EP3906357B1 - Leitapparat, turbine mit einem solchen leitapparat und turbomaschine mit einer solchen turbine - Google Patents

Leitapparat, turbine mit einem solchen leitapparat und turbomaschine mit einer solchen turbine Download PDF

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Publication number
EP3906357B1
EP3906357B1 EP19848997.3A EP19848997A EP3906357B1 EP 3906357 B1 EP3906357 B1 EP 3906357B1 EP 19848997 A EP19848997 A EP 19848997A EP 3906357 B1 EP3906357 B1 EP 3906357B1
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EP
European Patent Office
Prior art keywords
nozzle
sector
angular
foot
turbine
Prior art date
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Active
Application number
EP19848997.3A
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English (en)
French (fr)
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EP3906357A1 (de
Inventor
Coralie Cinthia Guerard
Hamza Guessine
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3906357A1 publication Critical patent/EP3906357A1/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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/33—Retaining components in desired mutual position with a bayonet coupling

Definitions

  • the present invention relates to a distributor for a low or high pressure turbine, a low or high pressure turbine comprising this distributor and a turbomachine, such as a turbojet or an airplane turboprop, comprising the aforementioned turbine.
  • Some turbomachines include a low pressure turbine and a high pressure turbine, which recover part of the energy released by the combustion of fuel to drive respectively a low pressure compressor and a high pressure compressor, located at the inlet of turbomachine air.
  • a low pressure turbine 1 with several stages 10, each stage 10 comprising successively a distributor 2 and a rotor wheel 3, from upstream to downstream with respect to the direction of flow of the air in the turbine (arrow V: i.e. from left to right on the figure 1 ). All the rotors are fixed on a shaft not shown in the figures and driven simultaneously in rotation.
  • the low pressure turbine 1 has a longitudinal axis X-X'.
  • Each distributor 2 is sectorized, that is to say formed of several angular sectors 20 of distributor, arranged circumferentially end to end and assembled.
  • Each angular sector of distributor 20 comprises two platforms in portion of an arc of circle, arranged coaxially one inside the other and interconnected by radial or substantially radial blades 201. These platforms delimit between them the annular flow path of the gases in the turbine 1.
  • the external platform 202 comprises hooking means on an external casing 100 of the turbine 1.
  • the internal platform 203 extends towards the inside of the turbine by a radial foot 204 which ends in a base 205.
  • This base 205 carries on its radially inner face, elements made of abradable material 206.
  • This abradable material is in the form of a honeycomb structure.
  • the elements made of abradable material 206 cooperate with annular wipers 30 carried by the neighboring rotor 3, to form seals of the “labyrinth seal” type. Indeed, in operation and under the effect of heat, the wipers 30 and the internal platform 203 expanding and approaching, the wipers 30 dig grooves in the abradable material 206. There thus exists between the grooves and the wipers, a small game that constitutes this maze joint. This clearance induces the performance of the stream of hot air flowing through the turbine.
  • the honeycomb 206 is brazed onto the base 205 of each angular sector 20 of the distributor, then is machined again.
  • this material is machined by spark erosion (known by the acronym EDM for “Electrical Discharge Machining” ) , which is an expensive technique and also requires specific and expensive controls.
  • each sector 20 has sealing slots 207, which open onto each of the end faces of a sector 20 intended to come into contact with the end faces of the adjacent distributor sector 20.
  • An inter-sector sealing tab (not shown in the figures) is engaged in each sealing slot 207, so as to overlap the space existing between two neighboring distributor sectors 20 and thus to stop or limit leaks. inter-sector air.
  • the production and manufacture of the sealing slots 207 and the mounting of the inter-sector sealing tabs are very expensive and time-consuming.
  • the slots 207 are also difficult to size and there is a significant risk that the sealing tabs will be dislodged from the sealing slots 207 and get lost in the air stream, resulting in air leaks and possible impacts on other parts of the turbine.
  • a distributor for a turbine comprising several angular sectors of distributors, each angular sector comprising two respectively internal and external sectors of platforms, in the shape of an arc of a circle, coaxial, interconnected by several radial or substantially radial blades.
  • Each internal platform sector is integral with a radially internal foot.
  • This distributor also comprises an annular ferrule on which said angular distributor sectors are fixed circumferentially end to end, this ferrule comprising a cylindrical ring whose radially inner face bears an abradable material.
  • the object of the invention is to propose a turbomachine distributor which solves the aforementioned drawbacks of the state of the art.
  • the object of the invention is to provide a turbomachine distributor which is simple and less expensive to produce and to assemble, while reducing air leaks in the vein.
  • Another object is to simplify the maintenance of the distributor.
  • the invention relates to a distributor for a turbine, comprising several angular sectors of distributors, each angular sector comprising two respectively internal and external sectors of platforms, in the form of an arc of a circle, coaxial, interconnected by several radial or substantially radial blades, each internal platform sector being integral with a radially internal foot, this distributor comprising an annular shroud on which said angular distributor sectors are fixed circumferentially end to end, this shroud comprising a cylindrical ring whose the radially inner face carries an abradable material.
  • the radially internal foot of each internal platform sector comprises a tongue, which extends radially inward from said foot, and which extends circumferentially over part of the length of said foot
  • the radially outer face of said cylindrical ring carries an outer radial wing, provided with a plurality of L-shaped lugs, one of the so-called “fixing” legs of which is integral with the outer radial wing and extends perpendicularly to a radius of the ring and parallel to the longitudinal axis X1-X' 1 of said ring and whose other branch, called “retaining”, extends opposite this external radial wing and at a short distance from it, so as to provide with it a slot for receiving said tongue of each angular sector of the distributor and this slot is open at one of its ends longitudinal to allow the engagement of said tongue, so as to ensure the fixing by dog clutching of said ferrule on each angular sector of the distributor.
  • the invention also relates to a turbomachine turbine comprising the aforementioned distributor and a turbomachine, such as a turbojet or an airplane turboprop, which comprises the aforementioned turbine.
  • the distributor according to the invention is referenced 4 and comprises an annular shell 5, on which are fixed several angular distributor sectors 6. Only part of the distributor 4 is visible on the figure 9 .
  • the annular shell 5 will now be described in more detail in connection with the figures 2 to 4 . It extends over 360° and has a longitudinal axis X1-X'1.
  • the annular shell 5 comprises a cylindrical ring 50 (or tube) of small width relative to its diameter, of small thickness and of longitudinal axis X1-X'1.
  • This ring 50 has a radially inner face 51 and a radially outer face 52.
  • the inner face 51 carries an abradable material 53 in one or more elements.
  • This abradable material 53 is preferably a honeycomb structure. It is brazed onto the ring 50 and resumed machining as previously described for the abradable material 206.
  • This abradable material 53 is also cylindrical.
  • the outer face 52 of the ring 50 comprises several first mechanical fixing members, distributed around its periphery and intended to cooperate with second complementary mechanical fixing members, carried by each of the angular sectors 6.
  • these mechanical fasteners are of the "clutch” type and allow coupling of the ferrule 5 and the distributor sectors 6 by the engagement of tabs in the slots for receiving these tabs.
  • the shroud 5 is provided with a radial wing 54, which extends radially outwards, from the outer face 52 of the ring 50.
  • This wing 54 is annular and extends over the entire periphery of the ring 50. It has a rear face 541 and an opposite front face 542.
  • the rear face 541 is preferably oriented downstream of the turbine.
  • a plurality of L-shaped tabs 55 are integral with the wing 54 and are uniformly distributed over the entire circumference of the latter.
  • Each leg 55 is also curved and has the general shape of an arc of a circle, the circle of which is coaxial with the ring 50 but with a radius greater than the radius of the ring 50.
  • the leg 55 matches the shape of the ring 50.
  • Each L-shaped leg 55 has a short branch 551, called the “fixing branch” and a long branch 552, called the “retaining branch”.
  • the fixing arm 551 extends perpendicular to a radius of the ring 50 and parallel to the longitudinal axis X1-X'1 of said ring.
  • the retaining branch 552 extends circumferentially and at a short distance from the rear face 541 of the wing 54, so as to define therewith a slot 553.
  • the long branch 552 has a front face 554 which extends opposite and parallel to the rear face 541 of the wing 54.
  • Part of the branch 551 constitutes the bottom 555 of the slot 553.
  • the slot 553 is open opposite the bottom 555, between the free end of the long branch 552 and the wing 54.
  • the long arm 552 has at its free end a lug 556 (see figure 4 ), which protrudes from the front face 554, in the direction of the rear face 541 of the wing 54, so as to only partially close the slot 555.
  • Branch 552 is advantageously slightly flexible.
  • the ring 50 can optionally be split, (see the longitudinal slot 500). This gives it a certain flexibility and facilitates the assembly of the distributor 4.
  • the different parts 50, 54 and 55 of the ferrule 5 are preferentially in one piece (made in one piece).
  • the ferrule 5 can be manufactured for example by machining or by additive manufacturing.
  • the ferrule 5 is preferably made of metal.
  • This sector 6 comprises, in a conventional manner, two angular sectors of platforms in an arc of a circle, coaxial, namely an external platform sector 61 and an internal platform sector 62, interconnected by several blades 63 radial or substantially radial.
  • the different angular sectors 6 are assembled around the shroud 5, end to end circumferentially, so that the different angular sectors of the external platform 61 together form the external platform of the distributor 4 and that the different angular sectors of the platform internal form 62 together form the internal platform of the dispenser 4.
  • the angular sector of the internal platform 62 is integral with a foot 621, called “internal radial foot", because it extends radially from the internal face of the said internal platform sector, in the direction from inside the dispenser 4.
  • the internal radial foot 621 is curved, seen from the front. It is extended radially inwards by an internal radial tab 622, also curved in front view.
  • the tongue 622 is centered in length with respect to the internal radial foot 621, so as to avoid the cantilever.
  • the length of the tongue 622 is preferably reduced to what is necessary for it to absorb the forces.
  • the tongue 622 has a tangential length L1, equal to approximately one third of the tangential length L2 of the foot 621.
  • the foot 621 supports a single tab 622.
  • the foot 621 supports a single tab 622.
  • the tongue 622 is thinner than the foot 621, so that it can form with this foot 621, i.e. a shoulder 623 which opens onto the front face 6211 of the foot 621 (see figure 7 ), or a shoulder 624 which opens onto the rear face 6212 of the foot 621 (see figure 8 ).
  • one or more sealing plates 7 can be fixed on the different angular sectors of the distributor 6.
  • the sheet 7 is formed of a profile slightly curved in an arc of a circle, in a circle whose radius is coaxial with the circle of the internal platform 62 in an arc of a circle, so as to match the shape of this platform.
  • the sheet 7 has a substantially L-shaped cross-section, with a fixing flank 71 and a protective flank 72.
  • the fixing flank 71 is intended to be fixed on the foot 621, for example by brazing or welding, this brazing or this welding being able to be carried out punctually or over the entire length of the sheet.
  • Each flank 71, 72 may optionally have folds, which define different sides, so as to adapt to the different shapes of feet 621, as can be seen for example on the figures 7 and 8 .
  • the sheet 7 provides both a sealing role by limiting the inter-sector leaks of the distributor 6 and a role of thermal protection with respect to the shroud 5, the abradable material 53 and the other elements of the low pressure turbine which are below this plate.
  • the sheet 8 is arcuate as is the protective sheet 7. It also has a substantially L-shaped cross-section with a fixing flank (not visible in the figure) intended to be fixed by welding or brazing on the external face 52 of the ferrule 50 and a protective flank 81 which extends substantially parallel to the feet 621.
  • the sheet 8 can be divided into sectors or extend over 360° and may or may not have scallops 810. Its role is to protect the shroud 5 and to direct the flow of hot air towards the blades. 63.
  • Each angular sector 6 is mounted on the shroud 5 so that its tab 622 is introduced laterally through the open end of the slot 553 then moved in the anti-clockwise direction, that is to say towards the left on the picture 3 .
  • the bottom 555 of the slot 553 acts as an anti-rotation stop.
  • the rear 541 and front 554 faces constitute bearing faces for the tongue 622 and limit its axial displacement and therefore the axial displacement of the corresponding angular sector 6.
  • the tabs 622 are preferably inserted into the slots 553, so that the shoulders 623 or 624 do not come into contact respectively with the wing 54 or the branch 552, which makes it possible to leave a slight radial clearance j1, respectively j2, between the two, and allows the expansion of the various components.
  • FIG. 6 represents an angular distributor sector 6 whose tab is inserted into the slot of the dog clutch carried by the ferrule 5.
  • the lug 556 makes it possible to prevent the disengagement of the tongue 622, the elasticity of the branch 552 being sufficient to allow the introduction of the tongue into the slot.
  • the various angular sectors 6 are all positioned on the outer casing of the turbine (see the casing 100 of the figure 1 ). Then, the ferrule 5 is brought closer to the tabs 622 so that each tab 622 is in front of the entrance to a slot 553 and then the ferrule 5 is rotated to the right of the picture 3 , to simultaneously engage all the tabs 622 in the slots 553.
  • the shroud 5 is mounted in the turbine so that its axis X1 -X'1 coincides with the axis X, X' of the turbine.
  • the invention has the following advantages:
  • the ferrule 5 is cylindrical in shape and with a simple claw fixing system. Its manufacture is therefore inexpensive, especially with new manufacturing processes, for example additive manufacturing.
  • the abradable material fixed 53 to the ferrule 5 is now separated from the sectors 6 of the distributor.
  • the repairs of the ferrule 5 or of the distributor sectors 6 are therefore independent of each other, which can simplify maintenance operations.
  • the invention also allows an overall mass saving on the whole of the distributor 4, because the ferrule 5 has a thickness less than that of the base of an internal platform on a conventional angular sector.
  • the manufacturing cost in particular the foundry cost for manufacturing the distributor, is also reduced, since there is less material and less areas to control. It is no longer necessary to braze and machine the abradable material on each distributor sector. In addition, it is no longer necessary to make slots on the internal platform 62, which leads to a reduction in costs and simplifies manufacture.

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

Claims (9)

  1. Leitapparat (4) für eine Turbine, der mehrere Leitapparat-Winkelsektoren (6) umfasst, wobei jeder Winkelsektor (6) zwei kreisbogenförmige Plattformsektoren, einen inneren (62) beziehungsweise einen äußeren (61), umfasst, die koaxial und durch mehrere radiale oder im Wesentlichen radiale Schaufeln (63) miteinander verbunden sind, wobei jeder innere Plattformsektor (62) fest mit einem radial inneren Fuß (621) verbunden ist, wobei dieser Leitapparat (4) eine ringförmige Hülse (5) umfasst, an der die Leitapparat-Winkelsektoren (6) in Umfangsrichtung aneinandergefügt befestigt sind, wobei diese Hülse (5) einen zylindrischen Ring (50) umfasst, dessen radial innere Seite (51) ein Abriebmaterial (53) trägt, dadurch gekennzeichnet, dass dieser radial innere Fuß (621) von jedem inneren Plattformsektor (62) eine Lasche (622) umfasst, die sich von dem Fuß (621) radial nach innen erstreckt und die sich in Umfangsrichtung über einen Teil der Länge des Fußes erstreckt, dadurch dass die radial äußere Seite (52) des zylindrischen Rings (50) einen äußeren radialen Flügel (54) trägt, der mit einer Vielzahl von L-förmigen Laschen (55) versehen ist, von denen einer der Schenkel (551), der "Befestigungsschenkel" genannt wird, fest mit dem äußeren radialen Flügel (54) verbunden ist und sich senkrecht zu einem Radius des Rings (50) und parallel zur Längsachse X1-X'1 des Rings (50) erstreckt, und von denen der andere Schenkel (552), der "Halteschenkel" genannt wird, sich diesem äußeren radialen Flügel (54) gegenüberstehend und in geringem Abstand davon erstreckt, derart dass damit ein Schlitz (553) zur Aufnahme der Lasche (622) von jedem Leitapparat-Winkelsektor (6) vorgesehen ist, und dadurch, dass dieser Schlitz (553) an einem seiner Längsenden offen ist, um den Eingriff der Lasche (622) zu ermöglichen, derart dass die Befestigung des Mantels (5) an jedem Leitapparat-Winkelsektor (6) durch Klauenkupplung sichergestellt wird.
  2. Leitapparat (4) nach Anspruch 1, dadurch gekennzeichnet, dass die Lasche (622) des radial inneren Fußes (621) sich in Umfangsrichtung über ein Drittel der Länge des Fußes (621) erstreckt.
  3. Leitapparat (4) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Lasche (622) sich in Umfangsrichtung in der Mitte des radial inneren Fußes (621) von jedem inneren Plattformsektor (62) erstreckt.
  4. Leitapparat (4) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Ende des Halteschenkels (552) mit einem Vorsprung (556) versehen ist, der in Richtung des äußeren radialen Flügels (54) hervorsteht, derart dass die Lasche (622) in Umfangsrichtung zurückgehalten wird, wenn diese in dem Aufnahmeschlitz (553) der Lasche in Eingriff ist.
  5. Leitapparat (4) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Halteschenkel (552) und der äußere radiale Flügel (54) durch einen Stift, eine Niete (91) und/oder eine Schweißung (90) verbunden sind.
  6. Leitapparat (4) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass er mindestens ein Dichtungsblech (7) aus mindestens einem Segment mit L- oder im Wesentlichen L-förmigem Querschnitt umfasst, das an dem radial inneren Fuß (621) eines Leitapparat-Winkelsektors (6) befestigt ist, derart dass es sich zumindest dem Schnitt zwischen zwei benachbarten Leitapparat-Winkelsektoren gegenüberstehend erstreckt.
  7. Leitapparat (4) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass er mindestens ein Hitzeschutzblech (8) aus mindestens einem Segment mit L- oder im Wesentlichen L-förmigem Querschnitt umfasst, das an dem zylindrischen Ring (50) des Mantels (5) befestigt ist.
  8. Turbomaschinenturbine, dadurch gekennzeichnet, dass sie mindestens einen Leitapparat (4) nach einem der vorhergehenden Ansprüche umfasst.
  9. Turbomaschine, wie beispielsweise ein Turbostrahltriebwerk oder ein Flugzeugpropellerturbinen-Luftstrahltriebwerk, dadurch gekennzeichnet, dass sie eine Turbine nach Anspruch 8 umfasst.
EP19848997.3A 2018-12-31 2019-12-30 Leitapparat, turbine mit einem solchen leitapparat und turbomaschine mit einer solchen turbine Active EP3906357B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1874402A FR3091311B1 (fr) 2018-12-31 2018-12-31 Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine.
PCT/FR2019/053317 WO2020141284A1 (fr) 2018-12-31 2019-12-30 Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine

Publications (2)

Publication Number Publication Date
EP3906357A1 EP3906357A1 (de) 2021-11-10
EP3906357B1 true EP3906357B1 (de) 2023-03-29

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EP19848997.3A Active EP3906357B1 (de) 2018-12-31 2019-12-30 Leitapparat, turbine mit einem solchen leitapparat und turbomaschine mit einer solchen turbine

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US (1) US11408295B2 (de)
EP (1) EP3906357B1 (de)
CN (1) CN113366191B (de)
FR (1) FR3091311B1 (de)
WO (1) WO2020141284A1 (de)

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US20220074312A1 (en) 2022-03-10
EP3906357A1 (de) 2021-11-10
CN113366191A (zh) 2021-09-07
US11408295B2 (en) 2022-08-09
FR3091311B1 (fr) 2021-04-09
CN113366191B (zh) 2023-03-28
WO2020141284A1 (fr) 2020-07-09
FR3091311A1 (fr) 2020-07-03

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