Turbomachine nozzle, turbine and turbomachine

Abstract

The invention relates to a turbomachine nozzle forming a ring centered on a longitudinal axis (X), and comprising a first nozzle sector (15a) and a second nozzle sector (15b) arranged circumferentially opposite one another. Each sector comprises a platform (13, 14) from which there extends, on one side, an airfoil (12) and, on the other side opposite the airfoil, at least one arm (17, 34) which projects from the platform. The first sector comprises a circumferential end face (24a, 31a) mounted circumferentially opposite a circumferential end face (24b, 31b) of the second circumferentially adjacent sector. Each circumferential end face of the first sector and of the second sector comprises grooves (25a, 25b, 25c, 32a, 32b) which have a predetermined shape and which communicate with one another. The nozzle comprises a single one-piece solid sealing tongue (26) having a cross section with a shape corresponding to the shape of the grooves. The sealing tongue comprises at least two tongue portions (26a, 26b, 26c), including a first tongue portion (26a) which extends into the platform of the first sector and of the second sector, and a second tongue portion (26b) which extends into the arm of the first sector and of the second sector. The sealing tongue has a thickness (e) substantially equal to the height H of the corresponding grooves.

Description

Description TITLE: TURBOMACHINE ASSEMBLY INCLUDING A ONE-PIECE SEALING DEVICE Technical field of the invention

[0001] The present invention relates to the field of turbomachinery, and in particular to aircraft turbomachinery. It specifically relates to a turbomachine assembly equipped with sealing means between sectors of a turbomachine distributor. Technological background

[0002] Prior art includes documents US2024 / 309771 A1, US2024 / 191631A1 and FR3115811A1.

[0003] A turbomachine turbine, particularly an aircraft gas turbine, comprises one or more stages, each consisting of a stator and a rotor. The stages are arranged alternately and successively along the longitudinal axis. The stator is formed by a fixed wheel with fixed blades, known as a distributor, and the rotor is formed by a rotating wheel with rotating blades.

[0004] The rotating wheel comprises, in particular, a disc on which are mounted several rotating blades that extend radially and are distributed circumferentially and regularly around the outer periphery of the disc. The rotating blades are surrounded by a ring, cylindrical or frustoconical in shape, mounted on a stator housing of the turbomachine.

[0005] The fixed wheel comprises several blades distributed circumferentially and regularly around the longitudinal axis of the turbomachine. The blades extend radially between an inner platform and an outer platform which are coaxial and which radially delimit an airflow channel within the turbine.

[0006] The fixed wheel and the moving wheel can each be respectively formed of several blade sectors and ring or internal and external platforms.

[0007] It is known to install a sealing device between sectors to reduce airflow leaks caused by pressure differences between the flow stream on the inner and outer sides. The sealing device typically comprises several separate sealing tabs installed in grooves formed in the circumferential end faces of the intersectors.

[0008] In the case of a distributor 01 as shown in Figure 1, the external platform 02 comprises a base 03 and two lugs 04 extending radially outwards from the base 03. The external platform 02 includes, at an inter-sector lateral face 05, a first groove 06 extending in a direction inclined with respect to a longitudinal axis of the turbomachine. The external platform 02 further comprises a second groove 07 and a third groove 08 extending radially from the first groove 06. The second groove 07 and the third groove 08 are formed at the lugs 04 and each communicates with the first groove 06. Three separate sealing tabs 09, 010, 011 of different dimensions are installed in the corresponding grooves.

[0009] However, installing the three tabs 09, 010, and 011 is tedious and time-consuming. Each tab must be lubricated to prevent disengagement during assembly, and this lubrication must be repeated for each sector and each sealing tab. Although the tabs differ in size, they are visually similar, and an operator could easily mistake them during installation. This could lead to quality and sealing problems later on.

[0010] Furthermore, several groove and tongue combinations were declared non-compliant because they generate leakage sections at the tongue intersections, resulting in thermal impacts and a degradation of the turbomachine turbine's efficiency. Indeed, gaps can appear between the walls of a groove and the corresponding tongue, and also between the tongues themselves at their intersections. These impacts can be significant and may necessitate the removal of the entire distributor sector.

[0011] Therefore, there is a need to address all or part of the aforementioned disadvantages. Summary of the invention

[0012] The objective of the present invention is to provide a simple, effective and economical solution to limit a temperature rise in a ring sector while avoiding in particular leakage sections.

[0013] We achieve this objective in accordance with the invention by means of a crown centered on a longitudinal axis, comprising a first sector and a second distributor sector arranged circumferentially opposite each other, each sector having a platform from which extends, on one side, a blade and on the other side opposite the blade at least one branch which projects from the platform, the first sector comprising a circumferential end face mounted circumferentially opposite a circumferential end face of the circumferentially adjacent second sector, each circumferential end face of the first and second sectors comprising grooves,the distributor comprising a one-piece sealing tab having at least two tab portions, a first tab portion extending into the platform of the first and second sectors and a second tab portion extending into the branch of the first and second sectors.

[0014] Thus, this solution achieves the aforementioned objective. In particular, such a configuration significantly reduces assembly steps, resulting in both manufacturing time savings and cost reductions. The manufacturing time savings can be estimated at at least thirty minutes for each stage of a turbomachine assembly, such as a turbine wheel. Furthermore, this tab configuration prevents leakage at the various groove and tab intersections. Airflow leaks from the flow channel to the outside are limited. This also reduces local thermal impacts and the degradation of the turbomachine's performance, especially that of the turbine. Moreover, this system prevents the tabs mounted in the grooves from disengaging.

[0015] The dispenser also includes one or more of the following features, taken alone or in combination: - a first groove is formed at the level of the platform and extends substantially along the longitudinal axis and a second groove, opening into the first groove, is formed in the branch, the sealing tongue having a first portion housed in the first groove and a second portion housed in the second groove. - the branch which extends radially in projection is inclined relative to the platform. - the platform comprises an upstream branch and a downstream branch which extend in projection from the platform, the upstream branch and the downstream branch each being extended by an axial end rim for mounting to a turbomachine housing, the sealing tongue comprising three portions, the first portion, a second portion located upstream which extends into the upstream branch of the first and second sectors and a third portion located downstream which extends into the downstream branch of the first and second sectors, the first portion connecting the second portion located upstream and the third portion located downstream. - the platform is an external platform and grooves are formed in the upstream branch and in the downstream branch, the grooves extending in an inclined direction at an angle to the longitudinal axis X. - the platform is an internal platform comprising a branch extending radially inwards from the internal platform, grooves being formed in the internal platform and in the branch, and the sealing tongue being housed in these grooves. - the sealing tab is formed from several portions of tabs fixed together by welding. - each portion of the tongue is formed from several parts which are welded together via spot welds. - the sealing tab has a general TT shape. - the sealing tab has a general T-shape. - - the grooves together form a housing. - - where each branch and the base are formed from a single piece. - - the grooves on each end face have a predetermined shape and communicate with each other and the one-piece sealing tongue has a cross-section having the shape corresponding to the shape of the grooves and is housed at least partly in the grooves of the end face of the first sector and at least partly in the grooves of the end face of the second adjacent sector. - the sealing tab is made of a metallic material or an alloy of metallic material or even a composite material.

[0016] The invention also relates to a turbine comprising at least one distributor as above surrounded by a housing comprising at least one upstream hook and one downstream hook, the distributor being mounted on the upstream hook by an upstream arm and on the downstream hook by a downstream arm, the upstream and downstream arms each extending outward from the distributor platform, the platform being an external platform of the distributor.

[0017] The invention also relates to a turbomachine equipped with such a turbomachine distributor or a turbine as mentioned above. Brief description of the figures

[0018] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the detailed explanatory description that follows, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which: - Figure 1 is a cross-sectional view passing through the axis of rotation of a distributor sector according to the prior art; - Figure 2 is an axial cross-sectional view of an example of a turbomachine turbine according to the invention; - Figure 3 illustrates in perspective an example of two sectors of a turbomachine component which are arranged adjacently circumferentially with respect to a longitudinal axis of the turbomachine; - Figure 4 illustrates in perspective an example of a sector of a turbomachine component comprising a sealing device at the level of an inter-sector lateral face according to the invention; - Figure 5 shows, in axial section, an example of a turbine wheel platform according to the invention; - Figure 6 is a detailed view of an example of a sealing device cooperating with grooves on an inter-sector lateral face of a sector of a turbomachine component according to the invention; and - Figure 7 is a front view of an example of a sealing device according to the invention. Detailed description of the invention

[0019] Figure 1 has already been described above.

[0020] Figure 2 schematically represents, in a partial axial section, a turbomachine 1 with longitudinal axis X, which is specifically designed to be mounted on an aircraft (not shown). The aircraft advantageously comprises a fuselage and at least two wings extending on either side of the fuselage relative to the fuselage axis. At least one turbomachine can be mounted on one wing.

[0021] The turbomachine 1 can be a turbojet (twin-spool and twin-flow) equipped with a fan or a turboprop equipped with at least one unfaired propeller. The invention generally applies to a turbomachine 1 that includes at least one fan or one propeller, whether faired or unfaired. Of course, the invention is not limited to this type of turbomachine.

[0022] The turbomachine 1 generally comprises, from upstream to downstream, a compressor assembly (not shown), a combustion chamber (not shown) and a turbine assembly 2.

[0023] In the present invention, and more generally, the terms "upstream," "downstream," "axial," and "axially" are defined with respect to the gas flow within the turbomachine and with respect to the longitudinal axis X of the turbomachine. Similarly, the terms "radial," "radially," "internal," and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X.

[0024] The compressor assembly and the turbine assembly include rotors which are connected by a drive shaft 3 which rotates around the longitudinal axis X. The rotors are movable in rotation relative to the stators which comprise the compressor and turbine assembly.

[0025] The turbine assembly (like the compressor assembly) may include a low-pressure turbine and a high-pressure turbine. In this case, the high-pressure turbine is placed immediately downstream of the combustion chamber, and the low-pressure turbine is placed downstream of the high-pressure turbine.

[0026] A primary flow F passes through the compressor assembly, the combustion chamber, and the turbine assembly. The primary flow F generally circulates in a primary channel 4.

[0027] Referring to Figure 2, the turbine assembly 2 advantageously comprises one or more stages 5. Each stage 5 includes a runner 6 with moving blades 7 and a stationary runner 8 with fixed blades 9, which alternate about the longitudinal axis X. The stationary runners 8 are known as distributors. The moving blades 7 differ from the stationary blades 9 in that they rotate about the longitudinal axis X, while the stationary blades 8 are fixed in rotation.

[0028] Each movable wheel 6 or rotor advantageously, but not exclusively, comprises a disc 10, centered on the longitudinal axis X, and movable blades 7 which extend radially from an external periphery 11 of the disc 10 and regularly around the longitudinal axis X. The discs 10 of each stage are coupled to each other but also to the drive shaft 3.

[0029] Each of the fixed blades 9 advantageously comprises a blade 12 extending substantially radially (radially or inclined at an angle of approximately 5° to 10°) between a first platform 13 (called the outer platform) and a second platform 14 (called the inner platform). The first platform 13 and the second platform 14 are each advantageously, but not exclusively, annular, concentric, and centered on the longitudinal axis X.

[0030] According to one embodiment, the distributor or fixed wheel 8 of the turbomachine forms a ring centered on the longitudinal axis X. Each distributor 8 comprises several sectors 15 which are arranged adjacently to each other and around the longitudinal axis X.

[0031] Figure 3 shows an example of a turbomachine assembly and preferably a turbomachine distributor. The distributor 8 advantageously comprises at least one turbomachine sector 15, and preferably one turbomachine distributor sector. In this figure, two sectors 15a, 15b are shown, arranged adjacently circumferentially around the longitudinal axis X. Each sector 15, 15a, 15b comprises, for example, several blades 12, each extending between the first platform 13 and the second platform 14.

[0032] Figure 4 shows in more detail a turbomachine sector 15. Each first platform 13 includes at least one leg or branch 17 that projects from the platform. In particular, the branch 17 extends substantially radially outwards. Advantageously, the first platform 13 includes a base 16, and the branch 17 extends from this base 16. Each base 16 is intended, for example, to delimit a portion of a flow channel, and preferably the primary channel 4 in which the primary flow flows. Each base 16 has a length determined between an upstream edge 19a and a downstream edge 19b, which are opposite along the longitudinal axis X. The upstream edge 19a and the downstream edge 19b connect a radially internal face 20 (oriented towards the longitudinal axis X) and a radially external face 21 (oriented outwards).

[0033] Advantageously, but not exclusively, the first platform 13 comprises two arms, hereinafter referred to as upstream arm 17a and downstream arm 17b. Each arm 17 allows the blade to be fixed to a housing 22 (see Figure 2) of the turbomachine. The upstream and downstream arms 17a and 17b each include, for example, at their free ends, an end flange 23 to which each arm 17 is fixed, via bolt-type fasteners (not shown), to the housing 22. The housing includes, for example, hooks 29 for securing at least one arm 17.

[0034] Advantageously, but not exclusively, each end flange 23 extends substantially along the longitudinal axis (for example, by + / - 10°) and prolongs the upstream and downstream branches 17a, 17b. The upstream and downstream branches 17a, 17b, together with the end flanges 23, form, for example, a mounting bracket for each sector of the turbomachine distributor, shown here in Figure 4 for the turbine distributor sector. Each end flange 23 is advantageously fixed to a hook 29.

[0035] The branch(es) 17a, 17b and the base 16 are advantageously formed from a single piece (either molded from another material or monolithic). In this case, the upstream branch 17a, the downstream branch 17b, and the base 16 have a general TT (pi) shape. This shape is, of course, only an option. Optionally, at least one branch 17 is inclined relative to the platform 13 or relative to the base 16. Preferably, the upstream branch 17a and the downstream branch 17b each extend in a direction inclined at an angle to the longitudinal axis X. The angle is, for example, between 30° and 50°. The upstream branch 17a and the downstream branch 17b may have different lengths or the same length. In this example, the length of the upstream branch 17a is less than that of the downstream branch 17b.

[0036] Advantageously, each first platform 13 of a sector includes an inter-sector lateral face or a circumferential end face 24. Preferably, each sector 15 is delimited by a first circumferential end face 24a and a second circumferential end face 24b which are opposite along a circumferential direction around the longitudinal axis X. Each circumferential end face 24a, 24b of a sector is opposite, for example, another circumferentially adjacent lateral end face of a sector. The end faces 24a, 24b are intended to be in contact with each other. Optionally, each end face 24a, 24b is defined in a plane parallel to the radial axis.

[0037] Each sector 15 further includes at least one sealing device arranged circumferentially between circumferentially adjacent sectors 15 and which is configured to prevent leakage of the primary flow outside the flow channel, here primary channel, into the turbine.

[0038] In Figure 5, each end face 24, particularly of the first platform 13, includes grooves 25 formed in it. The grooves 25 shown here are hollow. Advantageously, the grooves 25 have a predetermined shape and communicate with each other. The grooves 25 together advantageously form a housing. Each groove 25 advantageously, but not exclusively, opens onto the end face 24.

[0039] Advantageously, but not exclusively, a first groove 25a is formed at the level of the first platform 23, and preferably in the base 16. The first groove 25a extends, advantageously, but not exclusively, substantially along the longitudinal axis X. More precisely, the first groove 25a extends in a direction inclined at an angle to the longitudinal axis X, for example, an angle between 30° and 60°. The first groove 25a is parallel to the general direction of the base 16. The first groove 25a optionally extends for at least approximately two-thirds of the length of the base 16 along the longitudinal axis X.

[0040] A second groove 25b is formed at the upstream branch 17a. The second groove 25b opens into the first groove 25a. The second groove 25b advantageously, but not exclusively, extends in a direction inclined at an angle to the longitudinal axis X, for example, at an angle between 50° and 100°. The second groove 25b follows the direction of the first branch 17a. The second groove 25b extends, for example, substantially along at least two-thirds of the length of the first branch 17a and preferably along the entire length of the first branch 17a.

[0041] A third groove 25c is formed at the level of the second branch 17b. Advantageously, the third groove 25c also opens into the first groove 25a. As with the second groove, the third groove 25c follows the direction of the downstream branch 17b. In this example, the third groove 25c is longer than the second groove 25b.

[0042] With reference to Figure 6, each sector 15 comprises a single tab 26 or sealing plate to ensure its seal with another circumferentially adjacent sector. The sealing tab 26 is advantageously one-piece so as to ensure continuous sealing in the grooves 25 and at the intersections of the grooves 25. In this description, the term "one-piece" means a part that is formed from a single piece (either molded from a single material or monolithic) or that is formed by assembling several parts. Advantageously, in the case of an assembly of several parts, the parts of the sealing tab are not detachable.

[0043] The sealing tab 26 is advantageously housed, at least partially, in the grooves 25 of an end face 24 defining the housing. More precisely, the sealing tab 26 is housed or installed, at least partially, in the first groove 25a, the second groove 25b, and the third groove 25c of an end face. Advantageously, the sealing tab 26 has a shape corresponding to that of all the grooves 25.

[0044] More specifically, the sealing tab 26 comprises several tab portions that are connected to each other. Advantageously, the sealing tab 26 comprises at least two portions.

[0045] In the installation configuration, a first portion 26a extends into the platform of a pair of circumferentially adjacent sectors (and in particular into the first groove 25a), and a second portion 26b extends into the upstream branch 17a of the pair of circumferentially adjacent sectors (and in particular into the second groove 25b). Advantageously, the first portion 26a has a shape that allows it to be housed in the first groove 25a, and the second portion 26b has a shape that allows it to be housed in the second groove 25b. In this embodiment, the sealing tab 26 includes a third portion 26c that extends into the downstream branch 17b of the pair of circumferentially adjacent sectors (and in particular into the third groove 25c). The third portion 26c has a shape that allows it to be housed, for example, in the first groove 25a.

[0046] In other words, the sealing tab 26 is a single sealing tab 26 that fits the shape of the three grooves 25a, 25b, 25b. In this way, the assembly of the tab is simplified and faster.

[0047] Advantageously, the sealing tab 26 has a general TT (pi) shape. The second portion 26b and the third portion 26c are, for example, inclined at an angle with respect to the first portion 26a.

[0048] Advantageously, but not exclusively, the sealing tab 26 also has dimensions similar to those of the grooves 25. In this way, when grooves 25 have different dimensions, it is less easy for an operator to make a mistake.

[0049] Each portion of the sealing tongue 26 has a length substantially equal to that of the corresponding groove (plus or minus 10%).

[0050] The sealing strip 26 may also have a thickness e substantially equal to the height H of the corresponding grooves 25 (plus or minus 10%). The height of each groove 25 is advantageously, but not exclusively, measured between two opposite walls 27a, 27b. The two walls 27a, 27b are connected, for example, by a base 27c which is defined (or includes a point) substantially in a plane parallel to the plane of the end face 24.

[0051] According to an optional feature, the thickness e of the sealing strip 26 (solid) is constant (at each portion of the strip 26a, 26b, 26c). This simplifies the manufacturing of the sealing strip 26. The thickness e of the sealing strip 26 is, for example, between 0.1 and 1 mm.

[0052] Preferably, each sealing tab 26 rests against one of the walls 27a, 27b of the groove 25.

[0053] According to an alternative embodiment, each sealing tab 26 is located at an equal distance from the walls 27a, 27b of the grooves 25, creating an identical gap on both sides of the tab 26. This allows the circulation of fresh cooling air around the sealing tab 26. For efficient cooling, the gap can be between 0.1 mm and 0.5 mm.

[0054] The sealing tongue 26 advantageously has a width that is greater than the depth (in the circumferential direction) of the corresponding grooves. The depth of each groove 25 is measured between the bottom 27c of the groove and the plane in which the inter-sector end face 24 is defined. In this way, one part of the tongue 26 fits into the grooves of one end face 24 of a sector, and the other part of the sealing tongue 26 fits into the grooves of another circumferentially adjacent end face 24.

[0055] Advantageously, but not exclusively, the sealing tab 26 is made of a metallic material, a metallic alloy, or a composite material. These materials must at least have good mechanical resistance at high temperatures.

[0056] In one embodiment, the sealing tab 26 is formed from a single piece (molded from a single piece of material or monolithic). The first portion 26a and the second portion 26b are formed from the first portion 26a. In this case, the sealing tab 26 can be manufactured using an additive manufacturing process. Additive manufacturing allows for the rapid and easy production of parts of any shape.

[0057] According to another embodiment, the sealing tab portions are fixed together to form the single sealing tab 26. Advantageously, the sealing tab 26 comprises different portions which are welded by an arc welding process.

[0058] According to yet another embodiment, the sealing tab 26 is obtained by casting.

[0059] The solid sealing tab 26 can also be obtained by folding a material.

[0060] Figure 7 shows an example of a one-piece sealing tab 26 obtained by welding several parts together to form the tab sections. The multiple points 30 represent weld points. In this figure 7, each portion of the sealing tab 26 is formed by assembling and welding several parts. Between two weld points 30, for example, extends a portion which, together with other parts, will form a tab section.

[0061] In Figure 4, the second platform 14 also includes an end face 31. Advantageously, the second platform 14 is circumferentially delimited by a first sealing face 31a and a second sealing face 31b. As shown, each sealing face 31 includes grooves 32 opening onto it. The grooves 32 communicate with each other and have a predetermined shape. Preferably, two grooves 32a and 32b are provided and, in this example, have a general T-shape. The first groove 32a extends along the longitudinal axis, while the second groove 32b extends along the radial axis. Of course, other shapes and arrangements of the grooves 32 are possible.

[0062] Advantageously, but not exclusively, a single sealing strip (not shown in Figure 4) with a cross-section having the shape of the two grooves joined together is installed in the first groove 32a and the second groove 32b. In this example, the sealing strip 26 has a general T-shape. Advantageously, the sealing strip has similar dimensions (height and length to within ±10%) to those of the grooves 32, as shown for the strip 26.

[0063] In particular, the second platform 14 comprises a base 33 extending along the longitudinal axis X. The first groove 32a is formed at the base 33. The second platform 14 may further comprise a branch 34 projecting from the second platform 14. The branch 34 extends substantially radially outwards from the base 33. The branch 34 may be inclined relative to the second platform 14. The branch 34 can, for example, accommodate a sealing system (not shown). Advantageously, the second groove 32b is formed at the branch 34. In this way, the sealing tab is housed in the grooves formed in the base 33 and in the branch 34 so as to achieve efficient sealing.

[0064] In the installation configuration, a first portion of the tongue extends into the second platform 14 of a pair of circumferentially adjacent sectors, such as those shown in Figure 3 (and in particular into the first groove 32a), and a second portion of the tongue extends into the branch 34 of the pair of circumferentially adjacent sectors (and in particular into the second groove 32b). Advantageously, the first portion has a shape that allows it to be housed in the first groove 32a, and the second portion of the tongue allows it to be housed in the second groove 32b.

[0065] The second platform 14 may include an abradable material 35 with which a seal and / or a thermal barrier carried by the rotor cooperates. The seal may be of the labyrinth type.

Claims

Demands [1] A turbomachinery distributor forming a ring centered on a longitudinal axis (X), comprising a first sector (15, 15a) and a second sector (15, 15b) of the distributor arranged circumferentially opposite each other, each sector (15, 15a, 15b) having a platform (13, 14) from which extends, on one side, a blade (12) and on the other side opposite the blade (12), at least one arm (17, 34) projecting from the platform (13, 14), the first sector (15, 15a) comprising a circumferential end face (24, 31) mounted circumferentially opposite a circumferential end face of the second sector (15, 15b) circumferentially adjacent, each circumferential end face (24, 31) of the first and the second sector (15, 15a, 15b) comprising grooves (25, 25a, 25b, 25c, 32, 32a, 32b) which have a predetermined shape and which communicate with each other,characterized in that the distributor comprises a single, solid, one-piece sealing tab (26) having a cross-section corresponding to the shape of the grooves, the sealing tab comprising at least two tab portions (26a, 26b, 26c), of which a first tab portion (26a) extends into the platform (13, 14) of the first and second sectors and a second tab portion (26b) extends into the branch (17, 34) of the first and second sectors (15, 15a, 15b), the sealing tab having a thickness (e) substantially equal to the height H of the corresponding grooves. [2] Turbomachine distributor according to claim 1, characterized in that a first groove (25a) is formed at the level of the platform (13, 14) and extends substantially along the longitudinal axis (X) and a second groove (25b, 25c, 32b), opening into the first groove (25a, 32a), is formed in the branch (17, 17a, 17b, 34), the sealing tongue (26) having a first portion (26a) housed in the first groove (25a, 32a) and a second portion (26c) housed in the second groove (25b, 25c, 32b). [3] Turbomachine distributor according to any one of claims 1 and 2, characterized in that the platform (13) comprises an upstream branch (17a) and a downstream branch (17b) which project out from the platform (13), the upstream branch (17a) and the downstream branch (17b) each being extended by an axial end flange (23) for mounting to a turbomachine housing (22), the sealing tab (26) comprising three portions, of which the first portion (26a), a second portion (26b) located upstream which extends into the upstream branch (17a) of the first and second sectors and a third portion (26c) located downstream which extends into the downstream branch (17b) of the first and second sectors, the first portion (26a) connecting the second portion (26b) located upstream and the third portion (26c) located downstream. [4] Turbomachine distributor according to any one of claims 2 to 3, characterized in that the platform (13) is an external platform and grooves (25a, 25b, 25c) are formed in the upstream branch (17a) and in the downstream branch (17b), the grooves (25a, 25b, 25c) extending in an inclined direction at an angle with respect to the longitudinal axis (X). [5] Turbomachine distributor according to any one of claims 2 to 4, characterized in that the platform (14) is an internal platform comprising a branch (34) extending radially inwards from the internal platform (14), grooves (32a, 32b) being formed in the internal platform (14) and in the branch (34) and the sealing tab (26) being housed in these grooves (32a, 32b). [6] Turbomachine distributor according to any one of claims 1 to 5, characterized in that the sealing tab (26) is formed of several portions of tabs (26a, 26b, 26c) fixed together by welding. [7] Turbomachine distributor according to claim 6, characterized in that each portion of tongue (26a, 26b, 26c) is formed of several parts which are welded together via spot welds (30). [8] Turbomachine distributor according to any one of the preceding claims, characterized in that the sealing tab (26) has a general TT shape. [9] Turbomachine distributor according to any one of the preceding claims, characterized in that the sealing tab is made of a metallic material or an alloy of metallic material or even of a composite material. [10] Turbomachine distributor according to any one of the preceding claims characterized in that the thickness of the tongue is constant. [11] Turbine comprising at least one distributor, according to any one of claims 1 to 10, surrounded by a housing (22) comprising at least one upstream hook and one downstream hook (29), the distributor being mounted on the upstream hook by an upstream arm and on the downstream hook by a downstream arm (17, 17a, 17b, 34), the upstream and downstream arms each extending in projection from the platform (14) of the distributor, the platform (14) being an external platform of the distributor. [12] Turbomachine comprising at least one distributor according to any one of claims 1 to 10 or a turbine according to claim 9.

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