EP3857028B1 - Verbesserte tubinenleitschaufel - Google Patents

Verbesserte tubinenleitschaufel Download PDF

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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
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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
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English (en)
French (fr)
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EP3857028A1 (de
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
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3857028A1 publication Critical patent/EP3857028A1/de
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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.

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

Claims (10)

  1. Leitschaufel für eine Turbine eines Strahltriebwerks, die sich um eine Achse (X) erstreckt, wobei die Leitschaufel eine Vielzahl von Sektoren (10) aufweist, die jeweils mindestens eine Schaufel (13) umfassen, die sich radial zwischen einer inneren Plattform (18) und einer äußeren Plattform (16) erstreckt, wobei die Leitschaufel mindestens zwei Dichtlamellen (12) aufweist, die jeweils einen Hauptabschnitt (120) aufweisen, der ausgelegt ist, um die Dichtigkeit zwischen der Leitschaufel und einem Element (1) des Strahltriebwerks abzusichern, das der Leitschaufel benachbart ist, und einen ersten gebogenen Abschnitt (121) im Verhältnis zum Hauptabschnitt (120), dadurch gekennzeichnet, dass der erste gebogene Abschnitt (121) mit einer äußeren Fläche mindestens einer Plattform (16, 18) im Kontakt ist, wobei jede Lamelle (12) an der mindestens einen Plattform (16, 18) durch ein Spannmittel (40) gehalten wird, das ausgelegt ist, um den ersten gebogenen Abschnitt (121) zwischen der äußeren Fläche der Plattform (16, 18) und dem Spannmittel (40) zu spannen.
  2. Leitschaufel nach Anspruch 1, aufweisend zwei Lamellen (12), die jeweils einen Halbring bilden, wobei das Spannmittel (40) um die Leitschaufel derart angeordnet ist, dass die zwei Lamellen (12) gegen die äußeren Flächen der Plattformen (16, 18) der Leitschaufeln gespannt werden.
  3. Leitschaufel nach Anspruch 1 oder 2, wobei der Hauptabschnitt (120) und der erste gebogene Abschnitt (121) jeder Lamelle (12) zwischen sich einen Winkel bilden, der zwischen 90° und 150° liegt.
  4. Leitschaufel nach einem der Ansprüche 1 bis 3, wobei die Lamellen (12) jeweils einen zweiten gebogenen Abschnitt (122) aufweisen, der sich ab dem ersten gebogenen Abschnitt (121) etwa senkrecht zu diesem erstreckt und mit einer radialen Wand (163) in Kontakt kommt, die sich radial aus der mindestens einen Plattform (16, 18) hervorstehend erstreckt.
  5. Leitschaufel nach einem der Ansprüche 1 bis 4, umfassend zwei umfangmäßig benachbarte Lamellen (12) um die Leitschaufel, die derart angeordnet sind, dass ein Umfangsende (120a) des Hauptabschnitts (120) einer Lamelle (12) über einem Umfangsende (120a) des Hauptabschnitts (120) der benachbarten Lamelle (12) liegt.
  6. Leitschaufel nach Anspruch 5, wobei sich das Umfangsende (120a) des Hauptabschnitts (120) einer Lamelle (12) und das Umfangsende (120a) des Hauptabschnitts (120) der benachbarten Lamelle (12) über eine Strecke überlagern, die zwischen 1 und 10 mm liegt.
  7. Leitschaufel nach einem der Ansprüche 1 bis 6, wobei das Spannmittel (40) mindestens eine Spannfläche aufweist, wobei die Spannfläche mit dem ersten gebogenen Abschnitt (121) im Kontakt ist.
  8. Leitschaufel nach einem der Ansprüche 1 bis 7, wobei das Spannmittel (40) ein Ring ist.
  9. Leitschaufel nach einem der Ansprüche 4 bis 8, aufweisend mindestens eine Lasche (170), die an der radialen Wand (163) befestigt und ausgelegt ist, um einen Druck auf eine Lamelle (12) auszuüben.
  10. Strahltriebwerk, aufweisend eine Leitschaufel nach einem der vorangehenden Ansprüche.
EP19787014.0A 2018-09-26 2019-09-06 Verbesserte tubinenleitschaufel Active EP3857028B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1858804A FR3086329B1 (fr) 2018-09-26 2018-09-26 Distributeur ameliore de turbomachine
PCT/FR2019/052057 WO2020065161A1 (fr) 2018-09-26 2019-09-06 Distributeur ameliore de turbomachine

Publications (2)

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

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EP19787014.0A Active EP3857028B1 (de) 2018-09-26 2019-09-06 Verbesserte tubinenleitschaufel

Country Status (5)

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US (1) US11408292B2 (de)
EP (1) EP3857028B1 (de)
CN (1) CN112771247B (de)
FR (1) FR3086329B1 (de)
WO (1) WO2020065161A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3112813B1 (fr) * 2020-07-24 2022-08-19 Safran Aircraft Engines Assemblage anti-cisaillement d’une lamelle et d’un pion

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FR2955145B1 (fr) 2010-01-14 2012-02-03 Snecma Distributeur de turbine haute pression d'un turboreacteur
US8985592B2 (en) * 2011-02-07 2015-03-24 Siemens Aktiengesellschaft System for sealing a gap between a transition and a turbine
JP6392342B2 (ja) * 2013-07-19 2018-09-19 ゼネラル・エレクトリック・カンパニイ インピンジメントバッフルを有するタービンノズル
US10077669B2 (en) * 2014-11-26 2018-09-18 United Technologies Corporation Non-metallic engine case inlet compression seal for a gas turbine engine
EP3091188B1 (de) * 2015-05-08 2018-08-01 MTU Aero Engines GmbH Strömungsmaschine mit einer dichtungseinrichtung

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

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