EP3857028B1 - Improved turbomachine stator - Google Patents

Improved turbomachine stator Download PDF

Info

Publication number
EP3857028B1
EP3857028B1 EP19787014.0A EP19787014A EP3857028B1 EP 3857028 B1 EP3857028 B1 EP 3857028B1 EP 19787014 A EP19787014 A EP 19787014A EP 3857028 B1 EP3857028 B1 EP 3857028B1
Authority
EP
European Patent Office
Prior art keywords
platform
nozzle
distributor
main portion
turbomachine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19787014.0A
Other languages
German (de)
French (fr)
Other versions
EP3857028A1 (en
Inventor
Hugo Louis Rousseaux
Pamela Jessica BENEVENT
Léna JEFFROY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3857028A1 publication Critical patent/EP3857028A1/en
Application granted granted Critical
Publication of EP3857028B1 publication Critical patent/EP3857028B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to the field of aeronautical turbomachines, and more specifically to a distributor for a turbomachine turbine, and a turbomachine comprising such a distributor.
  • Turbomachinery high-pressure or low-pressure distributors include in particular fixed blades held at each of their radial ends by an inner platform and an outer platform, the latter defining a stream for the circulation of gases ejected by the combustion chamber. These blades make it possible to direct the flow of gases leaving the combustion chamber onto the rotor blades of the turbine. These blades are hollow, and comprise at least one cavity, one end of which opens outside the vein. Since these blades are exposed to the hot combustion gases, it is necessary to cool them to reduce the thermal stresses.
  • One solution consists in using air coming from another element of the turbomachine, for example the compressor.
  • relatively cool air is taken upstream of the combustion chamber at the outlet of a stage of the compressor.
  • This air is injected into the cavity(ies) of the blades by one and the other of the ends thereof, to cool them from the inside.
  • the air then escapes into the vein through holes made in the blades and communicating with the cavity or cavities of the blade and with the vein, the cooling air creating a protective film of cooler air s flowing along the blade.
  • Another example is disclosed in the document US 2016153299 .
  • the inner and outer blade/platform assembly is fixed to the casing of the turbine.
  • Sealing slats and joint covers are fixed at the level of the platforms by fixing means (pins/rivets), in order to ensure the seal between the distributor and the external casing.
  • This presentation relates to a turbine distributor for a turbomachine extending radially around an axis, the distributor comprising a plurality of sectors each comprising at least one blade which extends radially between an inner platform and an outer platform, the distributor comprising at least two sealing blades each comprising a main portion configured to provide sealing between the distributor and an element of the turbomachine adjacent to the distributor, and a first portion folded relative to the main portion, the first folded portion being contact with an external face of at least one platform, each slat being held to the at least one platform by a clamping means configured to clamp the first folded portion between the external face of the platform and the clamping means.
  • the term “radial” and its derivatives designate a radial direction of the turbine, that is to say a direction perpendicular to the axis of the turbine.
  • the terms “upstream” and “downstream” are considered along the axis of the turbine, and according to the direction of gas flow in the turbine, between the two platforms, that is to say in the vein of gas circulation.
  • the blades are arranged between two platforms: a radially outer platform, and a radially inner platform, the inner and outer platforms being annular or in the form of a ring sector and coaxial.
  • the “external face” of the platforms refers to the face of the platforms opposite the vein gas flow, the latter being delimited by the internal face of the platforms. In other words, the gas flow path is delimited by the inner face of the outer platform, and the inner face of the inner platform.
  • the sealing strips may have the form of a metal plate, for example made of an alloy based on nickel and/or cobalt, and having a thickness of less than 1 mm.
  • the plate forming a sealing strip is bent, so as to form a first bent portion, and a main portion having a larger surface than the bent portion.
  • the main portion of the slats is the portion of the slat having the largest surface, and extends on the one hand in a direction substantially parallel to the radial direction, or slightly inclined with respect to the radial direction, and on the other hand in a circumferential direction, following the shape of the distributor, so that the main portion has the shape of an arc of a circle.
  • the main portion of the slats is in contact with an element of at least one sector of the turbine engine, for example a shoulder of the sector disposed at an upstream or downstream end of the platform, and with an element of the turbine engine adjacent to the distributor.
  • This element of the turbomachine may for example be part of an adjacent casing, or a flange of the combustion chamber.
  • the folded portion extends in the axial direction, that is to say from upstream to downstream, and is in contact with the external face of the platform.
  • the folded portion is held and clamped against the outer face of the platform by means of the clamping means.
  • the latter is configured to hold and clamp the bent portion of each lamella over the entire circumference of the distributor, by exerting pressure on the lamellae in the radial direction, such that the bent portions are sandwiched between the clamping means and the outer faces of the platforms.
  • the clamping means exerts a force on the slats directed radially towards the axis of the turbine when the slats are arranged on the outer platform, and directed radially towards the direction opposite to the axis of the turbine when the slats are arranged on the interior platform.
  • the fixing of the sealing strips to the distributor is ensured by the first bent parts and the fixing means, and the sealing between the distributor and the elements of the turbomachine adjacent to the distributor is ensured by the main portion.
  • the use of studs and/or rivets which usually make it possible to fix the slats on the distributor, for example on the shoulder of the sector arranged at an upstream and/or downstream end of the platform, is therefore no longer necessary.
  • the risk of loss of the strips due to the shearing of the rivets is therefore reduced. Consequently, the risk of damage to the blades, due to the blocking of the cooling cavities by the lamellae, is also reduced.
  • the distributor comprises two lamellae each forming a half-ring, the clamping means being arranged around the distributor so as to clamp the two lamellae against the external faces of the platforms of the distributor.
  • each slat has the shape of an arc of a circle of 180°.
  • each of the two 180° blades is fixed to the external face of the adjacent platforms of the crown of the distributor, and are held and tightened against these external faces by the clamping means , the latter surrounding the distributor over its entire circumference and thus maintains the two slats simultaneously.
  • the circumferential ends of the two lamellae are joined together so as to form a sealing ring which extends around the dispenser.
  • the main portion and the first folded portion of each slat form between them an angle comprised between 90° and 150°.
  • this angle between the main portion and the first folded portion of each slat is the natural angle formed by these two portions of the slat, that is to say when there is no force tending to deform the slat, and therefore to modify this angle, is exerted on the lamella.
  • the plate forming the lamella is not folded so as to form a right angle between the portion main and the folded portion, but so as to form an obtuse angle between them.
  • the plane in which the main portion of the lamella extends is not parallel with respect to the radial direction, but slightly inclined with respect thereto.
  • This configuration makes it possible to improve the seal between the distributor and the element of the turbomachine adjacent to the distributor. Indeed, due to the inclination of the main portion, the element of the turbomachine adjacent to the distributor comes into contact with the radial end of the main portion. This contact tends to deform the strip so as to reduce the angle between the main portion and the bent portion. The main portion, tending to return to its initial position by elasticity, thus acts like a spring by exerting pressure on the element of the turbomachine adjacent to the distributor. In other words, the contact pressure between the main portion of the strip and the element of the turbomachine adjacent to the distributor is increased, thus improving the seal between this element and the distributor.
  • the slats each comprise a second bent portion extending from the first bent portion, substantially perpendicular thereto, and coming into contact with a radial wall which extends radially projecting from the at least a platform.
  • the slats are folded so as to present three portions: the main portion, the first folded portion in contact with the external face of the platform, and the second folded portion, the first folded portion being interposed between the main portion and the second portion folded, so that, in a cross section, the lamella has substantially the shape of a U.
  • the slat thus folded takes the form of a gutter in which the clamping means is housed, thus limiting its axial displacements, and limiting the risks that sufficient clamping of the slat against the platform is no longer ensured.
  • Sufficient tightening means tightening making it possible to prevent the lamella from becoming detached during normal operation of the turbine engine.
  • two circumferentially adjacent sipes around the dispenser are arranged such that a circumferential end of the main portion of one sipe is superimposed on a circumferential end of the main portion of a circumferentially adjacent sipe.
  • the circumferential end of the main portion of a lamella and the circumferential end of the main portion of the adjacent lamella overlap over a distance of between 1 and 10 mm.
  • each slat are provided so that the circumferential ends thereof overlap with each other, over their entire height.
  • height is understood their length in the radial direction.
  • the circumference of one of the two lamellae is substantially larger than the other, so as to overlap the ends of the latter.
  • This configuration makes it possible to avoid the presence of a clearance between the circumferential ends of each strip, and therefore to improve the seal between the distributor and an element of the turbomachine adjacent to the distributor.
  • the clamping means comprises at least one clamping surface, the clamping surface being in contact with the first bent portion.
  • the presence of at least one flat clamping surface makes it possible to obtain flat contact between the clamping means and the first bent portion, increasing the contact surface, and therefore the reliability of clamping the lamella on the platform.
  • the clamping means is a rod.
  • Ring means a ring, preferably metallic, having two free ends vis-à-vis but separate from each other. This device has the advantage of being simple and inexpensive.
  • the distributor comprises at least one blade fixed to the radial wall, and configured to exert pressure on a blade.
  • the blade is fixed to the radial wall, and is oriented so as to rest on a strip of the distributor, thus exerting pressure thereon. This makes it possible to exert pressure against the main portions of the slats, and thus accentuate the contact pressure between the main portions and the element of the turbomachine axially adjacent to the distributor, thus further improving the seal.
  • This presentation also relates to a turbine engine comprising a distributor according to any one of the preceding embodiments.
  • the figure 1 represents a sector 10 of a distributor for a high-pressure turbine of a turbomachine according to the prior art, the distributor comprising a crown of fixed hollow blades 13, arranged between two coaxial annular platforms: an outer platform 16 and an inner platform 18.
  • platforms are formed by ring sectors which extend around the axis X and which delimit a gas circulation vein 20 in which are located the blades 13 distributed regularly circumferentially and which extend radially between the platforms 16, 18
  • Each blade has a cavity 26 opening outside the passage 20 through the outer platform 16.
  • each blade has a cavity (not shown) opening outside the passage through the inner platform 18.
  • These cavities communicate with the stream 20 by rows of holes 30 extending axially and/or radially between the inner platform 18 and the outer platform 16 along the blades 13 to open into the stream 20.
  • a gas flowing from the The exterior of the stream 20 can thus enter the cavity 26, flow into the blade 13, then be evacuated into the stream 20 via the orifices 30, thus allowing the cooling of the blade 13.
  • a sleeve 36 is inserted into the cavity 26, so as to define an orifice 37 on the external face of the platform 16.
  • external is meant the face of the platform opposite to the vein 20.
  • the sleeve 36 further comprises a flange 38 resting on the outer face of the platform 16.
  • a jacket (not shown) is also inserted into the cavity on the side of the inner platform 18, so as to define an orifice on the outer face of the inner platform 18.
  • the distributor sector 10 also comprises sealing strips 12 fixed on the platforms 16, 18, and making it possible to ensure sealing between the distributor and an element of the turbomachine 1 axially adjacent to the distributor. More specifically, the sealing strips 12 are fixed on the shoulders 161, 162 of the platform 16, by means of pins and/or rivets 14.
  • the figure 2 illustrates a configuration that the invention seeks to prevent and according to which, after the detachment of a lamella 12 from its location of attachment to the high-pressure distributor due to the shearing stresses between the rivets 14 and the lamella 12, the latter is sucked in by the air entering the cavity 26, and obstructs the orifice 37, thus preventing the air, partially or totally, from entering the cavity 26.
  • the picture 3 represents a sector 10 of a high pressure turbine nozzle for a turbomachine according to one embodiment of the invention.
  • the elements identical to the elements of the figures 1 and 2 have the same reference signs and will not be described again.
  • a portion of a lamella 12 is illustrated in the picture 3 .
  • a distributor according to the present embodiment comprising a plurality of sectors 10 assembled together, may comprise two semi-annular strips 12 extending over 180°, so that the latter surround the crown of the distributor. when assembled together.
  • the sector 10 described below does not include rivets 14 to fix the slats 12 to the shoulders of the platform.
  • each slat 12 comprises a main portion 120, a first folded portion 121, and a second folded portion 122.
  • the slat 12 is first folded in two so as to obtain the main portion 120 and the first folded portion 121, and so that the main portion 120 and the first folded portion 121 have between them an angle substantially greater than 90°. More precisely, the main portion 120 and the first folded portion 121 have between them an angle of 90°+ ⁇ , where ⁇ is less than 60°, preferably less than 20°.
  • the slat 12 is folded again so as to obtain the second folded portion 122, the first folded portion 121 and the second folded portion 122 being substantially perpendicular to each other.
  • the lamella 12 thus formed thus has substantially the shape of a U, in section in a transverse section plane which extends axially and radially, so as to form a groove or a gutter around the crown of the distributor when the lamellae are fixed on the platforms of the distributor, thus making it possible, when a clamping element is housed in this groove, to thus limit the axial displacements of the latter.
  • the axial displacements of the element of clamping and slats are also limited by a radial wall 163 which extends radially projecting from the platform.
  • the main portion 120 makes it possible to ensure sealing between the distributor and the element of the turbomachine 1 axially adjacent to the distributor, for example a flange of the combustion chamber or a part of an axially adjacent casing, being in contact with a shoulder 161 of the platform 16 and the element of the turbomachine 1 adjacent to the distributor.
  • the lamella 12 is fixed to the distributor, and due to the inclination of its main portion 120, the element of the turbomachine 1 axially adjacent to the distributor comes into contact with the radial end of the main portion 120 during assembly or during operation of the turbomachine.
  • This contact generates a force on the radial end of the main portion 120, tending to reduce the angle between the main portion 120 and the folded portion 121.
  • the main portion 120 tending to return to its initial position by elasticity, thus acts like a spring by exerting pressure on the element of the turbomachine 1 axially adjacent to the distributor.
  • the value of the angle ⁇ is determined so that, when the distributor is assembled to the turbine engine, and during normal operation of the latter, a contact always exists between the main portion 120 of the lamella 12 and the element of the turbomachine 1 axially adjacent to the distributor.
  • the figure 6 represents a partial view from above, that is to say in the radial direction, of an upstream end of a platform 16.
  • Blades, or pins 170, used to exert pressure on joint covers in order to maintain these latter at the junctions between two circumferentially adjacent strips 12 can be used to exert pressure against the main portions 120 of the strips 12 via a contact portion 171, and thus increase the contact pressure between the portions main 120 and the element of the turbomachine 1, thus further improving the seal.
  • These pins are fixed on a radial wall 163 by means of a rivet 164. It is noted that the rivets 164 used to fix these pins 170 to the distributor, are not in contact with the slats 12, which makes it possible to limit the damage by shearing of the slats 12.
  • the first bent portion 121 is pressed against the outer face of the platform 16 by a clamping means 40, the latter being configured to exert pressure in the radial direction on the first bent portion 121, the latter thus being taken into sandwich between the clamping means 40 and the platform 16.
  • the clamping means 40 is a rod, making it possible to simultaneously clamp the two slats 12 by 180° against the external face of the platforms of the distributor, the rod coming lodge in the groove formed by the main portion 120, the first folded portion 121 and the second folded portion 122.
  • the ring is an open ring, preferably metallic, for example made of an alloy based on nickel and/or cobalt, having two circumferentially facing free ends, but separated from each other.
  • the rod has an initial diameter D 0 .
  • the rod then tends to regain its initial shape, until it comes into abutment against the first folded portion 121, thus reaching its final diameter D f , when it presses the slats 12 against the outer face of the outer platforms 16
  • the initial diameter D 0 of the rod must therefore be less than the final diameter D f .
  • This example shows the clamping of a slat 12 on the outer face of an outer platform 16.
  • the clamping means 40 can also be used to clamp a slat 12 on the outer face of an inner platform 18.
  • the rod is deformed by bringing the free ends thereof closer together, causing these ends to overlap, so that the diameter of the rod decreases.
  • the deformed position of the rod is then released.
  • the diameter of the rod then tends to increase again to regain its initial shape, until it comes into abutment against the first folded portion 121, thus reaching its final diameter D f , when it presses the slats 12 against the external face of the internal platforms 18.
  • the initial diameter D 0 of the rod In order for the force exerted by the clamping means 40 on the first folded portion 121 to be sufficient, that is to say that it provides clamping making it possible to prevent the slat from coming off , the initial diameter D 0 of the rod must therefore be greater than the final diameter D f .
  • the clamping means 40 is a rod
  • other clamping means are possible, such as circlips, clamps or rings comprising for example a first portion and a second portion, the first and second portions being fastened together around the distributor so as to clamp the slats against the external faces of the platforms of the distributor.
  • each strip 12 has a circumferential end 120a, said circumferential end 120a extending in the radial direction.
  • the dimensions of the slats 12 are configured such that the circumferential ends 120a of two circumferentially adjacent slats overlap, so as to form an overlapping portion 125.
  • This overlapping portion 125 makes it possible to seal the junction between two slats 12 circumferentially adjacent.
  • the dimensions of the slats 12 are configured such that the overlapping portion 125 extends over an angle between 1 and 10°.
  • the overlapping portion can also be formed by stamping a circumferential end of a lamella 12, thus creating a recess on one face of the main portion 120, at the circumferential end of this lamella 12, the circumferential end of the adjacent lamella then coming to stay in this disbursement (cf. figure 4 ).
  • the length along the circumference (in other words the length of the arc of a circle) of the first folded portion 121 and of the second folded portion 122 is substantially less than the length along the portion circumference main 120.
  • the circumferential ends of the first folded portion 121 and of the second folded portion 122 of two circumferentially adjacent strips 12 are separate from each other. This configuration facilitates the assembly of the slats 12 around the distributor, and in particular the joining of two adjacent slats 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

La présente invention concerne le domaine des turbomachines aéronautiques, et plus précisément un distributeur pour une turbine de turbomachine, et une turbomachine comportant un tel distributeur.The present invention relates to the field of aeronautical turbomachines, and more specifically to a distributor for a turbomachine turbine, and a turbomachine comprising such a distributor.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

Les distributeurs haute pression ou basse pression de turbomachines, tels que décrits dans le document FR 2 955 145 , comportent notamment des pales fixes maintenues à chacune de leurs extrémités radiales par une plateforme intérieure et une plateforme extérieure, ces dernières définissant une veine de circulation de gaz éjectés par la chambre de combustion. Ces pales permettent de diriger l'écoulement des gaz sortant de la chambre de combustion sur les pales de rotor de la turbine. Ces pales sont creuses, et comporte au moins une cavité dont une extrémité débouche à l'extérieur de la veine. Ces pales étant exposées aux gaz chauds de combustion, il est nécessaire de les refroidir pour atténuer les contraintes thermiques. Une solution consiste à utiliser de l'air provenant d'un autre élément de la turbomachine, par exemple le compresseur. Plus précisément, de l'air relativement frais est prélevé en amont de la chambre de combustion à la sortie d'un étage du compresseur. Cet air est injecté dans la ou les cavité(s) des pales par l'une et l'autre des extrémités de celles-ci, pour les refroidir de l'intérieur. L'air s'échappe ensuite dans la veine par des trous réalisés dans les pales et communiquant avec la ou les cavité(s) de la pale et avec la veine, l'air de refroidissement créant un film protecteur d'air plus frais s'écoulant le long la pale. Un autre exemple est divulgué dans le document US 2016153299 .Turbomachinery high-pressure or low-pressure distributors, as described in the document FR 2 955 145 , include in particular fixed blades held at each of their radial ends by an inner platform and an outer platform, the latter defining a stream for the circulation of gases ejected by the combustion chamber. These blades make it possible to direct the flow of gases leaving the combustion chamber onto the rotor blades of the turbine. These blades are hollow, and comprise at least one cavity, one end of which opens outside the vein. Since these blades are exposed to the hot combustion gases, it is necessary to cool them to reduce the thermal stresses. One solution consists in using air coming from another element of the turbomachine, for example the compressor. More specifically, relatively cool air is taken upstream of the combustion chamber at the outlet of a stage of the compressor. This air is injected into the cavity(ies) of the blades by one and the other of the ends thereof, to cool them from the inside. The air then escapes into the vein through holes made in the blades and communicating with the cavity or cavities of the blade and with the vein, the cooling air creating a protective film of cooler air s flowing along the blade. Another example is disclosed in the document US 2016153299 .

Par ailleurs, l'ensemble pales/plateformes intérieure et extérieure est fixé au carter de la turbine. Des lamelles d'étanchéité et des couvre-joints sont fixés au niveau des plateformes par des moyens de fixation (pions/rivets), afin d'assurer l'étanchéité entre le distributeur et le carter externe.Furthermore, the inner and outer blade/platform assembly is fixed to the casing of the turbine. Sealing slats and joint covers are fixed at the level of the platforms by fixing means (pins/rivets), in order to ensure the seal between the distributor and the external casing.

Cependant, il peut arriver qu'en cours de vol, des contraintes mécaniques telles que des contraintes de cisaillement entre des pions/rivets et des lamelles d'étanchéité ou des couvre-joints provoquent la perte de ces lamelles d'étanchéité et couvre-joints. Ces derniers peuvent alors être libérés et être aspirés par le distributeur. En particulier, l'air de refroidissement pénétrant dans les cavités de la pale peut entrainer ces lamelles d'étanchéité et couvre-joints vers ces cavités. Les lamelles d'étanchéité et les couvre-joints sont alors susceptibles d'obturer partiellement ou totalement ces cavités. Le refroidissement des pales n'est alors plus ou insuffisamment assuré. La température des pales risque alors d'augmenter, pouvant entraîner la détérioration des propriétés des pales.However, it may happen that during flight, mechanical stresses such as shear stresses between studs/rivets and sealing strips or joint covers cause the loss of these sealing strips and joint covers. These can then be released and sucked up by the distributor. In particular, the cooling air penetrating into the cavities of the blade can drive these sealing strips and joint covers towards these cavities. The sealing slats and joint covers are then likely to partially or totally block these cavities. The cooling of the blades is then no longer or insufficiently ensured. The temperature of the blades may then increase, which may lead to the deterioration of the properties of the blades.

Il existe donc un besoin pour un dispositif permettant de résoudre le problème technique ci-dessus.There is therefore a need for a device making it possible to solve the above technical problem.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

Le présent exposé concerne un distributeur de turbine pour une turbomachine s'étendant radialement autour d'un axe, le distributeur comportant une pluralité de secteurs comprenant chacun au moins une pale qui s'étend radialement entre une plateforme intérieure et une plateforme extérieure, le distributeur comportant au moins deux lamelles d'étanchéité comportant chacune une portion principale configurée pour assurer l'étanchéité entre le distributeur et un élément de la turbomachine adjacent au distributeur, et une première portion pliée par rapport à la portion principale, la première portion pliée étant en contact avec une face externe d'au moins une plateforme, chaque lamelle étant maintenue à la au moins une plateforme par un moyen de serrage configuré pour serrer la première portion pliée entre la face externe de la plateforme et le moyen de serrage.This presentation relates to a turbine distributor for a turbomachine extending radially around an axis, the distributor comprising a plurality of sectors each comprising at least one blade which extends radially between an inner platform and an outer platform, the distributor comprising at least two sealing blades each comprising a main portion configured to provide sealing between the distributor and an element of the turbomachine adjacent to the distributor, and a first portion folded relative to the main portion, the first folded portion being contact with an external face of at least one platform, each slat being held to the at least one platform by a clamping means configured to clamp the first folded portion between the external face of the platform and the clamping means.

Dans le présent exposé, le terme « radial » et ses dérivés désignent une direction radiale de la turbine, c'est-à-dire une direction perpendiculaire à l'axe de la turbine. De plus, les termes « amont » et « aval » sont considérés suivant l'axe de la turbine, et suivant le sens d'écoulement des gaz dans la turbine, entre les deux plateformes, c'est-à-dire dans la veine de circulation des gaz. Par ailleurs, les pales sont agencées entre deux plateformes: une plateforme radialement extérieure, et une plateforme radialement intérieure, les plateformes intérieure et extérieure étant annulaires ou sous forme de secteur d'anneau et coaxiales. En outre, la « face externe » des plateformes désigne la face des plateformes opposée à la veine d'écoulement des gaz, cette dernière étant délimitée par la face interne des plateformes. En d'autres termes, la veine d'écoulement des gaz est délimitée par la face interne de la plateforme extérieure, et la face interne de la plateforme intérieure.In the present description, the term “radial” and its derivatives designate a radial direction of the turbine, that is to say a direction perpendicular to the axis of the turbine. In addition, the terms "upstream" and "downstream" are considered along the axis of the turbine, and according to the direction of gas flow in the turbine, between the two platforms, that is to say in the vein of gas circulation. Furthermore, the blades are arranged between two platforms: a radially outer platform, and a radially inner platform, the inner and outer platforms being annular or in the form of a ring sector and coaxial. In addition, the "external face" of the platforms refers to the face of the platforms opposite the vein gas flow, the latter being delimited by the internal face of the platforms. In other words, the gas flow path is delimited by the inner face of the outer platform, and the inner face of the inner platform.

Les lamelles d'étanchéité peuvent avoir la forme d'une plaque métallique, par exemple en un alliage à base de nickel et/ou de cobalt, et présentant une épaisseur inférieure à 1 mm.The sealing strips may have the form of a metal plate, for example made of an alloy based on nickel and/or cobalt, and having a thickness of less than 1 mm.

La plaque formant une lamelle d'étanchéité est pliée, de manière à former une première portion pliée, et une portion principale présentant une surface plus grande que la portion pliée.The plate forming a sealing strip is bent, so as to form a first bent portion, and a main portion having a larger surface than the bent portion.

La portion principale des lamelles est la portion de la lamelle présentant la plus grande surface, et s'étend d'une part dans une direction sensiblement parallèle à la direction radiale, ou légèrement inclinée par rapport à la direction radiale, et d'autre part dans une direction circonférentielle, en suivant la forme du distributeur, de manière à ce que la portion principale présente la forme d'un arc de cercle.The main portion of the slats is the portion of the slat having the largest surface, and extends on the one hand in a direction substantially parallel to the radial direction, or slightly inclined with respect to the radial direction, and on the other hand in a circumferential direction, following the shape of the distributor, so that the main portion has the shape of an arc of a circle.

La portion principale des lamelles est en contact avec un élément d'au moins un secteur de la turbomachine, par exemple un épaulement du secteur disposé à une extrémité amont ou aval de la plateforme, et avec un élément de la turbomachine adjacent au distributeur. Cet élément de la turbomachine peut être par exemple une partie d'un carter adjacent, ou une bride de la chambre de combustion.The main portion of the slats is in contact with an element of at least one sector of the turbine engine, for example a shoulder of the sector disposed at an upstream or downstream end of the platform, and with an element of the turbine engine adjacent to the distributor. This element of the turbomachine may for example be part of an adjacent casing, or a flange of the combustion chamber.

La portion pliée s'étend dans la direction axiale, c'est-à-dire de l'amont vers l'aval, et est en contact avec la face externe de la plateforme. La portion pliée est maintenue et serrée contre la face externe de la plateforme par l'intermédiaire du moyen de serrage. Ce dernier est configuré pour maintenir et serrer la portion pliée de chaque lamelle sur toute la circonférence du distributeur, en exerçant une pression sur les lamelles dans la direction radiale, de telle sorte que les portions pliées sont prises en sandwich entre le moyen de serrage et les faces externes des plateformes. Plus précisément, le moyen de serrage exerce une force sur les lamelles dirigée radialement vers l'axe de la turbine lorsque les lamelles sont disposées sur la plateforme extérieure, et dirigée radialement vers la direction opposée à l'axe de la turbine lorsque les lamelles sont disposées sur la plateforme intérieure.The folded portion extends in the axial direction, that is to say from upstream to downstream, and is in contact with the external face of the platform. The folded portion is held and clamped against the outer face of the platform by means of the clamping means. The latter is configured to hold and clamp the bent portion of each lamella over the entire circumference of the distributor, by exerting pressure on the lamellae in the radial direction, such that the bent portions are sandwiched between the clamping means and the outer faces of the platforms. More specifically, the clamping means exerts a force on the slats directed radially towards the axis of the turbine when the slats are arranged on the outer platform, and directed radially towards the direction opposite to the axis of the turbine when the slats are arranged on the interior platform.

Par conséquent, selon le présent exposé, la fixation des lamelles d'étanchéité au distributeur est assurée par les premières parties pliées et le moyen de fixation, et l'étanchéité entre le distributeur et les éléments de la turbomachine adjacents au distributeur est assurée par la portion principale. L'utilisation de pions et/ou de rivets permettant usuellement de fixer les lamelles sur le distributeur, par exemple sur l'épaulement du secteur disposé à une extrémité amont et/ou aval de la plateforme, n'est donc plus nécessaire. Le risque de perte des lamelles due au cisaillement des rivets est donc réduit. Par conséquent, le risque de détérioration des pales, due à l'obturation des cavités de refroidissement par les lamelles, est également réduit.Consequently, according to the present description, the fixing of the sealing strips to the distributor is ensured by the first bent parts and the fixing means, and the sealing between the distributor and the elements of the turbomachine adjacent to the distributor is ensured by the main portion. The use of studs and/or rivets which usually make it possible to fix the slats on the distributor, for example on the shoulder of the sector arranged at an upstream and/or downstream end of the platform, is therefore no longer necessary. The risk of loss of the strips due to the shearing of the rivets is therefore reduced. Consequently, the risk of damage to the blades, due to the blocking of the cooling cavities by the lamellae, is also reduced.

Dans certains modes de réalisation, le distributeur comporte deux lamelles formant chacune un demi-anneau, le moyen de serrage étant disposé autour du distributeur de manière à serrer les deux lamelles contre les faces externes des plateformes du distributeur.In certain embodiments, the distributor comprises two lamellae each forming a half-ring, the clamping means being arranged around the distributor so as to clamp the two lamellae against the external faces of the platforms of the distributor.

Selon cette configuration, chaque lamelle présente une forme d'arc de cercle de 180°. Lorsque plusieurs secteurs sont assemblés de manière à former la couronne du distributeur, chacune des deux lamelles de 180° est fixée sur la face externe des plateformes adjacentes de la couronne du distributeur, et sont maintenues et serrées contre ces faces externes par le moyen de serrage, ce dernier entourant le distributeur sur toute sa circonférence et maintient ainsi les deux lamelles simultanément. Les extrémités circonférentielles des deux lamelles sont jointes l'une à l'autre de manière à former un anneau d'étanchéité qui s'étend autour du distributeur. L'utilisation de deux lamelles permet de limiter le nombre de pièces nécessaires, de limiter les fuites inter-secteurs et de simplifier le processus de montage.According to this configuration, each slat has the shape of an arc of a circle of 180°. When several sectors are assembled in such a way as to form the crown of the distributor, each of the two 180° blades is fixed to the external face of the adjacent platforms of the crown of the distributor, and are held and tightened against these external faces by the clamping means , the latter surrounding the distributor over its entire circumference and thus maintains the two slats simultaneously. The circumferential ends of the two lamellae are joined together so as to form a sealing ring which extends around the dispenser. The use of two slats makes it possible to limit the number of parts required, to limit inter-sector leaks and to simplify the assembly process.

Dans certains modes de réalisation, la portion principale et la première portion pliée de chaque lamelle forment entre elles un angle compris entre 90° et 150°.In some embodiments, the main portion and the first folded portion of each slat form between them an angle comprised between 90° and 150°.

On comprend que cet angle entre la portion principale et la première portion pliée de chaque lamelle est l'angle naturel que forment ces deux portions de la lamelle, c'est-à-dire lorsqu'aucun effort tendant à déformer la lamelle, et donc à modifier cet angle, n'est exercé sur la lamelle. Selon cette configuration, la plaque formant la lamelle n'est pas pliée de manière à former un angle droit entre la portion principale et la portion pliée, mais de manière à former un angle obtus entre ces dernières. En d'autres termes, lorsque la lamelle est fixée à un distributeur, le plan dans lequel s'étend la portion principale de la lamelle n'est pas parallèle par rapport à la direction radiale, mais légèrement incliné par rapport à celui-ci. Cette configuration permet d'améliorer l'étanchéité entre le distributeur et l'élément de la turbomachine adjacent au distributeur. En effet, de par l'inclinaison de la portion principale, l'élément de la turbomachine adjacent au distributeur vient en contact avec l'extrémité radiale de la portion principale. Ce contact tend à déformer la lamelle de manière à réduire l'angle entre la portion principale et la portion pliée. La portion principale, tendant à revenir dans sa position initiale par élasticité, agit ainsi comme un ressort en exerçant une pression sur l'élément de la turbomachine adjacent au distributeur. En d'autres termes, la pression de contact entre la portion principale de la lamelle et l'élément de la turbomachine adjacent au distributeur est accrue, améliorant ainsi l'étanchéité entre cet élément et le distributeur.It is understood that this angle between the main portion and the first folded portion of each slat is the natural angle formed by these two portions of the slat, that is to say when there is no force tending to deform the slat, and therefore to modify this angle, is exerted on the lamella. According to this configuration, the plate forming the lamella is not folded so as to form a right angle between the portion main and the folded portion, but so as to form an obtuse angle between them. In other words, when the lamella is fixed to a distributor, the plane in which the main portion of the lamella extends is not parallel with respect to the radial direction, but slightly inclined with respect thereto. This configuration makes it possible to improve the seal between the distributor and the element of the turbomachine adjacent to the distributor. Indeed, due to the inclination of the main portion, the element of the turbomachine adjacent to the distributor comes into contact with the radial end of the main portion. This contact tends to deform the strip so as to reduce the angle between the main portion and the bent portion. The main portion, tending to return to its initial position by elasticity, thus acts like a spring by exerting pressure on the element of the turbomachine adjacent to the distributor. In other words, the contact pressure between the main portion of the strip and the element of the turbomachine adjacent to the distributor is increased, thus improving the seal between this element and the distributor.

Dans certains modes de réalisation, les lamelles comportent chacune une deuxième portion pliée s'étendant depuis la première portion pliée, sensiblement perpendiculairement à celle-ci, et venant en contact avec une paroi radiale qui s'étend radialement en saillie de l'au moins une plateforme.In some embodiments, the slats each comprise a second bent portion extending from the first bent portion, substantially perpendicular thereto, and coming into contact with a radial wall which extends radially projecting from the at least a platform.

Selon cette configuration, les lamelles sont pliées de manière à présenter trois portions : la portion principale, la première portion pliée en contact avec la face externe de la plateforme, et la deuxième portion pliée, la première portion pliée étant interposée entre la portion principale et la deuxième portion pliée, de manière à ce que, dans une section transversale, la lamelle présente sensiblement la forme d'un U.According to this configuration, the slats are folded so as to present three portions: the main portion, the first folded portion in contact with the external face of the platform, and the second folded portion, the first folded portion being interposed between the main portion and the second portion folded, so that, in a cross section, the lamella has substantially the shape of a U.

La présence de la deuxième portion pliée permet de limiter les déplacements du moyen de serrage suivant la direction axiale. Plus précisément, la lamelle ainsi pliée prend la forme d'une gouttière dans laquelle est logé le moyen de serrage, limitant ainsi ses déplacements axiaux, et limitant les risques qu'un serrage suffisant de la lamelle contre la plateforme ne soit plus assuré. Par serrage suffisant, on comprend un serrage permettant d'empêcher que la lamelle ne se détache au cours d'un fonctionnement normal de la turbomachine.The presence of the second bent portion makes it possible to limit the displacements of the clamping means in the axial direction. More precisely, the slat thus folded takes the form of a gutter in which the clamping means is housed, thus limiting its axial displacements, and limiting the risks that sufficient clamping of the slat against the platform is no longer ensured. Sufficient tightening means tightening making it possible to prevent the lamella from becoming detached during normal operation of the turbine engine.

Dans certains modes de réalisation, deux lamelles circonférentiellement adjacentes autour du distributeur sont disposées de manière à ce qu'une extrémité circonférentielle de la portion principale d'une lamelle soit superposée à une extrémité circonférentielle de la portion principale d'une lamelle circonférentiellement adjacente.In some embodiments, two circumferentially adjacent sipes around the dispenser are arranged such that a circumferential end of the main portion of one sipe is superimposed on a circumferential end of the main portion of a circumferentially adjacent sipe.

Dans certains modes de réalisation, l'extrémité circonférentielle de la portion principale d'une lamelle et l'extrémité circonférentielle de la portion principale de la lamelle adjacente se superposent sur une distance comprise entre 1 et 10 mm.In some embodiments, the circumferential end of the main portion of a lamella and the circumferential end of the main portion of the adjacent lamella overlap over a distance of between 1 and 10 mm.

En d'autres termes, les dimensions de chaque lamelle sont prévues de manière à ce que les extrémités circonférentielles de celles-ci se chevauchent entre elles, sur toute leur hauteur. On comprend par hauteur leur longueur dans la direction radiale. Par exemple, lorsque le distributeur comporte deux lamelles de 180° formant chacune un demi anneau, la circonférence d'une des deux lamelles est sensiblement plus grande que l'autre, de manière à chevaucher les extrémités de cette dernière.In other words, the dimensions of each slat are provided so that the circumferential ends thereof overlap with each other, over their entire height. By height is understood their length in the radial direction. For example, when the dispenser has two 180° lamellae each forming a half-ring, the circumference of one of the two lamellae is substantially larger than the other, so as to overlap the ends of the latter.

Cette configuration permet d'éviter la présence d'un jeu entre les extrémités circonférentielles de chaque lamelle, et donc d'améliorer l'étanchéité entre le distributeur et un élément de la turbomachine adjacent au distributeur.This configuration makes it possible to avoid the presence of a clearance between the circumferential ends of each strip, and therefore to improve the seal between the distributor and an element of the turbomachine adjacent to the distributor.

Dans certains modes de réalisation, le moyen de serrage comporte au moins une surface de serrage, la surface de serrage étant en contact avec la première portion pliée.In certain embodiments, the clamping means comprises at least one clamping surface, the clamping surface being in contact with the first bent portion.

La présence d'au moins une surface de serrage plane permet d'obtenir un contact plan entre le moyen de serrage et la première portion pliée, augmentant la surface de contact, et donc la fiabilité de serrage de la lamelle sur la plateforme.The presence of at least one flat clamping surface makes it possible to obtain flat contact between the clamping means and the first bent portion, increasing the contact surface, and therefore the reliability of clamping the lamella on the platform.

Dans certains modes de réalisation, le moyen de serrage est un jonc.In certain embodiments, the clamping means is a rod.

On entend par jonc un anneau, de préférence métallique, présentant deux extrémités libres en vis-à-vis mais disjointes l'une de l'autre. Ce dispositif présente l'avantage d'être simple et peu coûteux.Ring means a ring, preferably metallic, having two free ends vis-à-vis but separate from each other. This device has the advantage of being simple and inexpensive.

Dans certains modes de réalisation, le distributeur comporte au moins une lame fixée à la paroi radiale, et configurée pour exercer une pression sur une lamelle.In certain embodiments, the distributor comprises at least one blade fixed to the radial wall, and configured to exert pressure on a blade.

La lame est fixée à la paroi radiale, et est orientée de manière à prendre appui sur une lamelle du distributeur, exerçant ainsi une pression sur celle-ci. Cela permet d'exercer une pression contre les portions principales des lamelles, et accentuer ainsi la pression de contact entre les portions principales et l'élément de la turbomachine axialement adjacent au distributeur, améliorant ainsi davantage l'étanchéité.The blade is fixed to the radial wall, and is oriented so as to rest on a strip of the distributor, thus exerting pressure thereon. This makes it possible to exert pressure against the main portions of the slats, and thus accentuate the contact pressure between the main portions and the element of the turbomachine axially adjacent to the distributor, thus further improving the seal.

Le présent exposé concerne également une turbomachine comportant un distributeur selon l'un quelconque des modes de réalisation précédents.This presentation also relates to a turbine engine comprising a distributor according to any one of the preceding embodiments.

BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

L'invention et ses avantages seront mieux compris à la lecture de la description détaillée faite ci-après de différents modes de réalisation de l'invention donnés à titre d'exemples non limitatifs. Cette description fait référence aux pages de figures annexées, sur lesquelles :

  • la figure 1 représente une vue partielle en perspective d'un distributeur de turbine pour une turbomachine selon l'art antérieure ;
  • la figure 2 représente une vue partielle en perspective d'un distributeur de turbine pour une turbomachine selon l'art antérieure, lorsqu'un orifice est obturé ;
  • la figure 3 représente une vue partielle en perspective d'un distributeur de turbine pour une turbomachine selon le présent exposé ;
  • la figure 4 représente une vue en perspective de la jonction entre deux lamelles selon le présent exposé ;
  • la figure 5 représente une section de l'extrémité d'une plateforme d'un distributeur selon le présent exposé.
  • la figure 6 représente une vue partielle du dessus d'une extrémité d'une plateforme selon le présent exposé.
The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given by way of non-limiting examples. This description refers to the pages of appended figures, on which:
  • the figure 1 shows a partial perspective view of a turbine nozzle for a turbomachine according to the prior art;
  • the picture 2 shows a partial perspective view of a turbine nozzle for a turbomachine according to the prior art, when an orifice is closed;
  • the picture 3 shows a partial perspective view of a turbine nozzle for a turbomachine according to the present disclosure;
  • the figure 4 shows a perspective view of the junction between two slats according to the present description;
  • the figure 5 represents a section of the end of a platform of a distributor according to the present description.
  • the figure 6 shows a partial top view of one end of a platform according to the present description.

DESCRIPTION DETAILLEE D'EXEMPLES DE REALISATIONDETAILED DESCRIPTION OF EXAMPLES OF REALIZATION

La figure 1 représente un secteur 10 d'un distributeur pour une turbine haute pression de turbomachine selon l'art antérieur, le distributeur comportant une couronne de pales fixes 13 creuses, agencées entre deux plateformes annulaires coaxiales : une plateforme extérieure 16 et une plateforme intérieure 18. Les plateformes sont formées par des secteurs d'anneau qui s'étendent autour de l'axe X et qui délimitent une veine de circulation de gaz 20 dans laquelle se trouvent les pales 13 réparties régulièrement circonférentiellement et qui s'étendent radialement entre les plateformes 16, 18. Chaque pale comporte une cavité 26 débouchant à l'extérieur de la veine 20 au travers de la plateforme extérieure 16. De même, chaque pale comporte une cavité (non représentée) débouchant à l'extérieur de la veine au travers de la plateforme intérieure 18. Ces cavités communiquent avec la veine 20 par des rangées de trous 30 s'étendant axialement et/ou radialement entre la plateforme intérieure 18 et la plateforme extérieure 16 le long des pales 13 pour déboucher dans la veine 20. Un gaz circulant depuis l'extérieur de la veine 20 peut ainsi pénétrer dans la cavité 26, s'écouler dans la pale 13, puis être évacué dans la veine 20 par l'intermédiaire des orifices 30, permettant ainsi le refroidissement de la pale 13.The figure 1 represents a sector 10 of a distributor for a high-pressure turbine of a turbomachine according to the prior art, the distributor comprising a crown of fixed hollow blades 13, arranged between two coaxial annular platforms: an outer platform 16 and an inner platform 18. platforms are formed by ring sectors which extend around the axis X and which delimit a gas circulation vein 20 in which are located the blades 13 distributed regularly circumferentially and which extend radially between the platforms 16, 18 Each blade has a cavity 26 opening outside the passage 20 through the outer platform 16. Similarly, each blade has a cavity (not shown) opening outside the passage through the inner platform 18. These cavities communicate with the stream 20 by rows of holes 30 extending axially and/or radially between the inner platform 18 and the outer platform 16 along the blades 13 to open into the stream 20. A gas flowing from the The exterior of the stream 20 can thus enter the cavity 26, flow into the blade 13, then be evacuated into the stream 20 via the orifices 30, thus allowing the cooling of the blade 13.

Dans la suite de l'exposé, la description est faite en se référant à la plateforme extérieure 16, notamment sur les figures. Cependant, une description analogue est applicable à la plateforme intérieure 18.In the following description, the description is made with reference to the outer platform 16, in particular in the figures. However, a similar description is applicable to the inner platform 18.

Une chemise 36 est insérée dans la cavité 26, de manière à définir un orifice 37 sur la face externe de la plateforme 16. Par « externe », on comprend la face de la plateforme opposée à la veine 20. La chemise 36 comporte en outre une collerette 38 prenant appui sur la face externe de la plateforme 16. Une chemise (non représentée) est également insérée dans la cavité du côté de la plateforme intérieure 18, de manière à définir un orifice sur la face externe de la plateforme intérieure 18.A sleeve 36 is inserted into the cavity 26, so as to define an orifice 37 on the external face of the platform 16. By "external", is meant the face of the platform opposite to the vein 20. The sleeve 36 further comprises a flange 38 resting on the outer face of the platform 16. A jacket (not shown) is also inserted into the cavity on the side of the inner platform 18, so as to define an orifice on the outer face of the inner platform 18.

Le secteur 10 de distributeur comporte également des lamelles d'étanchéité 12 fixées sur les plateformes 16, 18, et permettant d'assurer l'étanchéité entre le distributeur et un élément de la turbomachine 1 axialement adjacent au distributeur. Plus précisément, les lamelles d'étanchéité 12 sont fixées sur des épaulements 161, 162 de la plateforme 16, par l'intermédiaire de pions et/ou rivets 14.The distributor sector 10 also comprises sealing strips 12 fixed on the platforms 16, 18, and making it possible to ensure sealing between the distributor and an element of the turbomachine 1 axially adjacent to the distributor. More specifically, the sealing strips 12 are fixed on the shoulders 161, 162 of the platform 16, by means of pins and/or rivets 14.

La figure 2 illustre une configuration que l'invention cherche à prévenir et selon laquelle, après le détachement d'une lamelle 12 de son emplacement de fixation au distributeur haute pression en raison des contraintes de cisaillement entre les rivets 14 et la lamelle 12, cette dernière est aspirée par l'air entrant dans la cavité 26, et vient obstruer l'orifice 37, empêchant ainsi l'air, partiellement ou totalement, de pénétrer dans la cavité 26.The figure 2 illustrates a configuration that the invention seeks to prevent and according to which, after the detachment of a lamella 12 from its location of attachment to the high-pressure distributor due to the shearing stresses between the rivets 14 and the lamella 12, the latter is sucked in by the air entering the cavity 26, and obstructs the orifice 37, thus preventing the air, partially or totally, from entering the cavity 26.

La figure 3 représente un secteur 10 d'un distributeur de turbine haute pression pour turbomachine selon un mode de réalisation de l'invention. Les éléments identiques aux éléments des figures 1 et 2 présentent les même signes de référence et ne seront pas décrits à nouveau. Une portion d'une lamelle 12 est illustrée sur la figure 3. Néanmoins, un distributeur selon le présent mode de réalisation, comportant une pluralité de secteurs 10 assemblés les uns aux autres, peut comporter deux lamelles 12 semi-annulaires s'étendant sur 180°, de manière à ce que ces dernières entourent la couronne du distributeur lorsqu'elles sont assemblées l'une à l'autre. A la différence du secteur décrit en référence aux figures 1 et 2, le secteur 10 décrit ci-dessous ne comporte pas de rivets 14 pour fixer les lamelles 12 aux épaulements de la plateforme.The picture 3 represents a sector 10 of a high pressure turbine nozzle for a turbomachine according to one embodiment of the invention. The elements identical to the elements of the figures 1 and 2 have the same reference signs and will not be described again. A portion of a lamella 12 is illustrated in the picture 3 . Nevertheless, a distributor according to the present embodiment, comprising a plurality of sectors 10 assembled together, may comprise two semi-annular strips 12 extending over 180°, so that the latter surround the crown of the distributor. when assembled together. Unlike the sector described with reference to figures 1 and 2 , the sector 10 described below does not include rivets 14 to fix the slats 12 to the shoulders of the platform.

Selon ce mode de réalisation, chaque lamelle 12 comporte une portion principale 120, une première portion pliée 121, et une deuxième portion pliée 122. Pour ce faire, avant la fixation de la lamelle au distributeur, la lamelle 12 est pliée dans un premier temps en deux de manière à obtenir la portion principale 120 et la première portion pliée 121, et de manière à ce que la portion principale 120 et la première portion pliée 121 présentent entre elles un angle sensiblement supérieur à 90°. Plus précisément, la portion principale 120 et la première portion pliée 121 présentent entre elles un angle de 90° + α, où α est inférieur à 60°, de préférence inférieur à 20°. La lamelle 12 est à nouveau pliée de manière à obtenir la deuxième portion pliée 122, la première portion pliée 121 et la deuxième portion pliée 122 étant sensiblement perpendiculaire l'une à l'autre. La lamelle 12 ainsi formée présente ainsi sensiblement la forme d'un U, en section dans un plan de coupe transversal qui s'étend axialement et radialement, de manière à former une gorge ou une gouttière autour de la couronne du distributeur lorsque les lamelles sont fixées sur les plateformes du distributeur, permettant ainsi, lorsqu'un élément de serrage est logé dans cette gorge, de limiter ainsi les déplacements axiaux de celui-ci. Les déplacements axiaux de l'élément de serrage et des lamelles sont également limités par une paroi radiale 163 qui s'étend radialement en saillie depuis la plateforme.According to this embodiment, each slat 12 comprises a main portion 120, a first folded portion 121, and a second folded portion 122. To do this, before fixing the slat to the dispenser, the slat 12 is first folded in two so as to obtain the main portion 120 and the first folded portion 121, and so that the main portion 120 and the first folded portion 121 have between them an angle substantially greater than 90°. More precisely, the main portion 120 and the first folded portion 121 have between them an angle of 90°+α, where α is less than 60°, preferably less than 20°. The slat 12 is folded again so as to obtain the second folded portion 122, the first folded portion 121 and the second folded portion 122 being substantially perpendicular to each other. The lamella 12 thus formed thus has substantially the shape of a U, in section in a transverse section plane which extends axially and radially, so as to form a groove or a gutter around the crown of the distributor when the lamellae are fixed on the platforms of the distributor, thus making it possible, when a clamping element is housed in this groove, to thus limit the axial displacements of the latter. The axial displacements of the element of clamping and slats are also limited by a radial wall 163 which extends radially projecting from the platform.

De la même façon que la lamelle 12 selon l'art antérieure, la portion principale 120 permet d'assurer l'étanchéité entre le distributeur et l'élément de la turbomachine 1 axialement adjacent au distributeur, par exemple une bride de la chambre de combustion ou une partie d'un carter axialement adjacent, en étant en contact avec un épaulement 161 de la plateforme 16 et l'élément de la turbomachine 1 adjacent au distributeur. En effet, lorsque la lamelle 12 est fixée au distributeur, et de par l'inclinaison de sa portion principale 120, l'élément de la turbomachine 1 axialement adjacent au distributeur vient en contact avec l'extrémité radiale de la portion principale 120 lors de l'assemblage ou au cours du fonctionnement de la turbomachine. Ce contact engendre une force sur l'extrémité radiale de la portion principale 120, tendant à réduire l'angle entre la portion principale 120 et la portion pliée 121. La portion principale 120, tendant à revenir dans sa position initiale par élasticité, agit ainsi comme un ressort en exerçant une pression sur l'élément de la turbomachine 1 axialement adjacent au distributeur. La valeur de l'angle α est déterminée de manière à ce que, lorsque le distributeur est assemblé à la turbomachine, et au cours d'un fonctionnement normal de celle-ci, un contact existe toujours entre la portion principale 120 de la lamelle 12 et l'élément de la turbomachine 1 axialement adjacent au distributeur.In the same way as the lamella 12 according to the prior art, the main portion 120 makes it possible to ensure sealing between the distributor and the element of the turbomachine 1 axially adjacent to the distributor, for example a flange of the combustion chamber or a part of an axially adjacent casing, being in contact with a shoulder 161 of the platform 16 and the element of the turbomachine 1 adjacent to the distributor. Indeed, when the lamella 12 is fixed to the distributor, and due to the inclination of its main portion 120, the element of the turbomachine 1 axially adjacent to the distributor comes into contact with the radial end of the main portion 120 during assembly or during operation of the turbomachine. This contact generates a force on the radial end of the main portion 120, tending to reduce the angle between the main portion 120 and the folded portion 121. The main portion 120, tending to return to its initial position by elasticity, thus acts like a spring by exerting pressure on the element of the turbomachine 1 axially adjacent to the distributor. The value of the angle α is determined so that, when the distributor is assembled to the turbine engine, and during normal operation of the latter, a contact always exists between the main portion 120 of the lamella 12 and the element of the turbomachine 1 axially adjacent to the distributor.

La figure 6 représente une vue partielle du dessus, c'est-à-dire selon la direction radiale, d'une extrémité amont d'une plateforme 16. Des lames, ou épingles 170, servant à exercer une pression sur des couvres joints afin de maintenir ces derniers au niveau des jonctions entre deux lamelles 12 circonférentiellement adjacentes peuvent être utilisées afin d'exercer une pression contre les portions principales 120 des lamelles 12 par l'intermédiaire d'une portion de contact 171, et accentuer ainsi la pression de contact entre les portions principales 120 et l'élément de la turbomachine 1, améliorant ainsi davantage l'étanchéité. Ces épingles sont fixées sur une paroi radiale 163 par l'intermédiaire d'un rivet 164. On note que les rivets 164 servant à fixer ces épingles 170 au distributeur, ne sont pas en contact avec les lamelles 12, ce qui permet de limiter l'endommagement par cisaillement des lamelles 12.The figure 6 represents a partial view from above, that is to say in the radial direction, of an upstream end of a platform 16. Blades, or pins 170, used to exert pressure on joint covers in order to maintain these latter at the junctions between two circumferentially adjacent strips 12 can be used to exert pressure against the main portions 120 of the strips 12 via a contact portion 171, and thus increase the contact pressure between the portions main 120 and the element of the turbomachine 1, thus further improving the seal. These pins are fixed on a radial wall 163 by means of a rivet 164. It is noted that the rivets 164 used to fix these pins 170 to the distributor, are not in contact with the slats 12, which makes it possible to limit the damage by shearing of the slats 12.

En outre, la première portion pliée 121 est plaquée contre la face externe de la plateforme 16 par un moyen de serrage 40, ce dernier étant configuré pour exercer une pression dans la direction radiale sur la première portion pliée 121, cette dernière étant ainsi prise en sandwich entre le moyen de serrage 40 et la plateforme 16. Selon ce mode de réalisation, le moyen de serrage 40 est un jonc, permettant de serrer simultanément les deux lamelles 12 de 180° contre la face externe des plateformes du distributeur, le jonc venant se loger dans la gorge formée par la portion principale 120, la première portion pliée 121 et la deuxième portion pliée 122.In addition, the first bent portion 121 is pressed against the outer face of the platform 16 by a clamping means 40, the latter being configured to exert pressure in the radial direction on the first bent portion 121, the latter thus being taken into sandwich between the clamping means 40 and the platform 16. According to this embodiment, the clamping means 40 is a rod, making it possible to simultaneously clamp the two slats 12 by 180° against the external face of the platforms of the distributor, the rod coming lodge in the groove formed by the main portion 120, the first folded portion 121 and the second folded portion 122.

Le jonc est un anneau ouvert, de préférence métallique, par exemple en un alliage à base de nickel et/ou de cobalt, présentant deux extrémités libres circonférentiellement en vis-à-vis, mais séparées l'une de l'autre. Le jonc présente un diamètre initial D0. Lorsque ces deux extrémités libres sont éloignées l'une de l'autre, à l'aide d'une pince par exemple, le jonc métallique se déforme élastiquement de telle sorte que son diamètre augmente, permettant de disposer ce dernier autour du distributeur, tout en maintenant les extrémités éloignées l'une de l'autre. Lorsque le jonc est à la position souhaitée, dans la gorge formée par les lamelles 12, ses extrémités libres sont relâchées. Le jonc tend alors à retrouver sa forme initiale, jusqu'à ce qu'il vienne en butée contre la première portion pliée 121, atteignant ainsi son diamètre final Df, lorsqu'il serre les lamelles 12 contre la face externe des plateformes extérieures 16. Afin que la force exercée par le moyen de serrage 40 sur la première portion pliée 121 soit suffisante, c'est-à-dire qu'il assure un serrage permettant d'éviter que la lamelle ne se détache, le diamètre initial D0 du jonc doit donc être inférieur au diamètre final Df.The ring is an open ring, preferably metallic, for example made of an alloy based on nickel and/or cobalt, having two circumferentially facing free ends, but separated from each other. The rod has an initial diameter D 0 . When these two free ends are moved away from each other, using pliers for example, the metal rod deforms elastically so that its diameter increases, allowing it to be placed around the distributor, while keeping the ends away from each other. When the rod is in the desired position, in the groove formed by the slats 12, its free ends are released. The rod then tends to regain its initial shape, until it comes into abutment against the first folded portion 121, thus reaching its final diameter D f , when it presses the slats 12 against the outer face of the outer platforms 16 In order for the force exerted by the clamping means 40 on the first folded portion 121 to be sufficient, that is to say that it provides clamping making it possible to prevent the lamella from coming off, the initial diameter D 0 of the rod must therefore be less than the final diameter D f .

Cet exemple présente le serrage d'une lamelle 12 sur la face externe d'une plateforme extérieure 16. Néanmoins, le moyen de serrage 40 peut également être utilisé pour serrer une lamelle 12 sur la face externe d'une plateforme intérieure 18. Dans ce cas, à l'inverse du cas décrit dans le paragraphe précédent, le jonc est déformé en rapprochant les extrémités libres de celui-ci, amenant ces extrémités à se chevaucher, de telle sorte que le diamètre du jonc diminue. Lorsque le jonc est à la position souhaitée, dans la gorge formée par les lamelles 12, la position déformée du jonc est alors relâchée. Le diamètre du jonc tend alors à augmenter de nouveau pour retrouver sa forme initiale, jusqu'à ce qu'il vienne en butée contre la première portion pliée 121, atteignant ainsi son diamètre final Df, lorsqu'il serre les lamelles 12 contre la face externe des plateformes intérieures 18. Afin que la force exercée par le moyen de serrage 40 sur la première portion pliée 121 soit suffisante, c'est-à-dire qu'il assure un serrage permettant d'éviter que la lamelle ne se détache, le diamètre initial D0 du jonc doit donc être supérieur au diamètre final Df.This example shows the clamping of a slat 12 on the outer face of an outer platform 16. Nevertheless, the clamping means 40 can also be used to clamp a slat 12 on the outer face of an inner platform 18. In this case, unlike the case described in the previous paragraph, the rod is deformed by bringing the free ends thereof closer together, causing these ends to overlap, so that the diameter of the rod decreases. When the rod is in the desired position, in the groove formed by the slats 12, the deformed position of the rod is then released. The diameter of the rod then tends to increase again to regain its initial shape, until it comes into abutment against the first folded portion 121, thus reaching its final diameter D f , when it presses the slats 12 against the external face of the internal platforms 18. In order for the force exerted by the clamping means 40 on the first folded portion 121 to be sufficient, that is to say that it provides clamping making it possible to prevent the slat from coming off , the initial diameter D 0 of the rod must therefore be greater than the final diameter D f .

Bien que dans le mode de réalisation décrit ci-dessus, le moyen de serrage 40 soit un jonc, d'autres moyens de serrage sont envisageables, tels que des circlips, des colliers de serrage ou des bagues comportant par exemple une première portion et une deuxième portion, les première et deuxième portions étant fixées ensemble autour du distributeur de manière à serrer les lamelles contre les faces externes des plateformes du distributeur.Although in the embodiment described above, the clamping means 40 is a rod, other clamping means are possible, such as circlips, clamps or rings comprising for example a first portion and a second portion, the first and second portions being fastened together around the distributor so as to clamp the slats against the external faces of the platforms of the distributor.

Par ailleurs, les portions principales 120 de chaque lamelle 12 présentent une extrémité circonférentielle 120a, ladite extrémité circonférentielle 120a s'étendant suivant la direction radiale. Les dimensions des lamelles 12 sont configurées de telle sorte que les extrémités circonférentielles 120a de deux lamelles circonférentiellement adjacentes se chevauchent, de manière à former une portion de chevauchement 125. Cette portion de chevauchement 125 permet d'assurer l'étanchéité de jonction entre deux lamelles 12 circonférentiellement adjacentes. Les dimensions des lamelles 12 sont configurées de telle sorte la portion de chevauchement 125 s'étendent sur un angle compris entre 1 et 10°. La portion de chevauchement peut également être formée en emboutissant une extrémité circonférentielle d'une lamelle 12, créant ainsi un décaissement sur une face de la portion principale 120, à l'extrémité circonférentielle de cette lamelle 12, l'extrémité circonférentielle de la lamelle adjacente venant alors se loger dans ce décaissement (cf. figure 4).Furthermore, the main portions 120 of each strip 12 have a circumferential end 120a, said circumferential end 120a extending in the radial direction. The dimensions of the slats 12 are configured such that the circumferential ends 120a of two circumferentially adjacent slats overlap, so as to form an overlapping portion 125. This overlapping portion 125 makes it possible to seal the junction between two slats 12 circumferentially adjacent. The dimensions of the slats 12 are configured such that the overlapping portion 125 extends over an angle between 1 and 10°. The overlapping portion can also be formed by stamping a circumferential end of a lamella 12, thus creating a recess on one face of the main portion 120, at the circumferential end of this lamella 12, the circumferential end of the adjacent lamella then coming to stay in this disbursement (cf. figure 4 ).

En outre, pour chaque lamelle 12, la longueur selon la circonférence (en d'autres termes la longueur de l'arc de cercle) de la première portion pliée 121 et de la deuxième portion pliée 122, est sensiblement inférieure à la longueur selon la circonférence de la portion principale 120. Ainsi, seules les extrémités circonférentielles des portions principales 120 se chevauchent. Les extrémités circonférentielles de la première portion pliée 121 et de la deuxième portion pliée 122 de deux lamelles 12 circonférentiellement adjacentes sont disjointes l'une de l'autre. Cette configuration permet de faciliter l'assemblage des lamelles 12 autour du distributeur, et notamment la jonction de deux lamelles 12 adjacentes.In addition, for each slat 12, the length along the circumference (in other words the length of the arc of a circle) of the first folded portion 121 and of the second folded portion 122 is substantially less than the length along the portion circumference main 120. Thus, only the circumferential ends of the main portions 120 overlap. The circumferential ends of the first folded portion 121 and of the second folded portion 122 of two circumferentially adjacent strips 12 are separate from each other. This configuration facilitates the assembly of the slats 12 around the distributor, and in particular the joining of two adjacent slats 12.

Bien que la présente invention ait été décrite en se référant à des exemples de réalisation spécifiques, il est évident que des modifications et des changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. En particulier, des caractéristiques individuelles des différents modes de réalisation illustrés/mentionnés peuvent être combinées dans des modes de réalisation additionnels. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que restrictif.Although the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the different illustrated/mentioned embodiments can be combined in additional embodiments. Accordingly, the description and the drawings should be considered in an illustrative rather than restrictive sense.

Claims (10)

  1. A nozzle for a turbomachine turbine extending about an axis (X), the nozzle including a plurality of sectors (10) each comprising at least one vane (13) which extends radially between an internal platform (18) and an external platform (16), the nozzle including at least two sealing strips (12) each including a main portion (120) configured to ensure the sealing between the nozzle and an element (1) of the turbomachine which is adjacent to the nozzle, and a first portion (121) folded relative to the main portion (120), characterized in that the first folded portion (121) being in contact with an outer face of at least one platform (16, 18), each strip (12) being held to the at least one platform (16, 18) by a clamping means (40) configured to clamp the first folded portion (121) between the outer face of the platform (16, 18) and the clamping means (40).
  2. The nozzle according to claim 1, including two strips (12) each forming a half-ring, the clamping means (40) being disposed around the nozzle so as to clamp the two strips (12) against the outer faces of the platforms (16, 18) of the nozzle.
  3. The nozzle according to claim 1 or 2, wherein the main portion (120) and the first folded portion (121) of each strip (12) form therebetween an angle comprised between 90° and 150°.
  4. The nozzle according to any one of claims 1 to 3, wherein the strips (12) each include a second folded portion (122) extending from the first folded portion (121), substantially perpendicularly thereto, and coming into contact with a radial wall (163) which protrudes radially from the at least one platform (16, 18).
  5. The nozzle according to any one of claims 1 to 4, comprising two strips (12) circumferentially adjacent around the nozzle disposed such that a circumferential end (120a) of the main portion (120) of a strip (12) is superimposed on a circumferential end (120a) of the main portion (120) of the adjacent strip (12).
  6. The nozzle according to claim 5, wherein the circumferential end (120a) of the main portion (120) of a strip (12) and the circumferential end (120a) of the main portion (120) of the adjacent strip (12) are superimposed over a distance comprised between 1 and 10 mm.
  7. The nozzle according to any one of claims 1 to 6, wherein the clamping means (40) includes at least one clamping surface, the clamping surface being in contact with the first folded portion (121).
  8. The nozzle according to any one of claims 1 to 7, wherein the clamping means (40) is a bead.
  9. The nozzle according to any one of claims 4 to 8, including at least one slat (170) fixed to the radial wall (163), and configured to exert pressure on a strip (12).
  10. A turbomachine including a nozzle according to any one of the preceding claims.
EP19787014.0A 2018-09-26 2019-09-06 Improved turbomachine stator Active EP3857028B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1858804A FR3086329B1 (en) 2018-09-26 2018-09-26 IMPROVED TURBOMACHINE DISTRIBUTOR
PCT/FR2019/052057 WO2020065161A1 (en) 2018-09-26 2019-09-06 Improved turbomachine stator

Publications (2)

Publication Number Publication Date
EP3857028A1 EP3857028A1 (en) 2021-08-04
EP3857028B1 true EP3857028B1 (en) 2022-08-03

Family

ID=65243888

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19787014.0A Active EP3857028B1 (en) 2018-09-26 2019-09-06 Improved turbomachine stator

Country Status (5)

Country Link
US (1) US11408292B2 (en)
EP (1) EP3857028B1 (en)
CN (1) CN112771247B (en)
FR (1) FR3086329B1 (en)
WO (1) WO2020065161A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3112813B1 (en) * 2020-07-24 2022-08-19 Safran Aircraft Engines ANTI-SHEARING ASSEMBLY OF A LAMINATE AND A PIN

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314793A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Temperature actuated turbine seal
US5797723A (en) * 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
FR2786222B1 (en) * 1998-11-19 2000-12-29 Snecma LAMELLE SEALING DEVICE
FR2829796B1 (en) * 2001-09-20 2003-12-12 Snecma Moteurs DEVICE FOR HOLDING JOINTS OF PLATFORMS OF DISTRIBUTOR SECTORS OF TURBOMACHINE WITH SEALING BLADES
FR2860264B1 (en) * 2003-09-30 2006-02-10 Snecma Moteurs TURBOMACHINE COMPRISING TWO ELEMENTS MADE IN COMMUNICATION WITH INTERPOSITION OF A JOINT
US7246995B2 (en) * 2004-12-10 2007-07-24 Siemens Power Generation, Inc. Seal usable between a transition and a turbine vane assembly in a turbine engine
FR2955145B1 (en) 2010-01-14 2012-02-03 Snecma HIGH PRESSURE TURBINE DISPENSER OF A TURBOREACTOR
US8985592B2 (en) * 2011-02-07 2015-03-24 Siemens Aktiengesellschaft System for sealing a gap between a transition and a turbine
CN105378226B (en) * 2013-07-19 2017-11-10 通用电气公司 Turbine nozzle with impact baffle plate
US10077669B2 (en) * 2014-11-26 2018-09-18 United Technologies Corporation Non-metallic engine case inlet compression seal for a gas turbine engine
EP3091188B1 (en) * 2015-05-08 2018-08-01 MTU Aero Engines GmbH Flow engine with a sealing arrangement

Also Published As

Publication number Publication date
US20220042419A1 (en) 2022-02-10
US11408292B2 (en) 2022-08-09
CN112771247B (en) 2023-09-15
FR3086329B1 (en) 2020-12-11
FR3086329A1 (en) 2020-03-27
CN112771247A (en) 2021-05-07
WO2020065161A1 (en) 2020-04-02
EP3857028A1 (en) 2021-08-04

Similar Documents

Publication Publication Date Title
CA2931374C (en) Device for guiding synchronizing ring vanes with variable pitch angle of a turbine engine and method for assembling such a device
EP2937517B1 (en) Stator of an axial turbomachine and corresponding turbomachine
EP3207221B1 (en) Rotating assembly for turbomachine and turbomachine
EP2324207B1 (en) Fixed vane assembly for a turbine engine with a reduced weight, and a turbine engine including at least one such fixed vane assembly
EP3473806A1 (en) Turbine engine casing comprising a central portion projecting relative to two side portions in a joining region
EP1811131B1 (en) Set of fixed sectorised diffuser inserts for a turbomachine compressor
EP1703084B1 (en) Device for varying the cross-section of a turbine stator
EP0017534A1 (en) Exchangeable sealing for the stator segment of a turbomachine
FR2989724A1 (en) TURBINE STAGE FOR A TURBOMACHINE
EP3161263B1 (en) Drehbare vorrichtung einer turbomaschine
EP2673545B1 (en) Reduced pressure-drop pipe element
EP3597864B1 (en) Sealing assembly for a turbine rotor of a turbine engine and turbine of a turbine engine comprising such an assembly
FR2916826A1 (en) SEAL TRIM WITH ROCKY TAIL SYSTEM.
EP2039885B1 (en) Element for locking ring sectors on the casing of a turbomachine, comprising handling means
FR3020408A1 (en) ROTARY ASSEMBLY FOR TURBOMACHINE
CA2858797A1 (en) Turbomachine compressor guide vanes assembly
EP3857028B1 (en) Improved turbomachine stator
CA2898864A1 (en) Fixed diffuser vanes assembly for guiding flow through a turbomachine, comprising an internal platform with inbuilt reinforcements, and associated turbomachine and production method
FR2942638A1 (en) Angular sector for rectifier in compressor of e.g. turbojet engine, of airplane, has angular locking flange arranged coaxially around outer shell and including shoulder that is radially supported against outer shell
FR3070718A1 (en) RING SECTOR TURBINE ASSEMBLY
EP4165286B1 (en) Annular assembly for a turbomachine turbine
EP2060744B1 (en) Stage of a turbine or turbomachine compressor
FR3072122B1 (en) TURBOMACHINE WHEEL
EP0651139A1 (en) Turbomachine with means to control the tip clearance between rotor and stator
FR3080406A1 (en) IMPROVED TURBINE DISPENSER FOR TURBOMACHINE

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20210312

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20220524

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1508905

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220815

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019017889

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20220803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20221205

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20221103

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1508905

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20221203

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20221104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019017889

Country of ref document: DE

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20220930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220906

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

26N No opposition filed

Effective date: 20230504

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220930

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220906

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220930

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230823

Year of fee payment: 5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230822

Year of fee payment: 5

Ref country code: DE

Payment date: 20230822

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220803