (see...). Figure 8 It also enables the implementation of sealing and utility wiring functions.

[0087] The reverser 30 includes elements for guiding the blade 32 during movement of the blade 32 between the forward position and the retracted position.

[0088] Typically, the guiding element may include a guide rail and / or track and / or roller connected to the fixing structure 31 of the fan housing 11 and / or intermediate housing 11A and / or reverser 30.

[0089] In this example, the guiding element includes a track 70, with two fixed to the upper beam 40 of the fixing structure 31 of the reverser 30, and two others fixed to the lower beam 41 (see [link]). Figure 3 , Figure 6 , Figure 9 and Figure 10 ).

[0090] In this example, via fitting 71, the rail 70 is fastened to the fixing structure 31 via its rear end and to the housing 11A via its front end, as shown. Figure 11 As shown in the diagram.

[0091] Alternatively, the front end of the track 70 may extend in a suspended position or be connected to the fan housing 11 or the mounting structure 31 via a collar and / or connecting rod and / or any other connecting device (not shown in the embodiment).

[0092] Therefore, track 70 performs the guiding function of cascade 32 and, in the reverse thrust configuration, performs the aerodynamic load (basically radial and tangential) absorption function.

[0093] Obviously, depending on the size of the blade cascade 32 and the load to be absorbed, the reverser 30 may include additional and / or otherwise constructed tracks.

[0094] Figure 12 The contact block 72, fastened to the housing 11A, is shown, which allows the blades 32 to be positioned radially, substantially absorbing the radial loads they bear and / or compensating for clearance, particularly in forward thrust configurations.

[0095] Such contact blocks 72 thus form radial stops that can be regularly distributed around axis A1.

[0096] exist Figure 6 In the example, the fixing structure 31 of the inverter 30 includes such a contact block 72 mounted on the outer surface of a portion 44 of the circumferential section 42.

[0097] exist Figure 13 In one embodiment, the circumferential section 42 of the fixing structure 31 of the reverser 30 forms an axial flange 73, and the blade cascade 32 includes a stop 74, which in this example is supported by the front frame 32A of the blade cascade 32.

[0098] The stop 74 of the blade cascade 32 is configured to engage with the axial flange 73 of the fixing structure 31 when the blade cascade 32 is in the retracted position, thereby forming an axial travel end and a radial stop that can reduce the deformation of the blade cascade 32.

[0099] In one embodiment not shown, the fixing structure 31 and / or housing 11 and / or 11A of the reverser 30 may include tangential stops for the blade 32 in the forward position and / or retracted position.

[0100] Such axial and / or radial and / or circumferential stops can improve the distribution and absorption of the load on the blade cascade 32 and reduce the load on the cylinder (not shown) used to move the blade cascade 32 and the movable cover 33, especially in reverse thrust configurations where the cylinder is typically at the end of its stroke.

[0101] In this example, the fixing structure 31 of the reverser 30 includes a component (not shown) for supporting the cylinder, and thus optimizes the load path when the configuration of the reverser 30 is changed.

[0102] The above description illustrates the multifunctional principle of the fixing structure 31 of the present invention, which enables the reduction of the compactness of the reverser 30 and the mass and cost of the propulsion unit 1.

[0103] Of course, the present invention is not limited to the embodiments described above. For example, the reverser 30 may have a C-shaped or O-shaped pipe structure, and its fixing structure 31 may not have a lower beam 41.

Claims

1. A thrust reverser for an aircraft propulsion unit, having a longitudinal central axis and including a fixed structure, at least one shroud and deflecting blades, wherein the at least one shroud and deflecting blades are movable relative to the fixed structure during translation along the longitudinal central axis between a forward thrust position and a retracted reverse thrust position, characterized in that, The fixed structure has an annular shape extending about a longitudinal central axis and is configured to be rigidly fastened to the rear end of the turbine engine casing of the propulsion unit to form an axial extension of the casing. When at least one shroud and blade array are in the reverse thrust position, the fixed structure forms a deflection edge intended to deflect airflow through the blade array. At least one shroud is rotatable about a pivot between a closed flight position and an open maintenance position. The fixed structure includes a lower beam and an upper beam. The lower beam is circumferentially disposed opposite the mast of the propulsion unit and is configured to engage with at least one shroud when the at least one shroud is in the closed position. The upper beam is circumferentially disposed at the mast of the propulsion unit and includes a grid module extending circumferentially to at least one side of the mast and forming a front end. The front end extends circumferentially along a radial flange of the fixed structure and is configured to fasten the fixed structure to the casing.

2. The reverser of claim 1, wherein the upper beam is configured to cooperate with at least one shroud to enable the transfer of load from at least one shroud to the turbine engine housing and / or from at least one shroud to the propulsion unit mast.

3. The reversing device of claim 1, wherein the fixing structure includes elements for guiding the blade cascade between the forward position and the retracted position.

4. The reversing device of claim 2, wherein the fixing structure includes elements for guiding the vane cascade between a forward position and a retracted position, and wherein the upper beam supports at least one of the elements of the guide vane cascade.

5. The inverter according to claim 3, wherein, The lower beam supports at least one of the elements of the guide vane cascade.

6. The reverser according to claim 1, wherein the fixing structure includes a member that forms a radial and / or tangential and / or axial stop for the blade cascade.

7. A propulsion unit for an aircraft, comprising a turbine engine and a reversing device according to any one of claims 1 to 6.

8. The propulsion unit according to claim 7, wherein the housing is formed by a fan housing of a turbine engine or by an intermediate housing extending axially to the rear of the fan housing.

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