Stator component for a turbine engine equipped with at least one fin, and method for installing at least one fin in a stator component

Abstract

The invention relates to a stator component (21) of a turbine engine (1), in particular of an aircraft, the stator member extends around a longitudinal axis and comprises two circumferentially adjacent stator blades (20, 20 '), each comprising a paddle (22) extending radially from an annular wall (23) centered on the longitudinal axis, the stator member comprising a fin (25) arranged circumferentially between the two stator blades (20, 20'). According to the invention, the annular wall comprises a recess (28) formed in its body having a predetermined shape, opening into a radially outer surface (23a) of the annular wall and at a distance from upstream and downstream edges (24a, 25b) of the annular wall, the fin comprising a root portion (26) having a shape matching the recess, the root portion being intended to be removably arranged in the recess, and a fin body (27) having a shape matching the root portion and intended to be removably arranged in the recess. The fin body extends radially from the root and elongate in an elongate direction substantially parallel to the longitudinal axis.

Description

TECHNICAL FIELD

[0001] The present invention relates to the field of turbine engines, in particular the field of turbine engines of an aircraft, in which air flows from upstream to downstream. More particularly, but not exclusively, the present invention relates to a stator member of a turbine engine comprising stator vanes and at least one fin. The present invention also relates to a method for mounting at least one fin in a stator member. BACKGROUND

[0002] Aircraft turbine engines can be equipped with one or more stator members, such as stator vane stages of a compressor or a turbine. Turbines and compressors generally comprise multiple stages of stator vanes and movable vanes alternating along a longitudinal axis of the turbine engine. The stator vanes extend radially between both a radially inner wall and a radially outer wall. The air flow passes through the compressor and the turbine, between the respective stages of stator vanes and movable vanes. The stator vanes enable the air flow to be rectified downstream of the movable vanes. However, when the air flow interacts with the stator vanes, vortexes are generated at the radially inner wall. The vortexes can generate friction losses and, if they impinge on the suction side of the stator vanes, also cause aerodynamic separation.

[0003] Fins have been placed between adjacent stator vanes to reduce or even eliminate these vortexes. These fins are generally smaller than the stator vanes. There are multiple examples of fins, such as those described in patent documents US-A1-2018 / 017079, FR-B1-3106614, FR1854134 and FR3081185. However, in most cases, the arrangement of these fins in the stator member seems complex, for example with respect to the radially inner wall, and the fins do not seem to be easily assembled and / or removed without disassembling the stator member and / or the entire module for maintenance. The geometry of some fins is very thin, which can quickly wear out and require regular replacement. On the other hand, these fins can be mounted on platforms that have complex retaining means on the radially inner wall, and that can cause disturbances in the air flow. Furthermore, the shape of the fins can not be suitable for the sought performance or mission, and it can not be possible to solve this problem of shape. These drawbacks are detrimental to the performance of the turbine engine.

[0004] There is a need to address some or all of the above-mentioned drawbacks. SUMMARY

[0005] The object of the present invention is to provide a simple, cost-effective and robust solution that enables the integration of fins into a stator member safely and efficiently.

[0006] According to the invention, this is achieved by means of a stator member of a turbine engine, in particular of an aircraft, extending around a longitudinal axis, comprising at least one first stator blade and at least one second stator blade which are circumferentially adjacent, each comprising a paddle extending radially from an annular wall centered on the longitudinal axis, the stator member comprising a fin arranged circumferentially between the first stator blade and the second stator blade, the annular wall comprising a recess with a predetermined shape formed in the thickness of said annular wall, said recess opening onto a radially outer surface of the annular wall and being spaced apart from an upstream edge and a downstream edge of the annular wall, the fin comprising a root and a fin body, the shape of said root being complementary to the recess, said root being configured to be arranged removably in the recess, said fin body extending radially from the root and being elongated in a direction substantially parallel to the longitudinal axis.

[0007] This solution thus makes it possible to achieve the above-mentioned objectives. In particular, the arrangement of fins, considered as a passive system, improves the operability of the turbine engine by limiting or even eliminating the flow between two adjacent stator blades of the stator member. Each fin forms a wall close to the stator blade which blocks the wall flow from the pressure side surface of the paddle of the adjacent stator blade. The configuration of the recess and the corresponding root shape make it possible to optimize the integration of the fin into the annular wall of the stator member and to secure the fin in a simple, quick and effective manner. The configuration of the recess and the root also makes it possible to easily replace each fin, for example under the wing, without having to disassemble the entire module, in particular the entire stator grid. The fins can be designed with different shapes according to the task to be performed, which makes the system more flexible and optimized. In addition, replacing the fins means cost savings, flexibility in the shape of the fins depending on the required performance, and a reduction in the impact on the environment.

[0008] The stator member also comprises one or more of the following features and / or steps, taken alone or in combination: - the root extends along the axis of revolution and comprises a base and a separate platform connected by a stem along the axis of revolution A.

[0009] - the base has two lugs which have the same shape and are arranged on either side of the stem in a plane perpendicular to the axis of revolution.

[0010] - the fin is made of a material or formed from an assembled monolithic piece.

[0011] - the recess comprises three parts configured to receive one of the elements forming the root respectively.

[0012] - the recess comprises a first portion having a shape corresponding to the shape of the platform, the platform having an outer surface having surface continuity with the radially outer surface of the annular wall.

[0013] - the recess comprises a second portion and a third portion, each having a shape similar to the shape of the base, at least one dimension of the third portion being greater than the dimensions of the second portion and of the base.

[0014] - the fin comprises a blocking device for blocking the root in the recess.

[0015] - the blocking device comprises a locking element arranged in the cavity of the base, the locking element being configured to occupy a locked position and an unlocked position, and a retaining element for retaining the locking element in its locked position, the retaining element being arranged in the recess.

[0016] - the blocking device comprises a return element mounted in the cavity and configured to continuously urge the locking element towards the locked position.

[0017] - the recess comprises at least one groove configured to receive at least one portion of the locking element in the unlocked position.

[0018] - the recess and the root of the fin are configured so that the fin pivots between an inactive position, in which the elongation direction of the fin body is transverse to the longitudinal axis, and an active position, in which the elongation direction of the fin body is substantially parallel to the longitudinal axis.

[0019] - the second portion of the recess opens out both to the first portion of the recess and to the third portion of the recess.

[0020] The invention relates to a turbomachine, in particular a turbomachine of an aircraft, comprising at least one stator member having any of the preceding features.

[0021] The invention also relates to a method of mounting at least one fin in a stator member as described above. The method comprises the following steps: - positioning the root of the fin in the recess in a complementary shape so that the elongation direction of the fin body is transverse to the longitudinal axis, and - rotating the root of the fin in the recess about the axis of revolution A to orient the elongation direction of the fin body substantially parallel to the longitudinal axis. BRIEF DESCRIPTION OF DRAWINGS

[0022] The invention will be better understood and other objectives, details, features, and advantages of the invention will become clearer from reading the detailed explanatory description of an embodiment of the invention given solely by way of example and without limitation, with reference to the accompanying drawings in which: - Figure 1 is a perspective view of a turbomachine according to the invention, in particular a turbomachine of an aircraft, comprising at least one stator member according to the invention, in particular a stator member of an aircraft, comprising at least one fin according to the invention, in particular a fin of an aircraft, - Figure 2 is a perspective view of a stator member according to the invention, in particular a stator member of an aircraft, comprising at least one fin according to the invention, in particular a fin of an aircraft, - Figure 3 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, - Figure 4 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, in an inactive position, - Figure 5 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, in an active position, - Figure 6 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, in an inactive position, in which the root of the fin is positioned in the recess of the stator member, - Figure 7 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, in an active position, in which the root of the fin is positioned in the recess of the stator member, and - Figure 8 is a perspective view of a fin according to the invention, in particular a fin of an aircraft, in an active position, in which the root of the fin is positioned in the recess of the stator member. Figure 1 is an axial cross-sectional view of an example of a turbomachine to which the application applies; Figure 2 is a detailed perspective view of an example of a stator member comprising stator vanes and fins according to the application; Figure 3 shows a perspective view of an example of a fin configured to be removably integrated into a stator member according to the application; Figure 4 is a perspective view of another embodiment of a fin according to the application; Figure 5 shows an example of a recess formed in an annular wall of a stator member according to the application; Figure 6 is a detailed view of a portion of the recess shown in Figure 5 ; Figure 7 is a perspective view of a step of inserting a fin into a recess of an annular wall of a stator member according to the application; Figure 8 is a perspective view of a rotation step of rotating a fin in a recess as shown in Figure 7 ; Figure 9 is a perspective view of a fin mounted and secured between two adjacent stator vanes according to the application; Figure 10 is a partial perspective view of a portion of a root of a fin in a portion of a recess of an annular wall according to the application; Figure 11 is a cross-sectional view of an example of a fin secured in a recess formed in an annular wall according to the application; and Figure 12 shows a flowchart of a method for mounting at least one fin in a stator member according to the application. DETAILED DESCRIPTION

[0023] Figure 1 A turbomachine 1 to which the application applies is shown. The turbomachine 1 is a double-flow double-body turbomachine configured to be mounted on an aircraft, such as an airplane. Of course, the application can apply to other types of turbomachines, such as turbofan engines, turboprop engines or turboshaft engines, and it can be ducted and non-ducted.

[0024] ​​​​​​​​​​​​In the present invention, generally, the terms "upstream" and "downstream" are relative to the flow through of the gas or air flow in the turbine engine and are defined here along the longitudinal axis X. The terms "axial" and "axially" are defined relative to the longitudinal axis X. The terms "external", "out", "internal", "in" and "radial" are defined relative to a radial axis Z extending from the longitudinal axis X and relative to the distance from the longitudinal axis X. The radial axis is perpendicular to the longitudinal axis.

[0025] The illustrated turbine engine comprises a fan 2 mounted upstream of a gas generator 3 or (gas turbine) engine.

[0026] The gas generator 3 comprises, from upstream to downstream, a low pressure compressor 4, a high pressure compressor 5, a combustion chamber 6, a high pressure turbine 7 and a low pressure turbine 8. Generally, the turbine engine 1 comprises a low pressure shaft (not shown) connecting the low pressure compressor 4 and the low pressure turbine 8 to form a low pressure body and a high pressure shaft 10 connecting the high pressure compressor 5 and the high pressure turbine 7 to form a high pressure body. The low pressure shaft centered on the longitudinal axis X is configured to drive a fan shaft (not shown). A power transmission mechanism 11, such as a reduction gear, can be interposed between the low pressure shaft and the fan shaft fixed on a hub of the fan 2.

[0027] The fan 2 comprises fan blades 12 carried by a hub having a longitudinal axis X and surrounded by a fan casing 13 carrying a nacelle (not shown). The fan 2 compresses the air flow entering the turbine engine 1, which is divided into a primary flow Fl passing through the gas generator and a secondary flow F2 flowing around the gas generator 3.

[0028] Each compressor 4, 5 and each turbine 7, 8 comprises a plurality of stator stages or stator members comprising stator blades 4a, 5a, 7a, 8a and a plurality of rotor stages comprising movable blades 4b, 5b, 7b, 8b along the longitudinal axis X. In the present invention, the term "stator blade" or "fixed blade" refers to a blade that is not driven to rotate around the longitudinal axis X of the turbine engine. In other words, the stator blades 4a, 5a, 7a, 8a are distinct from and opposite to the movable or rotor blades 4b, 5b, 7b, 8b of the turbine engine. The stator blades and the movable blades are arranged in annular rows and the stator blade stages 4a, 5a, 7a, 8a alternate with the movable blade stages 4b, 5b, 7b, 8b along the longitudinal axis X. The stator blades 4a, 5a, 7a, 8a deflect and straighten the primary flow Fl at the outlet of each movable blade 4b, 5b, 7b, 8b located upstream thereof.

[0029] Stator vanes 15 can be arranged downstream of the fan vanes 12 to straighten the secondary flow F2. These stator vanes 15 are referred to as outlet guide vanes (OGVs). The stator vanes 15 are arranged transversely in the nacelle in a plane that is transverse to the longitudinal axis X. In this example, the stator vanes 15 are evenly distributed around the axis X of the turbine engine 1.

[0030] Figure 2 A plurality of stator vanes 20 is shown fitted to the stator member 21. The stator vanes 20 are distributed circumferentially around the longitudinal axis X. The stator vanes 20 each comprise a blade 22 extending substantially radially from an annular wall 23 centered on the longitudinal axis X. The annular wall 23 extends along the longitudinal axis X between an upstream edge 24a and a downstream edge 24b. More precisely, the blade 22 extends radially between a radially inner wall and a radially outer wall (not shown) centered on the longitudinal axis X. The radially inner wall and the radially outer wall can be sectorized. In the remainder of the description, the radially inner wall is considered to be the annular wall 23, although the radially outer wall can be an annular wall.

[0031] Each blade 22 extends radially between a root end 22c and a tip end (not shown). Each blade 22 also comprises a pressure side surface 22i and a suction side surface 22e extending axially generally along the longitudinal axis X and connected upstream by a leading edge 22a and connected downstream by a trailing edge 22b. The pressure side surface and the suction side surface are opposite each other in the transverse direction. The root end 22c of each blade 22 is attached to the radially inner wall 23. Advantageously, the stator vanes 20 are identical and arranged longitudinally in the same way along the entire radially inner wall 23. In particular, the radially inner wall 23 and the blade 22 are a single piece. In other words, the blade 22 and the radially inner wall 23 (or radially inner wall sector) are integrally formed.

[0032] In the example shown in Figure 2 , at least one fin 25 is arranged between two circumferentially adjacent stator vanes 20. In this embodiment, a plurality of fins 25 alternate with the stator vanes 20 around the longitudinal axis X. The fin 25 is arranged close to the leading edge 22a of the blade 22 of the stator vane, but can be positioned in any area of the radially inner wall 23 that is between two adjacent stator vanes 20, 20'.

[0033] With reference to Figure 3 , each fin 25 comprises a root 26 and a fin body 27 extending radially from the root 26. The height hi of each fin 25 is generally between 5% and 15% of the height of the stator vane.

[0034] The fin body 27 is elongated in a direction substantially parallel to the longitudinal axis X (in the mounted state). In the example shown, the aerodynamic profile of the fin body 27 is substantially identical to the aerodynamic profile of the stator blade 20. This aerodynamic profile allows, on the one hand, to limit the passage of the vortex at the radial inner wall 23 and to control any aerodynamic separation between two adjacent stator blades 20. Of course, the fin body can have a different shape, such as a rounded shape similar to a hump, a symmetrical shape or a non-axisymmetrical shape. The fin body can have various shapes to adapt to the flow to be controlled and can be more or less steep.

[0035] More precisely, the fin body 27 comprises an upstream edge 27a and a downstream edge 27b connected by a suction side surface 27i and a pressure side surface 27e. The fin body 27 has a length LI measured between the upstream edge 27a and the downstream edge 27b, which is less than the length of each paddle of the stator blade 20. The length LI can be between 5% and 70% of the length of the paddle of the stator blade. In particular, the length LI of the fin body 27 must be such that the fin 25 can rotate between two stator blades (between the inactive position and the active position), as will be detailed later. In the present example, the upstream edge 27a of each fin body 27 is offset downstream of the leading edge 22a of the paddle of the stator blade along the longitudinal axis X. This axial offset can be between 0% and 40% of the chord (or chord line) connecting the leading edge 22a to the trailing edge 22b of the paddle 22 of the stator blade 20. Alternatively, the upstream edge 27a of each fin body 27 is aligned with the leading edge 22a of the paddle of the stator blade 20.

[0036] The root 26 is designed to be detachably fitted in a recess 28 of predetermined shape formed in the annular wall 23. The shape of the root 26 of each fin 25 is complementary to the corresponding recess 28. Thus, the fin 25 is configured to fit and be detachably fixed to the stator member 21, in particular to the radial inner wall 23.

[0037] More precisely, each root 26 extends along the axis of revolution A. Each root 26 comprises a base 29 and a platform 30 which are distinct and connected by a stem 31 along the axis of revolution A. In other words, the base 29 and the platform 30 are opposite each other along the axis of revolution A. In the mounted case, the axis of revolution A is parallel to the radial axis Z.

[0038] Advantageously, the stem 31 is cylindrical and has a circular cross-section. The fin body 27 is arranged on the platform 30 and extends radially outwardly from the platform 30. The platform 30 has a circular cross-section in order to facilitate the integration of the fin 25 into the radially inner wall 23 of the stator member 21. In particular, the platform 30 has an outer surface 30a and an inner surface 30b opposite each other along the axis of revolution A.

[0039] The platform 30 comprises a circular edge 30c connecting the outer surface 30a and the inner surface 30b. The fin body 27 is located on the outer surface 30a. Advantageously, but not limitatively, the upstream edge 27a and the downstream edge 27b of the fin body 27 are comprised in the edge 30c of the platform 30. In other words, the fin body 27 extends inside the edge 30c.

[0040] In another embodiment of the fin 25, illustrated in Figure 4 In this embodiment, the fin body 27 located on the outer surface 30a of the platform 30 extends beyond the edge 30c. In other words, the length LI of the fin body 27 is greater than the diameter of the platform 30. The root 26 in this embodiment is similar to the root 26 in the previous embodiment.

[0041] Each pedestal 29 has two identical shaped lugs 32, referred to as first lug 32a and second lug 32b. The lugs 32a, 32b are arranged on both sides of the stem 31 in a plane perpendicular to the axis of revolution A of the stem 31. Each lug 32a, 32b has an outer surface 33a and an inner surface 33b opposite each other along the axis of revolution A. The outer surface 33a and the inner surface 33b of the lugs 32a, 32b form the inner and outer surfaces of the pedestal 29. Each lug 32a, 32b further comprises two radially extending abutment surfaces 33c, 33d connected by a contact surface 33e. The abutment surfaces 33c, 33d are flat and are defined in a plane transverse to the plane defining the outer surface 33a and the inner surface 33b. The inner surface 33b and the outer surface 33a are connected by the abutment surfaces 33c, 33d and the contact surface 33e.

[0042] In this example, the lugs 32a, 32b have a triangular cross-section. The abutment surfaces 33c, 33d are connected to the contact surface 33e on the one hand and to the cylindrical outer surface 35 of the stem 31 on the other hand. Advantageously, but not limitatively, the contact surface 33e has a curvature. This curvature is defined by a circular arc, the center of which is located on the axis of revolution A. The abutment surfaces 33c, 33d form a predetermined angle with each other. Advantageously, the predetermined angle can be between 45° and 80°.

[0043] Advantageously but not limitatively, the fin is made of a material. In other words, the fin body 27, the platform 30, the stem 31 and the base 29 are formed as one piece or are formed of a material. This simplifies the manufacturing and the mounting of the fin. Alternatively, the fin can be formed of several one pieces, for example a fin body and a root, which are manufactured separately and assembled later using a fixation means such as welding, threaded members, adhesives, etc.

[0044] Advantageously but not limitatively, the base 29 comprises a wedging element configured to enable the correct assembly of the base in the recess 28 and to distinguish preferably the correct mounting direction. The wedging element comprises one of the first lug 32a and the second lug 32b of the base 29. At least one dimension of one of the first lug 32a and the second lug 32b is greater than at least one dimension of the other of the first lug and the second lug to form the wedging element. In the present example, the first lug 32a extends in an angular section in a plane perpendicular to the axis of revolution A, which angular section is greater than the angular section of the second lug 32b. A portion of the recess 28 has a shape complementary to the shape of the first lug 32a. Alternatively or additionally, the wedging element can of course comprise at least one pin or other component configured to cooperate with other components or portions formed in the recess 28.

[0045] In Figure 3 and Figure 4 , the blocking device 37 is configured to lock the root 26 of the fin 25 in the corresponding recess 28. Preferably, the blocking device 37 is self-locking. The term "self-locking" means that the locking or unlocking occurs automatically, without human intervention or the use of special additional accessories acting on the blocking device itself. However, the rotation of the fin is operated by an operator not covered by this definition. The blocking device 37 comprises a locking element 38 movable between a locked position and an unlocked position. In the present example, the locking element 38 is carried by the root 26. Alternatively, the locking element 38 is carried by the platform 30 or the stem 31. The blocking device 37 comprises at least one retaining element 39 for retaining the locking element 38 in the locked position.

[0046] The locking element 38 is mounted so that it can move in a cavity 40 (shown in dashed lines in Figure 3 ) formed in the base 29 of the root 26. However, the locking element 38 protrudes from a contact surface 33e of the base 29. The cavity 40 is substantially cylindrical along an axis B. The axis B is perpendicular to the axis of revolution A.

[0047] The blocking device 37 comprises a return element 41 configured to permanently push the locking element 38 towards the locked position. The return element 41 is mounted in the cavity 40.

[0048] The movable locking element 38 comprises a ball, a rod, a finger, etc. Preferably, the locking element 38 is a ball. The return element 41 is a compression spring. The return element 41 comprises a first end fixed to the bottom 40a of the cavity 40 and a second end fixed to the locking element, in this case a ball.

[0049] The retaining element 39 is arranged in each recess 28.

[0050] Figure 5 A portion of the radially inner wall 23 is more precisely shown, this portion comprising at least one recess 28 formed in the thickness of the wall 23 and opening onto the radially outer surface 23a of the wall 23. It can be seen that the recess 28 is advantageously positioned at a distance from the upstream edge 24a and the downstream edge 24b of the annular wall. This facilitates the assembly of each fin and avoids components arranged upstream of the upstream edge 24a of the annular wall or downstream of the downstream edge 24b of the annular wall which could hinder the assembly or disassembly of each fin 25.

[0051] The recess 28 has different portions configured to receive the corresponding elements forming the root 26. The different portions are positioned along the radial axis Z. In other words, the different portions are arranged at different depths in the thickness of the radially inner wall 23.

[0052] The recess 28 comprises a first portion 42 configured to receive the platform 30 of the root 26. The shape of the first portion 42 is similar to the shape of the platform. Here, the platform 30 and the first portion 42 have a circular cross-section and are shape-complementary. The platform 30 and the first portion 42 have the same height (along the radial axis). The first portion 42 comprises a bottom 42a defined in a plane perpendicular to the radial axis. A circular wall 42b rises from the bottom 42a (along the radial axis). The height of the first portion 42 is measured from this bottom. When installed, the outer surface 30a of the platform 30 has surface continuity with the radially outer surface 23a of the radially inner wall 23. The edge 30c of the platform cooperates with the circular wall 42b while allowing the platform 30 to rotate around the axis of revolution A.

[0053] The recess 28 also comprises a second portion 43, the shape of which corresponds to that of the base 29. In this example, the second portion 43 is delimited by a through hole on either side along the radial axis and is bounded by a radial wall 43b. In other words, the second portion 43 opens onto the bottom 42a of the first portion 42. More particularly, the shape of the second portion 43 has two sectors 44a, 44b which are opposite one another in a direction defined in a plane perpendicular to the radial axis. This shape is very similar to an hourglass. The second portion 43 also comprises a central region 44c, the cross-sectional wall of which is semi-circular in shape and is complementary to the cylindrical surface 31a of the stem 31. Advantageously, but not limitatively, the height of the second portion 43 is the same as or less than the height of the stem 31. In this example, the sector 44a of the second portion extends over a greater angular sector than the second sector 44b. The first sector 44a can accommodate the first lug of the base and the second sector can accommodate the second lug of the base 29. This function of the wedging element of the second portion 43 and of the lugs of the base 29 makes it possible for the root 26 to be inserted in the recess in the correct direction.

[0054] With reference to Figure 6 , the recess 26 comprises a third portion 45, which also has a shape corresponding to that of the base 29. The third portion 45 comprises a generally hourglass shape similar to that of the second portion 43, i.e. comprising two opposite sectors in a direction defined in a plane perpendicular to the radial axis. The second portion 43 opens onto the third portion 45. The third portion 45 is configured to receive the base 29 when it is mounted. However, the third portion 45 is larger than the second portion 42 and the base 29. This makes it possible for the base 29 to be rotated in the third portion of the recess 28.

[0055] To this end, the third portion 45 has a bottom 45a from which rises a radial wall 45b which defines its shape. The bottom 45a is defined in a plane perpendicular to the radial axis. The inner surface 33b of the base 29 is configured to lie on the bottom 45a of the third portion 45 of the recess. In this example, the area of the inner surface 33b of the base is substantially half the area of the bottom 45a of the third portion 45 of the recess.

[0056] For each sector 46a, 46b making up the third portion 45, the radial wall 45b comprises two opposite panels 47a, 47b which are connected by a curved partition 48. The two sectors are connected by a central region 49 having a semi-cylindrical wall. The opposite panels 47a, 47b of each sector form a predetermined angle with one another. Advantageously, the predetermined angle can be between 50° and 160°.

[0057] As mentioned previously, and as in Figure 6As can be seen, the recess 28 comprises a retaining element 39 for retaining the locking element 38 in its locked position. The retaining element 39 is formed in the curved partition 48. Here, the retaining element 39 is formed by a housing, the opening of which leads to the curved partition 48 at the third portion 45. Here, the housing has a circular cross-section.

[0058] The recess 28 further comprises at least one recess which is configured to receive at least a portion of the locking element 38 in the unlocked position. In particular, a first recess 50 is arranged in the curved partition 48 in the third portion 45. The first recess 50 is complementary to the locking element 38, in this case a ball, which protrudes from the base 29 in the unlocked position. In particular, the first recess 50 is arranged at a distance from the housing which receives the locking element 38 in the locked position.

[0059] A second recess 51 is arranged in the circular partition 52 of the second portion 43, in particular in the circular partition of one of the sections 44a, 44b of the second portion 43, here the first section. Advantageously, the second recess 51 is located in the central region of the partition 51. The second recess 51 is also complementary in shape to the locking element 38, in particular in the unlocked position.

[0060] Reference will now be made to Figures 7 to 11 The method of installing at least one fin 25 in a corresponding recess 28 of an annular wall 23 of a stator member 21 of a turbine engine will be described in detail. The method is illustrated in the flowchart of Figure 12 .

[0061] The method 100 comprises the step of positioning 101 the root 26 of the fin 25 in the recess 28 of the annular wall 23 of the stator member 21 in a complementary shape. During this positioning, a translation along the radial axis Z is performed. The radial translation facilitates assembly and avoids any obstacle to assembly and / or disassembly.

[0062] Before positioning the root 26 in the recess 28, the fin 25 is positioned such that the upstream edge 27a of the fin body 27 is positioned substantially opposite the suction side surface 22e of the paddle 22 of the first stator blade 20. In other words, the direction of elongation of the fin body 27 is transverse to the longitudinal axis. This is achieved by a wedging element, in this case the difference in size between the lugs 32a, 32b of the base 29 and the second portion 43.

[0063] During positioning, the base 29 first passes through the first portion 42 of the recess, then through the second portion 43 of the recess, stopping in the third portion 45.

[0064] After the root 26 has been positioned in the recess 28, the fin 25 is in the inactive position in which the elongation direction of the fin body 27 is transverse to the longitudinal axis. More particularly, the inner surface 33b of the base 29 is in contact with the bottom 45a of the third portion 45 of the recess and the inner surface 30b of the platform 30 is in contact with the bottom 42a of the first portion 42 of the recess. The contact surface 33a of each lug 32a, 32b is substantially complementary to the corresponding curvilinear partition 48. The stem 31 extends through the third portion and / or the second portion, in particular in the central region. The axis of the stem 31 serves as a rotation axis of the root in the recess 28. The locking element 38 (ball) of the blocking device 37 is inserted into the first groove 50. The locking element 38 occupies its unlocked position. The outer surface 30a of the platform is flush with the radially outer surface 23a of the annular wall 23. The platform 30 is arranged in the first portion 42 of the recess in a complementary shape.

[0065] The method 100 comprises a step of rotating 102 the root 26 of the fin in the recess 28 about the swivel axis A to orient the elongation direction of the fin body 27 substantially parallel to the longitudinal axis X. The elongation direction can have an angular offset from the longitudinal axis of between 5° and 20°. In particular, the fin 25 is pivoted between an inactive position in which the elongation direction of the fin body 27 is transverse to the longitudinal axis and an active position in which the elongation direction of the fin body 27 is substantially parallel to the longitudinal axis X. The rotation of the root 26 is achieved by the difference in cross section between the base 29 and the third portion 45 of the recess. Since the third portion 45 has a greater size than the base (angular sector of each sector), the base can easily be pivoted in the plane of the bottom 45a about the swivel axis. This rotation is facilitated on the one hand by the stem 31 which serves as a pivot and is housed in at least one central region of the complementary-shaped recess 28 and on the other hand by the platform 30 which is housed in the first portion 42 of the recess in a complementary shape. Similarly, since the platform 30, the stem 31 and the base 29 are one piece, the entire assembly is pivoted about the swivel axis.

[0066] The angle of rotation of the root is between 40° and 60°. The rotation of the root 26 is limited by at least one abutment. Alternatively or additionally, the rotation of the root 26 is limited by the blocking device 37, in particular when the locking element is housed in one of the first groove 50 and the second groove 51 or in the retaining element 39. In this example, the abutment is formed by one of the abutment surfaces 47a in the third portion 45 of the recess, as shown in Figure 10 Figure 10 ​The fins 25 are shown in their active position. The abutment surfaces 33c of the first lugs are in planar / flat contact with the panel 47a of the first section of the third portion 45, and the abutment surfaces 33d are in planar / flat contact with the panel 47b of the second section of the third portion 45. If the rotation is limited by the blocking means, the abutment surfaces 33c, 33d can be at a distance from the panels 47a, 47b of the recesses 28.

[0067] After rotation, the locking elements are housed in the housing of the third portion 45 provided for this purpose (forming the retaining element 39). When the root is rotated, the ball comes into contact with the curvilinear partition of the third recess 45 having a radius substantially equal to that of the lug, thus pushing the ball into the cavity 40. Once the ball is positioned opposite the housing (each lug resting against the panel of the third portion), the ball is returned to its unlocked position by the spring and is introduced into the housing to lock the root 26 of the fin 25 in the corresponding recess 28. We understand that simply rotating the fin 25 makes it possible to quickly and efficiently lock the fin in the recess 28 and on the annular wall 23.

[0068] Figure 11 The fin 25 is shown removably fixed in the annular wall 23, with the ball carried by the root 26 housed in the recess 28 and the fin body 27 oriented substantially along the longitudinal axis.

[0069] In this way, the configuration of the root 26 of the fin 25 and the recess 28 makes it possible to position the fin 25 precisely, quickly and efficiently in the annular wall 23 of the stator member, while ensuring sealing in the wall and facilitating replacement of the fin in the event of damage due to wear or breakage, or adjusting the shape of the fin body according to the mission. It is sufficient to access the stator member from upstream or downstream to replace / install the fin. Furthermore, in the case of an annular wall sector, installing the fin between two adjacent stator blades 20, 20' does not interfere with the sealing of the annular wall 23 and can be done independently of the connection area between the two annular wall sectors.

Claims

1. Stator member (21) of a turbomachine (1), in particular of an aircraft, extending around a longitudinal axis (X), comprising at least one first stator blade (20) and at least one second stator blade (20') which are circumferentially adjacent, the first and second stator blades (20, 20') each comprising a paddle (22) extending radially from an annular wall (23) centred on the longitudinal axis (X), the stator member (21) comprising a fin (25) arranged circumferentially between the first and second stator blades (20, 20'), characterised in that, The annular wall (23) comprises a recess (28) of predetermined shape formed in the thickness of the annular wall, which opens onto the radially outer surface (23a) of the annular wall and is spaced apart from the upstream and downstream edges (24a, 25b) of the annular wall (23), the fin (25) comprising a root (26) and a fin body (27), the root being complementary in shape to the recess (28), the root being configured to be removably arranged in the recess (28), the fin body extending radially from the root (26) and being elongated in a direction substantially parallel to the longitudinal axis (X).

2. Stator member (21) according to the preceding claim, characterized in that The root (26) extends along an axis of revolution (A) and comprises a base (29) and a separate platform (30) connected by a stem (31) along the axis of revolution (A).

3. Stator member (21) according to the preceding claim, characterized in that The base (29) has two lugs (32a, 32b) which are identical in shape and are arranged on either side of the stem (31) in a plane perpendicular to the axis of revolution (A).

4. Stator member (21) according to any one of the preceding claims, characterized in that The fin (25) is made of material or formed from an assembled unitary piece.

5. Stator member (21) according to any of claims 2 to 4, characterized in that The recess (28) comprises three portions (42, 43, 45) configured to receive one of the elements forming the root (26) respectively.

6. Stator member (21) according to any of claims 2 to 5, characterized in that The recess (28) comprises a first portion (42) which is shaped to correspond to the shape of the platform (30), the platform (30) having an outer surface (30b) which has surface continuity with the radially outer surface (23a) of the annular wall (23).

7. Stator member (21) according to any one of the preceding claims, characterized in that The recess (28) comprises a second portion (43) and a third portion (45), each having a shape similar to that of the base (29), at least one dimension of the third portion (45) being greater than the dimensions of the second portion (43) and the base (29).

8. Stator member (21) according to any one of the preceding claims, characterized in that The fin (25) comprises blocking means (37) for blocking the root (26) in the recess (28).

9. Stator member (21) according to any one of the preceding claims, characterized in that The blocking means (37) comprise a locking element (38) arranged in a cavity (40) of the base (29), the locking element (38) being configured to occupy a locked position and an unlocked position, and a retaining element (39) for retaining the locking element (38) in its locked position, the retaining element being arranged in the recess (28).

10. Stator member (21) according to the preceding claim, characterized in that The blocking means (37) comprise a return element (41) mounted in the cavity (40) and configured to continuously push the locking element towards the locked position.

11. A stator member according to claim 9 or 10, characterised in that The recess (28) comprises at least one groove (50, 51) configured to receive at least one portion of the locking element (38) in the unlocked position.

12. A turbomachine (1), in particular for an aircraft, comprising at least one stator member (21) according to any one of the preceding claims.

13. Method (100) of mounting at least one fin in a stator member according to any one of claims 1 to 11, comprising the steps of: - positioning (101) a root (26) of the fin (25) in the recess (26) in a complementary shape such that an elongation direction of the fin body (27) is transverse to the longitudinal axis (X), and - rotating (102) the root (26) of the fin in the recess (28) around the axis of revolution (A) to orient the elongation direction of the fin body (27) substantially parallel to the longitudinal axis (X).

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