Turbomachine module comprising a post locking to a locking plate

Abstract

The invention relates to an aircraft turbomachine module comprising two tubular casings equipped with a first and a second annular flange assembled by means of studs (24a, 24b) received in the first flange and receiving a nut on the back of the second flange, each stud comprising a hexagonal intermediate extension (34a, 34b) cooperating with a fitting plate (36) comprising a first orifice (38, 38a) received on said intermediate extension (34, 34a) by means of at least two opposite walls (58, 58a), the fitting plate (36) comprising a transverse body (40) fixed to prevent the rotation of said plate (36) and of the stud (24, 24a, 24b), characterized in that each plate (36) is fitted on two contiguous studs (24a, 24b) and that the body (40) for this comprises a similar second orifice (38b) opposite the first orifice (38a) received on the intermediate extension (34b) of the contiguous stud (24b) and cooperating with the hexagonal intermediate extension (34b) of said stud (24b).

Description

Technical Field

[0001] This invention relates to the field of turbines, and more particularly to turbine modules constituting turbines. Background Technology

[0002] In a known manner, a turbine is assembled during its final installation by assembling modules, including a compressor module, a combustion chamber module, and a turbine module assembled together. Each module includes a stationary element or stator that receives a rotatable element or rotor, which carries compressor blades or turbine blades depending on whether the module is a compressor module or a turbine module. The stator is constructed from an assembly of tubular housings, the tubular housings including annular flanges for attaching the tubular housings, the annular flanges being assembled to each other by bolts.

[0003] Typically, the annular flange of the tubular shell is assembled together by a column and a nut.

[0004] Therefore, the assembly of the first annular flange of the first tubular housing and the second annular flange of the second tubular housing is carried out via a series of posts, which are fixedly received in the first annular flange, more specifically in retainer nuts attached to the back of the first annular flange for fixation. Assembly is also carried out by a series of corresponding nuts fastened to the back of the second annular flange. In particular, the first flange carrying the posts receives the second flange, the holes of the second flange being threaded to the posts, thus the second annular flange is bolted to the first annular flange by nuts received at the ends of the posts.

[0005] This assembly is subjected to high levels of vibration and thermal constraint during operation, which will generate stress on the bolted joints and may cause them to loosen.

[0006] To avoid this phenomenon, methods are usually proposed to fix the rotation of the column to prevent the column from coming off the retaining nut that receives the column.

[0007] For this purpose, the end of the column typically includes a hexagonal central extension to secure it and prevent rotation. For each column, this central extension is secured relative to the second flange by a generally transverse locking plate comprising a hexagonal orifice received in the hexagonal central extension, and a body extending transversely relative to axis C, which is fixed to prevent rotation of the plate and the column. The body includes two radial protrusions extending to the outer periphery of the second annular flange, and two radial tabs nested on the outer periphery of the second annular flange. As a result, the body, secured relative to the second annular flange, prevents rotation of the hexagonal central extension of the column, thereby preventing rotation of the column itself.

[0008] In current turbines, locking plates are used on each column, which significantly reduces the overall weight of this assembly. However, these locking plates must be machined, increasing costs. Finally, the installation of the locking plates requires more installation time for the first and second flange assemblies, further increasing the final cost of this assembly.

[0009] On the one hand, since the columns are not usually distributed at an angle in a uniform manner around the outer periphery of the flange (which would force the flange to be mounted relative to each other at a given angular position), and on the other hand, since the cost of manufacturing such a disc or plate and the associated machining would make the manufacturing cost too high, it is not conceivable to replace the locking plate with a single locking disc or single locking plate that includes all the hexagonal orifices.

[0010] On the other hand, a ventilated metal plate is typically inserted axially between the annular flanges. This metal plate is attached to the second annular flange by screws, the ends of which protrude from the outer surface of the second flange. The presence of these screws necessitates additional machining of this locking plate or locking disc so that it can be supported on the second flange.

[0011] In another known design in the prior art, a locking plate for accommodating two angled, continuous pillars is proposed in document US-2003 / 0118399-A1. However, this plate is incompatible with the aforementioned protruding screws.

[0012] Therefore, there is indeed a need for a locking plate that is economical to manufacture, easy to install, and adaptable to different column center distances and screws with protruding attachment points. Summary of the Invention

[0013] The present invention overcomes the shortcomings of known locking plates in the prior art by proposing a simplified locking plate, which is fixed by a common support between at least two columns.

[0014] To address this, the present invention proposes an aircraft turbine module comprising a first tubular housing having an axis X and a second tubular housing having an axis X. The first tubular housing is equipped with a first annular flange, and the second tubular housing is equipped with a second annular flange. The second annular flange is assembled to the first annular flange by a plurality of pillars having an axis C parallel to the axis X and distributed around the axis X. Each pillar passes through the second flange and includes an end portion that protrudes from the outer surface of the second flange and is capable of receiving a fastening nut. Each pillar portion also includes a hexagonal intermediate extension. The turbine module includes at least one locking plate applied to the second annular flange. The at least one locking plate includes a first orifice received in the intermediate extension, and at least two opposing walls of the first orifice mate with the hexagonal intermediate extension. The assembly plate covers... The aircraft turbine module comprises a body extending transversely to axis C, the body being fixed to prevent rotation of the plates and to prevent rotation of the columns about the axis of the columns. Each plate is mounted on two adjacent columns, and the body for this purpose includes a second orifice opposite to a first orifice, the second orifice being received in the intermediate extension of the adjacent columns, and at least two opposing walls of the second orifice engaging with the hexagonal intermediate extension of the adjacent columns. The aircraft turbine module is characterized by comprising an annular metal plate attached between a first flange and a second flange by screws having an axis B, the screws being distributed about and parallel to axis X, and each screw being angled between two consecutive columns. Each screw includes an end protruding from the outer surface of the second flange, the end being received with a gap in a groove formed in the transversely extending body of each mounted plate.

[0015] Based on other characteristics of the turbine module:

[0016] - Each column is fixedly received in the first flange.

[0017] The opposing walls of the first and second orifices are parallel to a direction that passes through the axis of the column, and at least one column is capable of sliding in at least the first and second orifices in said direction.

[0018] - At least one of the first and second openings is a U-shaped open opening that opens at one end of the body and includes two bottom walls that are complementary to the two panels of the hexagonal central extension and connect the two opposing walls.

[0019] - The first and second openings are identical and open relative to each other at opposite ends of the body.

[0020] - One of the first and second openings is hexagonal in shape and complements the hexagonal extension in the middle of the column.

[0021] - At least one of the first and second orifices is in the form of an oblong hole, the oblong hole being defined by two opposing walls, and each of the ends of the oblong hole being defined by a mating wall.

[0022] One of the first and second openings is hexagonal in shape, and the other of the first and second openings is oblong in shape. The openings are located at opposite ends of the main body.

[0023] - One of the first and second openings is hexagonal in shape, and the other of the first and second openings is an open opening shaped like a U. The openings are arranged at opposite ends of the body. Attached Figure Description

[0024] Other features and advantages of the invention will become apparent from the following detailed description, and with reference to the accompanying drawings, in order to understand it:

[0025] [ Figure 1 ] Figure 1 This is a cross-sectional view of the assembly of the first tubular shell and the second tubular shell.

[0026] [ Figure 2 ] Figure 2 This is a perspective view of a locking plate according to the prior art, which is supported on a second annular flange and received on a post portion of a first annular flange.

[0027] [ Figure 3 ] Figure 3 This is a perspective view of the assembly of the first and second annular flanges.

[0028] [ Figure 4 ] Figure 4 It is an unobstructed perspective view showing only the second annular flange equipped with a ring-shaped metal plate.

[0029] [ Figure 5 ] Figure 5 This is a front view of a first embodiment of the present invention. The first embodiment includes a locking plate with two pillars, the locking plate including two open holes shaped like a U.

[0030] [ Figure 6 ] Figure 6 This is a front view of a second embodiment of the present invention. The second embodiment includes a locking plate with two pillars, the locking plate including a hexagonal opening and an opening including an oblong hole. Detailed Implementation

[0031] In the following description, the same reference numerals denote the same or similar parts.

[0032] Figure 1 A portion of an aircraft turbine module is shown. In a known manner, a turbine module includes a rotor that typically carries blades (not shown), which are surrounded by a stator composed of assemblies of tubular housings assembled together. For example, such assemblies include a series of tubular housings associated with different stages of a high-pressure turbine, a turbine center frame (TCF) inter-turbine housing, and a series of tubular housings associated with different stages of a low-pressure turbine. Figure 1 Detailed views of an assembly of a first tubular housing 12 (here, a low-pressure turbine housing) having an axis X and a tubular housing 14 (also having an axis X, a TCF turbine inter-housing housing) are shown in a non-limiting manner according to the invention. It should be understood that this arrangement does not limit the invention, and the invention can relate to assemblies of any two tubular housings.

[0033] A first tubular housing 12 is equipped with a first annular flange 16, and a second tubular housing 14 is equipped with a second annular flange 18. The second annular flange is assembled to the first annular flange 16 by a plurality of posts having an axis C parallel to the axis X, and the plurality of posts being distributed around the axis X. The first annular flange 16 is centered in the second annular flange 18, for example, by an annular collar 20, which extends from the second flange 18 and receives the outer periphery of the first flange 16. Figure 1 A single column 24 is shown in the figure.

[0034] Each post 24 is fixedly received in the first flange 16. The post 24 may, for example, be received in a non-open thread of the first flange 16; however, preferably, it is received in a retaining nut 26. The post 24 passes through the first and second flanges and includes an end 28 projecting from the face 30 of the second flange 18. The post 24 receives a fastening nut 32 at its end 28, such as... Figure 1 and Figure 3 As shown.

[0035] The column portion 24 also includes a polygonal intermediate extension 34, which is designed to allow the column portion 24 to be fixed without rotation. In the accompanying drawings, a hexagonal intermediate extension 34 is shown; however, it should be understood that this configuration does not limit the invention, and the intermediate extension may be, for example, splined or have a square cross-section.

[0036] In order to enable the column 24 to be fixed without rotation by the intermediate extension 34 of the column, the turbine module includes at least one locking plate 36, which is applied to the second annular flange 18 and is fitted to each column 24.

[0037] like Figure 2 As shown, the locking plate 36 includes a first opening 38, which is received in and passed through the intermediate extension 34 of the post portion 24. The first opening 38 includes at least two opposing walls 58 that mate with the hexagonal intermediate extension 34.

[0038] Typically, the aperture 38 is shaped as a polygon (hexagonal in this case) aperture 38, which is complementary to and nested into the polygonal intermediate extension 34. Here, the aperture 38 thus includes three pairs of opposing walls 58 corresponding to the six panels of the hexagon.

[0039] The locking plate 36 also includes at least one body 40 extending transversely to the axis C, which is fixed to prevent the locking plate 36 from rotating and thus prevent the column 24 from rotating.

[0040] According to the prior art, the body 40 includes two curved protrusions 42, which are designed to support the outer periphery 44 of the second annular flange 18.

[0041] like Figure 1 As shown, the turbine module may also include a support plate 45, which is inserted into the column 24 between the locking plate 36 and the nut 32.

[0042] In this configuration, each column 24 is thus secured and does not rotate by a locking plate 36. Therefore, it is necessary to use as many locking plates 36 as there are columns 24. This configuration increases the cost of assembling the turbine module due to the numerous assembly operations required. Furthermore, these locking plates 36 are typically machined such that the curved protrusions 42 of the locking plate mate with the outer periphery 44 of the second annular flange 18, making these locking plates particularly expensive.

[0043] This invention overcomes this drawback by proposing a simplified locking plate that uses alternative support members.

[0044] According to the present invention, such as Figure 5 and Figure 6 As shown, in order to fix the column portion 24a in place by the intermediate extension portion 34a of the column portion without rotation, as previously described, the turbine module includes at least one locking plate 36, which is applied to the second annular flange 18 and is fitted to each column portion 24a.

[0045] The locking plate 36 includes a first opening 38a, which is received in the intermediate extension 34a, and at least two opposing walls 58a of the first opening mate with the hexagonal intermediate extension 34a.

[0046] As previously described, the locking plate 36 includes at least one body 40 extending transversely to the axis C, which is fixed to prevent the locking plate 36 from rotating and thus prevent the column portion 24a from rotating.

[0047] To provide further support, according to the invention, each plate 36 is fitted to a column portion 24a and also to an adjacent column portion 24b. For this purpose, the body 40 includes a second opening 38b opposite to the first opening 38a, the second opening being received in the intermediate extension 34b of the adjacent column portion 24b. The second opening 38b includes at least two opposing walls 58b, which mate with the hexagonal intermediate extension 34b of the adjacent column portion 24b.

[0048] In a known manner, such as Figure 1 and Figure 4 As shown, the turbine module may include an annular metal plate 46 mounted between a first flange 16 and a second flange 18. This metal plate 46 serves as an insulating metal plate. The metal plate 46 is attached to at least the second flange 18 by screws 48 having an axis B parallel to axis X, and the screws are distributed around axis X. Each screw 48 is arranged at an angle between two consecutive columns. Figure 4 A screw 48 is shown arranged in the second flange 18 between two holes 50, the holes being designed to allow the post 24 to pass through.

[0049] Each screw 48 includes an end 52 that protrudes from the outer surface 30 of the second flange 18.

[0050] Therefore, advantageously, the installation of the turbine locking plate 36 will not interfere with the protruding end 52.

[0051] In a standard installation, each locking plate 36 is independent, so the protruding end 52 of the screw 48 does not interfere with these locking plates 36.

[0052] According to the invention, alternatively, the laterally extending body 40 of each mounting plate 36 needs to include at least one recess 54 in which the protruding end 52 of the screw 48 is received with a gap. This configuration makes it possible to ensure that the plate 36 is mounted around the end of the screw.

[0053] Advantageously, plate 36 is adapted to different column center distances 24a, 24b. This makes it possible to equip turbine modules of different sizes with plates 36 of the same size.

[0054] To enable this adaptability, the opposing walls 58a, 58b of the first orifice 38a and the second orifice 38b are parallel to a direction T that passes through the axis C of the pillars 24a, 24b, and at least one of the pillars 24a, 24b can slide along said direction T in at least one of the first orifice 38a and the second orifice 38b.

[0055] For example, such as Figure 5 As shown, at least one of the first and second orifices (in this case, two orifices 38a and 38b) is formed as a U-shaped open orifice, each of the U-shaped open orifices being open at the corresponding ends 60a and 60b of the body 40. Thus, orifices 38a and 38b are open at opposite ends 60a and 60b.

[0056] Each of the openings 38a and 38b includes two bottom walls 62a and 32b, which are complementary to the two panels of the hexagonal intermediate extensions 34a and 34b and connect the two opposing walls 58a and 58b. Therefore, the plate 36 can fix at least two and at most four of the six panels of each hexagonal intermediate extension 34a and 34b.

[0057] In already Figure 5 In the first embodiment shown, the first aperture 38a and the second aperture 38b are identical and open away from each other at opposite ends 60a, 60b of the body 40.

[0058] Therefore, plate 36 can be arranged on any pair of posts 24a, 24b, the center distance of which is at least equal to a minimum distance at which the intermediate extension 34a is supported against the walls 62a, 62b, and for any greater center distance of the pair of posts, as long as the posts 24a, 24b do not disengage from the openings 38a, 38b. For the posts 24a, 24b, the intermediate extension 34a is not supported against the walls 62a, 62b at any center distance, therefore plate 36 has sliding freedom in direction T, but is fixed by tightening the nut 32.

[0059] like Figure 6 As shown, at least one of the first orifice 38a or the second orifice 38b can be hexagonal in shape and complementary to the hexagonal intermediate extension 34a or 34b of the column portions 24a, 24b, while the other orifice provides freedom of movement in the T direction to accommodate different center distances. Therefore, the other orifice can be as described above. Figure 5 The description refers to the U-shaped open opening.

[0060] However, in order to provide this freedom of movement, such as Figure 6As shown, at least one of the first aperture 38a and the second aperture 38b may also be in the form of an oblong aperture, which is defined by two opposing walls and by a mating wall at each end of the oblong aperture. Figure 5 An orifice 38b in the form of an oblong hole is shown, which is defined by two opposing walls 58b and by an arc-shaped joining wall at each end of the oblong hole.

[0061] Therefore, in Figure 6 The second embodiment of the present invention is shown in the figure. The second embodiment includes a hexagonal first aperture 38a and a second aperture 38b shaped like an oblong hole, with apertures 38a and 38b arranged at opposite ends of the body 40.

[0062] It should be understood that the main body 40 may also include two orifices 38a and 38b shaped like oblong holes, provided that these orifices include opposing walls 58a and 58b parallel to the direction T, and the direction T passes through the axis C of the column portions 24a and 24b.

[0063] Therefore, the present invention enables the connecting posts 24a and 24b of the tubular housing to be fixed without rotation by reducing the number of locking plates.

Claims

1. An aircraft turbine module comprising a first tubular housing (12) having an axis X and a second tubular housing (14) having an axis X, the first tubular housing being provided with a first annular flange (16) and the second tubular housing being provided with a second annular flange (18), the second annular flange being assembled to the first annular flange (16) by a plurality of posts (24, 24a, 24b), the plurality of posts having an axis C parallel to the axis X and being distributed around the axis X, each post passing through the second annular flange (18) and including an end (28) protruding from an outer surface (30) of the second annular flange (18) and capable of receiving a fastening nut (32), each post (24, 24a, 24b) further comprising a hexagonal intermediate extension (34, 34a, 34b). The aircraft turbine module includes at least one locking plate (36) applied to the second annular flange (18), the at least one locking plate including a first aperture (38, 38a) received in the intermediate extension (34, 34a), and at least two opposing walls (58, 58a) of the first aperture engaging with the hexagonal intermediate extension (34, 34a), the locking plate (36) including a body (40) extending laterally relative to the axis C, the body being fixed to prevent rotation of the locking plate (36) and to prevent rotation of the column portions (24, 24a, 24b) about the axis C of the column portions. Each locking plate (36) is fitted onto two adjacent pillars (24a, 24b), and the body (40) for this purpose includes a second opening (38b) opposite to the first opening (38a), the second opening being received in the intermediate extension (34b) of the adjacent pillar (24b), and at least two opposing walls (58b) of the second opening engaging with the hexagonal intermediate extension (34b) of the adjacent pillar (24b). Its features are, The aircraft turbine module includes an annular metal plate (46) attached between a first annular flange (16) and a second annular flange (18) by screws (48) having an axis B. The screws are distributed around and parallel to the axis X, and each screw is arranged at an angle between two consecutive columns (24). Each screw (48) includes a screw end (52) protruding from the outer surface (30) of the second annular flange. The screw end is received in a groove with a gap, the groove being formed in the laterally extending body (40) of each assembled locking plate (36).

2. The aircraft turbine module according to claim 1, characterized in that, The opposing walls (58a, 58b) of the first orifice (38a) and the second orifice (38b) are parallel to a direction (T) that passes through the axis C of the column (24a, 24b), and at least one column (24b) is capable of sliding in at least one of the first orifice (38a) and the second orifice (38b) in the direction (T).

3. The aircraft turbine module according to claim 2, characterized in that, At least one of the first opening (38a) and the second opening (38b) is a U-shaped open opening that opens outward at one end (60a, 60b) of the body (40) and includes two bottom walls (62a, 62b) that are complementary to the two panels of the intermediate extension (34a, 34b) of the hexagon, and the two bottom walls connect the two opposing walls (58b).

4. The aircraft turbine module according to claim 3, characterized in that, The first opening (38a) and the second opening (38b) are identical and open relative to each other at opposite body ends (60a, 60b) of the body (40).

5. The aircraft turbine module according to claim 2, characterized in that, One of the first opening (38a) and the second opening (38b) is hexagonal in shape and is complementary to the hexagonal middle extension (34a) of the column (24a).

6. The aircraft turbine module according to claim 2, characterized in that, At least one of the first orifice and the second orifice (38b) has the shape of an elongated hole, which is defined by two opposing walls (58b) and by a joining wall (64b) at each end of the elongated hole.

7. The aircraft turbine module according to claim 5, characterized in that, At least one of the first orifice and the second orifice (38b) has the shape of an elongated hole defined by two opposing walls (58b) and by a joining wall (64b) at each end of the elongated hole. One of the first orifice and the second orifice (38a) is hexagonal in shape, and the other of the first orifice and the second orifice (38b) is shaped like an elongated hole. The first orifice and the second orifice are arranged at opposite ends of the body.

8. The aircraft turbine module according to claim 3, characterized in that, One of the first opening (38a) and the second opening (38b) is hexagonal and complementary to the hexagonal middle extension (34a) of the column (24a). The other of the first opening and the second opening is a U-shaped open opening. The first opening and the second opening are arranged at opposite ends of the body (40).

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