EP1840331A1 - Blade and cooling jacket assembly, turbomachine nozzle comprising the assembly, turbomachine, method of installing and repairing the assembly - Google Patents

Blade and cooling jacket assembly, turbomachine nozzle comprising the assembly, turbomachine, method of installing and repairing the assembly Download PDF

Info

Publication number
EP1840331A1
EP1840331A1 EP07290365A EP07290365A EP1840331A1 EP 1840331 A1 EP1840331 A1 EP 1840331A1 EP 07290365 A EP07290365 A EP 07290365A EP 07290365 A EP07290365 A EP 07290365A EP 1840331 A1 EP1840331 A1 EP 1840331A1
Authority
EP
European Patent Office
Prior art keywords
flange
blade
opening
liner
jacket
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.)
Granted
Application number
EP07290365A
Other languages
German (de)
French (fr)
Other versions
EP1840331B1 (en
Inventor
Alexandre Dervaux
Olivier Jean Daniel Baumas
Jean-Luc Bacha
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1840331A1 publication Critical patent/EP1840331A1/en
Application granted granted Critical
Publication of EP1840331B1 publication Critical patent/EP1840331B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the invention relates to a set of a blade and a cooling jacket of the blade, in a distributor of a turbomachine.
  • a turbomachine comprises rotor stages - compressor and / or turbine - separated by distributors.
  • the latter comprise a plurality of vanes, intended to guide the flow of gas.
  • the vanes extend in the gas vein between an outer shell and an inner shell. Due to the temperature of the gases flowing through them, in particular in the distributors separating the turbine stages, the vanes are subjected to very severe operating conditions; it is therefore necessary to cool them, usually by forced convection or by air impact, inside the blades.
  • multi-perforated longitudinal liners can be used. These jackets are generally made of a hot-resistant alloy, for example based on Chromium (Cr), Cobalt (Co) and Nickel (Ni).
  • Cr Chromium
  • Co Cobalt
  • Ni Nickel
  • Such a shirt is slid longitudinally into the cavity of a blade. It is supplied with cooling air at the outer shell. Due to the pressure difference between the inner cavity of the liner and the cavity between the liner and the blade, a portion of the air is projected, via the perforations of the liner, against the inner wall of the liner. dawn, thus ensuring its cooling. This air is then evacuated along the trailing edge of the blade by calibrated perforations in the gas vein. The remainder of the air is discharged through the inner shroud to other parts of the engine to be cooled, such as the turbine disk or bearings.
  • the dawn cavity provides two openings in the inner and outer platforms.
  • the liner is generally attached externally to the wall of the outer opening by soldering or welding, for example. This gives a kind of brazed slide connection.
  • the liner is further guided, at its other end portion, in the inner opening, whose wall slid form for this purpose and which makes it possible to compensate for the differential expansions between the liner and the blade.
  • the jacket comprises, on its external side, a flange, brazed on the dispenser.
  • a collared shirt is known from the document US 2002/0028133 . Compared to the shirts whose outer portion is brazed at a slide, a collarless shirt presents various advantages: it allows a simple mounting of the liner in the blade, with a determined radial positioning, and the brazing of the collar on the distributor is easy to implement and can be visually controlled.
  • Such a connection can be obtained by brazing.
  • brazing can be visually controlled on the flange, there is a risk of incomplete or failed brazing, leaving room for a possible air leak.
  • the present invention aims to provide an assembly of a blade and a cooling collar jacket of the blade in which the sealing of the fastener at the collar is provided.
  • the invention relates to a set of a blade and a cooling jacket of the blade, here in a distributor of a turbomachine, the blade having a central cavity, with at least a first opening , in which the liner extends, the liner comprising a flange fixed to the rim of the opening, characterized in that it comprises, at proximity of the flange, a peripheral interposition element between the wall of the jacket and the wall of the opening.
  • Such an interposition element creates a pressure drop.
  • loss of load is meant not only a conventional pressure loss created by a narrowing of the passage section of a flow or a baffle, but also an pressure drop - infinite - created by a seal.
  • the applicant has also discovered that it was possible to greatly simplify the assembly of the assembly. Indeed, the presence of an interposing element near the collar has a very effective effect on air leakage, so it is no longer necessary to perfectly braze the flange on the distributor. It is therefore possible to simply fix, by spot welding between the flange and the flange, the jacket on the blade, the leaks being avoided thanks to the interposing element. The time and cost savings are considerable in comparison with soldering over the entire periphery of the collar.
  • the interposer may serve a baffle and / or seal function.
  • the liner has an end portion, opposite the flange, which is guided in the second opening, the wall forming a slide for this purpose.
  • a clearance is provided between the jacket and the wall of the first opening.
  • the interposing element comprises a peripheral ring forming a baffle.
  • the interposing element comprises an elastic lamella.
  • the interposing element comprises a peripheral spring.
  • the invention also relates to a turbomachine distributor, comprising a plurality of assemblies as presented above, and a turbomachine comprising such a distributor.
  • Such a method has the advantage of its simplicity of implementation.
  • the invention is particularly applicable to an assembly whose jacket is open on both sides, the end portion opposite the flange being guided in an opening whose wall form slider, but it goes without saying that the The invention also applies to an assembly whose jacket is open only on the side of the collar, without necessarily being guided in a slide at its other end.
  • a distributor 1 comprises a plurality of stationary blades 2, forming a grid that straighten the flow of air passing through the gas stream of the engine.
  • the arrow in Figure 2 shows the flow direction of the gas, from upstream to downstream. This vein is delimited by an outer shell 3 and an inner shell 4, supporting the blades 2.
  • Each blade 2 is hollow and comprises a central cavity 5 within which is inserted a cooling jacket 6.
  • the leftmost cooling jacket 6 has been shown partially out of the cavity 5 of its blade 2 reception, to help understand the shape of the various elements. We will describe later a particular set of a dawn 2 and a jacket 6, it being understood that all the sets 2, 6 of the distributor 1 are similar in their structure.
  • the cavity 5 of the blade 2 has an external opening 7 and an internal opening 8, respectively in the outer and inner ring 3 4 of the distributor.
  • the jacket 6 is inserted through the external opening 7.
  • the jacket 6 comprises a hollow body 9 pierced, here on the upstream side, with a plurality of orifices 10 through which is projected, against the inner wall of the blade 2, air fed into the body 9 of the jacket 6 at a supply pipe 11 located near the outer opening 7 of the blade 2.
  • the inner wall of the blade 2 comprises, facing these orifices 10, a plurality of disruptive fins 11, for better cooling of the blade 2, in known manner.
  • the liner 6 further includes, on its outer surface, a plurality of bosses 12 - also shown schematically in Figure 2, although the latter is in section - whose function is to allow the positioning of the liner 2 in the cavity 5 of dawn 2.
  • the liner 6 comprises, on the external side, a flange 13.
  • This flange 13 is here obtained by forming the sheet forming the liner 6. It could also be reported on the latter.
  • the flange 13 is arranged to bear on the flange 14 formed by the distributor around the outer opening 7 formed by the cavity 5 of the blade 2.
  • the flange 13 is fixed to this rim 14, by soldering or welding, as will be detailed below.
  • the liner 6 On its internal side, the liner 6 comprises an end portion 15, in the extension of its body 6, inserted into the internal opening 8 formed by the blade 2, whose wall 8 'slider form to guide this portion of end 15, in known manner. Due to this freedom of movement, the differences in thermal expansion between the blade 2 and the liner 6 can be absorbed.
  • the assembly of the blade 2 and the liner 6 further includes, near the collar 13, an interposing element 16.
  • the function of the interposing element 16 is to create a pressure drop in the vicinity collar 13, to avoid or at least limit air leakage, in one direction or the other.
  • This interposing element 16 is peripheral around the jacket 6. It can be secured to either the jacket 6 or the distributor 1. It is located at close to the flange 13, that is to say that it is in an area in which its effects can be combined with those of the collar 13. In other words, the pressure losses generated by the interposition element 16 must be sufficient to prevent air leakage through the possible gaps between the flange 13 and the flange 14. In this case, the interposing element 16 is located, under the flange 13, at the wall 7 'of the external opening 7, which is extended by the flange 14 where the flange 13 is fixed.
  • the interposition element 16 is shown integral with the jacket 6, but It goes without saying that the skilled person will transpose without difficulty to an interposing element 16 secured to the wall 7 'of the outer opening 7 formed by the blade 2. In the three figures, the interposing element is designated by the same reference 16.
  • the interposition element 16 comprises, according to a first embodiment, a peripheral ring 16, or peripheral strip, fixed around the jacket 6, under the collar 13.
  • This ring 16, metallic is arranged to extend radially to a distance less than that separating the wall of the liner 16 from the wall 7 'of the outer opening 7 at this point, preferably flush with the latter.
  • radially is meant radially with respect to the overall axis of the liner, that is to say with respect to its longitudinal direction between the flange 13 and the end portion 15. The pressure loss thus created is sufficient to avoid or limit satisfactorily leaks between the flange 13 and the flange 14.
  • the interposing element forms a baffle, for the air flows, over the entire periphery of the jacket 6.
  • the interposing element 16 comprises, according to a second embodiment, a strip 16 peripheral, having a certain elasticity.
  • This lamella 16, metal has a radial dimension which may possibly be greater than the average distance between the wall of the liner 6 of the wall 7 'of the outer opening 7 at this location.
  • the sipe 16 bears on the wall portions 7 ' of opening 7 whose shirt 6 is closer and elastically bends outwards during the introduction of the liner 6, thus compensating for the play. It may also be provided that the dimension of the sipe 16 is such that the sipe comes into contact with the wall 7 'of the opening 7 over the entire periphery of the liner 6, thereby forming a seal.
  • the interposing element 16 can either perform the function of a baffle, or perform the function of a seal, or both, depending on whether it touches the wall 7 'of external opening 7 (seal function) or not touching it (baffle function). In all cases, it induces a loss of load at its level.
  • the sealing element 16 fills on certain portions - where the strip 16 is not in contact with the wall 7 'of the opening 7 - a baffle function and on others portions - where the blade 16 is in contact with the wall 7 'of the opening 7 - a seal function.
  • the interposing element 16 comprises, according to a third embodiment, a peripheral spring 16.
  • This spring 16 made of metal, comprises a lamella, the edges of which are fixed to the surface of the jacket 6 , the slat having a U-shaped section flared between the two fixed edges.
  • a spring member 16 compensates for a possible play at the outer opening 7 and may, depending on the areas of the jacket 6, perform a seal function and / or baffle, depending on whether the spring 16 is in contact or not with the wall 7 'of the opening 7.
  • interposing element has been presented according to three preferred embodiments, but it goes without saying that it is possible to envisage other structures, insofar as they extend between the wall of the jacket 6 and that of the opening 7 to create a pressure drop. We could also combine several elements of interposition and create a kind of labyrinth seal.
  • Such a mounting method is very fast and inexpensive. Indeed, instead of being soldered over its entire circumference, the collar 13 is simply welded in a plurality of points (usually referred to as "pointing").
  • the assembly is viable in operation because the weld points are sufficient to ensure the holding of the liner 6 on the blade 2, while the interposing element 16 seals or at least the limitation of leaks at the It should be noted that the point-welding fastening between the liner 6 and the flange 14 is sufficiently strong because the mechanical stresses at the level of a distributor liner are not too great.
  • the method of attachment can freely be adapted according to mechanical constraints on the one hand, time constraints and mounting cost on the other hand.
  • This freedom of adaptation is conferred by the presence of an interposing element between the wall of the liner 6 and the wall 7 'of the opening 7, which makes it possible to choose between brazing and spot welding.
  • the step of leveling the flange 13 may be implemented by machining, or preferably by ripping by an EDM machine (this type of routing is well known to those skilled in the art under its English acronym EDM, meaning "Electro-Discharge Machine”).
  • EDM Electro-Discharge Machine
  • the routing to be operated is very quickly implemented, because it suffices to break down the flange 13, which does not have, in general, a very large thickness. It is simple then, once the liner 6 removed from the central cavity 5 of the blade 2, to report a flange on the body 9 of the liner 6, for example by welding, to reform a new liner. The latter can then be inserted again in the central cavity 5 of the blade 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The assembly has an interposition element (16) near a collar (13) that is fixed on an flange (14) of an outer opening (7) arranged by a cavity (5) of a blade (2), where the element creates a loss of charge. The element is situated below the collar at the level of a wall (7`) of the opening, where the element is peripheral around a cooling jacket (6). The jacket has an end portion (15) opposite to the collar that is guided in another opening (8) whose wall (8`) forms a slide. Independent claims are also included for the following: (1) a method for mounting a cooling jacket in a hollow blade of a nozzle of a turbomachine (2) a method for repairing a blade and cooling jacket assembly.

Description

L'invention concerne un ensemble d'une aube et d'une chemise de refroidissement de l'aube, dans un distributeur d'une turbomachine.The invention relates to a set of a blade and a cooling jacket of the blade, in a distributor of a turbomachine.

Une turbomachine comporte des étages rotoriques - de compresseur et/ou de turbine - séparés par des distributeurs. Ces derniers comportent une pluralité d'aubes fixes, destinées à orienter les flux de gaz. Les aubes fixes s'étendent, dans la veine de gaz, entre une virole externe et une virole interne. En raison de la température des gaz qui les parcourent, en particulier dans les distributeurs séparant les étages de turbines, les aubes sont soumises à des conditions de fonctionnement très sévères ; il est donc nécessaire de les refroidir, en général par convection forcée ou bien par impact d'air, à l'intérieur des aubes.A turbomachine comprises rotor stages - compressor and / or turbine - separated by distributors. The latter comprise a plurality of vanes, intended to guide the flow of gas. The vanes extend in the gas vein between an outer shell and an inner shell. Due to the temperature of the gases flowing through them, in particular in the distributors separating the turbine stages, the vanes are subjected to very severe operating conditions; it is therefore necessary to cool them, usually by forced convection or by air impact, inside the blades.

Pour un refroidissement par impact d'air, on peut utiliser des chemises longitudinales multiperforées. Ces chemises sont généralement constituées d'un alliage résistant à chaud, par exemple à base de Chrome (Cr), Cobalt (Co) et Nickel (Ni). Une telle chemise est glissée longitudinalement dans la cavité d'une aube. Elle est alimentée en air de refroidissement au niveau de la virole externe. En raison de la différence de pression existant entre la cavité intérieure de la chemise et la cavité ménagée entre la chemise et l'aube, une partie de l'air est projetée, via les perforations de la chemise, contre la paroi interne de l'aube, assurant ainsi son refroidissement. Cet air est ensuite évacué, le long du bord de fuite de l'aube, par des perforations calibrées, dans la veine de gaz. Le reste de l'air est évacué à travers la virole interne vers d'autres parties du moteur à refroidir, telles que le disque de turbine ou les paliers.For air-impact cooling, multi-perforated longitudinal liners can be used. These jackets are generally made of a hot-resistant alloy, for example based on Chromium (Cr), Cobalt (Co) and Nickel (Ni). Such a shirt is slid longitudinally into the cavity of a blade. It is supplied with cooling air at the outer shell. Due to the pressure difference between the inner cavity of the liner and the cavity between the liner and the blade, a portion of the air is projected, via the perforations of the liner, against the inner wall of the liner. dawn, thus ensuring its cooling. This air is then evacuated along the trailing edge of the blade by calibrated perforations in the gas vein. The remainder of the air is discharged through the inner shroud to other parts of the engine to be cooled, such as the turbine disk or bearings.

La cavité de l'aube ménage deux ouvertures dans les plates-formes interne et externe. La chemise est généralement fixée, du côté externe, à la paroi de l'ouverture externe, par brasage ou soudage, par exemple. On obtient ainsi une sorte de liaison glissière brasée. La chemise est en outre guidée, au niveau de son autre portion d'extrémité, dans l'ouverture interne, dont la paroi forme glissière à cet effet et qui permet de compenser les dilatations différentielles entre la chemise et l'aube.The dawn cavity provides two openings in the inner and outer platforms. The liner is generally attached externally to the wall of the outer opening by soldering or welding, for example. This gives a kind of brazed slide connection. The liner is further guided, at its other end portion, in the inner opening, whose wall slid form for this purpose and which makes it possible to compensate for the differential expansions between the liner and the blade.

Selon une configuration avantageuse, la chemise comporte, de son côté externe, une collerette, brasée sur le distributeur. Une chemise à collerette est connue du document US 2002/0028133 . Par rapport aux chemises dont la portion externe est brasée au niveau d'une glissière, une chemise à collerette présente divers avantages : elle permet un montage simple de la chemise dans l'aube, avec un positionnement radial déterminé, et le brasage de la collerette sur le distributeur est facile à mettre en oeuvre et peut être contrôlé visuellement.According to an advantageous configuration, the jacket comprises, on its external side, a flange, brazed on the dispenser. A collared shirt is known from the document US 2002/0028133 . Compared to the shirts whose outer portion is brazed at a slide, a collarless shirt presents various advantages: it allows a simple mounting of the liner in the blade, with a determined radial positioning, and the brazing of the collar on the distributor is easy to implement and can be visually controlled.

Il est essentiel d'assurer une bonne étanchéité de la chemise sur l'aube, au niveau de la collerette. En effet, si ce n'est pas le cas, des fuites se produisent dans un sens ou dans l'autre et sont préjudiciables dans les deux cas. Ainsi, si la pression du côté externe de la virole externe du distributeur est supérieure à la pression dans la cavité ménagée entre la chemise et l'aube, de l'air va pénétrer dans cette dernière cavité ; il en résulte une augmentation de la pression à l'extérieur de la chemise, l'air ayant moins tendance à être projetée de l'intérieur de la chemise contre l'aube et le refroidissement de cette dernière étant donc moins bien assuré. A l'inverse, si la pression est plus importante dans la cavité entre la chemise et l'aube que du côté externe de la virole externe du distributeur, l'air, qui a servi à refroidir l'aube et s'est donc réchauffé, s'échappe de cette dernière cavité et détériore le refroidissement, assuré par ailleurs, du côté externe du distributeur. On pourrait pallier en partie les problèmes ci-dessus en augmentant le volume du flux de refroidissement à ce niveau ; toutefois, augmenter le volume à un endroit signifie le diminuer à un autre.It is essential to ensure a good tightness of the shirt on the dawn, at the level of the collar. Indeed, if this is not the case, leaks occur in one direction or the other and are detrimental in both cases. Thus, if the pressure on the outer side of the outer shell of the distributor is greater than the pressure in the cavity between the jacket and the blade, air will enter the latter cavity; This results in an increase in the pressure outside the jacket, the air being less likely to be projected from the inside of the shirt against the blade and the cooling of the latter is therefore less well ensured. Conversely, if the pressure is greater in the cavity between the jacket and the blade than on the outer side of the outer ring of the dispenser, the air, which was used to cool the dawn and therefore warmed , escapes from the latter cavity and deteriorates the cooling, provided elsewhere, the outer side of the dispenser. Some of the above problems could be overcome by increasing the volume of the cooling flow at this level; however, increasing the volume in one place means decreasing it to another.

Aucune de ces situations n'est satisfaisante et il est nécessaire d'avoir une liaison d'étanchéité satisfaisante au niveau de la collerette.None of these situations is satisfactory and it is necessary to have a satisfactory sealing connection at the flange.

Une telle liaison peut être obtenue par brasage. Toutefois, quand bien même un tel brasage peut être contrôlé visuellement sur la collerette, il existe un risque de brasage incomplet ou défaillant, laissant place à une éventuelle fuite d'air.Such a connection can be obtained by brazing. However, even if such brazing can be visually controlled on the flange, there is a risk of incomplete or failed brazing, leaving room for a possible air leak.

La présente invention vise à proposer un ensemble d'une aube et d'une chemise à collerette de refroidissement de l'aube dans lequel l'étanchéité de la fixation au niveau de la collerette est assurée.The present invention aims to provide an assembly of a blade and a cooling collar jacket of the blade in which the sealing of the fastener at the collar is provided.

C'est ainsi que l'invention concerne un ensemble d'une aube et d'une chemise de refroidissement de l'aube, ici dans un distributeur d'une turbomachine, l'aube comportant une cavité centrale, avec au moins une première ouverture, dans laquelle s'étend la chemise, la chemise comportant une collerette fixée sur le rebord de l'ouverture, caractérisé par le fait qu'il comporte, à proximité de la collerette, un élément d'interposition périphérique entre la paroi de la chemise et la paroi de l'ouverture.Thus, the invention relates to a set of a blade and a cooling jacket of the blade, here in a distributor of a turbomachine, the blade having a central cavity, with at least a first opening , in which the liner extends, the liner comprising a flange fixed to the rim of the opening, characterized in that it comprises, at proximity of the flange, a peripheral interposition element between the wall of the jacket and the wall of the opening.

Un tel élément d'interposition crée une perte de charge. Par perte de charge, on entend, non seulement, une perte de charge classique créée par un rétrécissement de la section de passage d'un écoulement ou par une chicane, mais encore, une perte de charge - infinie - créée par un joint étanche.Such an interposition element creates a pressure drop. By loss of load is meant not only a conventional pressure loss created by a narrowing of the passage section of a flow or a baffle, but also an pressure drop - infinite - created by a seal.

Grâce à la combinaison d'une collerette fixée au rebord et d'un élément d'interposition à proximité de cette collerette, l'air ne fuit pas - du moins d'éventuelles fuites ne sont pas significatives - et une éventuelle lacune de brasure n'est pas problématique. En effet, la collerette étant fixée, d'éventuelles fuites d'air ne pourraient se faire que par un jeu faible entre la collerette et le rebord. Or, de telles fuites par un faible interstice ne sont pas possibles en raison de l'élément d'interposition créant une perte de charge, ni dans un sens, ni dans l'autre.Thanks to the combination of a flange fixed to the rim and an interposition element near this collar, the air does not leak - at least any leaks are not significant - and a possible solder gap n is not problematic. Indeed, the flange being fixed, any air leakage could be done only by a small clearance between the flange and the flange. However, such leakage by a small gap is not possible because of the interposing element creating a pressure drop, neither in one direction nor in the other.

En résolvant un problème précis, la demanderesse a par ailleurs découvert qu'il était possible de simplifier de manière considérable le montage de l'ensemble. En effet, la présence d'un élément d'interposition à proximité de la collerette a un effet très efficace sur les fuites d'air, si bien qu'il n'est plus nécessaire de braser parfaitement la collerette sur le distributeur. Il est donc possible de simplement fixer, par un soudage par points entre la collerette et le rebord, la chemise sur l'aube, les fuites étant évitées grâce à l'élément d'interposition. Les gains de temps et de coût sont considérables en comparaison avec un brasage sur toute la périphérie de la collerette.In solving a specific problem, the applicant has also discovered that it was possible to greatly simplify the assembly of the assembly. Indeed, the presence of an interposing element near the collar has a very effective effect on air leakage, so it is no longer necessary to perfectly braze the flange on the distributor. It is therefore possible to simply fix, by spot welding between the flange and the flange, the jacket on the blade, the leaks being avoided thanks to the interposing element. The time and cost savings are considerable in comparison with soldering over the entire periphery of the collar.

L'élément d'interposition peut remplir une fonction de chicane et/ou de joint d'étanchéité.The interposer may serve a baffle and / or seal function.

De préférence, la cavité centrale ménageant une deuxième ouverture, la chemise comporte une portion d'extrémité, opposée à la collerette, qui est guidée dans la deuxième ouverture, dont la paroi forme glissière à cet effet.Preferably, the central cavity providing a second opening, the liner has an end portion, opposite the flange, which is guided in the second opening, the wall forming a slide for this purpose.

Avantageusement dans ce cas, un jeu est ménagé entre la chemise et la paroi de la première ouverture.Advantageously in this case, a clearance is provided between the jacket and the wall of the first opening.

Selon une première forme de réalisation particulière, l'élément d'interposition comporte un jonc périphérique formant une chicane.According to a first particular embodiment, the interposing element comprises a peripheral ring forming a baffle.

Selon une deuxième forme de réalisation particulière, l'élément d'interposition comporte une lamelle élastique.According to a second particular embodiment, the interposing element comprises an elastic lamella.

Selon une troisième forme de réalisation particulière, l'élément d'interposition comporte un ressort périphérique.According to a third particular embodiment, the interposing element comprises a peripheral spring.

L'invention concerne également un distributeur de turbomachine, comportant une pluralité d'ensembles tels que présentés ci-dessus, ainsi qu'une turbomachine comportant un tel distributeur.The invention also relates to a turbomachine distributor, comprising a plurality of assemblies as presented above, and a turbomachine comprising such a distributor.

L'invention concerne encore un procédé simplifié, que l'on a présenté ci-dessus, de montage d'une chemise de refroidissement dans une aube creuse de distributeur de turbomachine, pour former l'ensemble de l'invention, l'aube comportant une cavité centrale, avec au moins une première ouverture, et la chemise comportant une collerette, dans lequel :

  • on insère la chemise dans la cavité de l'aube, par la première ouverture, de manière à placer un élément d'interposition périphérique entre la paroi de la chemise et la paroi de la première ouverture et
  • on soude par points la collerette sur le rebord.
The invention also relates to a simplified method, which has been presented above, for mounting a cooling jacket in a hollow turbine engine nozzle blade, to form the assembly of the invention, the blade comprising a central cavity, with at least a first opening, and the sleeve having a flange, wherein:
  • inserting the liner into the blade cavity, through the first opening, so as to place a peripheral interposing element between the liner wall and the wall of the first opening and
  • the collar is dotted by points on the rim.

Grâce à l'utilisation de l'élément d'interposition de l'invention, l'utilisation d'une chemise à collerette peut être mise en oeuvre industriellement, en maîtrisant les risques de fuites d'air. Il est ainsi possible, en cas de réparation d'un distributeur et donc de l'ensemble de l'invention, pour démonter et remonter la chemise de l'aube, de mettre en oeuvre un procédé dans lequel :

  • on arase la collerette de la chemise, jusqu'au rebord, sans araser l'élément d'interposition,
  • on enlève la chemise du corps central de l'aube, par l'ouverture,
  • on rapporte une nouvelle collerette sur la chemise,
  • on insère la chemise, avec la nouvelle collerette, dans la cavité de l'aube, par la première ouverture, de manière à placer l'élément d'interposition périphérique entre la paroi de la chemise et la paroi de la première ouverture et
  • on fixe la collerette sur le rebord.
Thanks to the use of the interposing element of the invention, the use of a flanged jacket can be implemented industrially, by controlling the risk of air leakage. It is thus possible, in case of repair of a distributor and thus of the whole of the invention, to dismantle and reassemble the jacket of the blade, to implement a method in which:
  • the collar of the shirt is cut to the brim, without striking the interposition element,
  • we remove the shirt from the central body of the dawn, through the opening,
  • there is a new collar on the shirt,
  • the jacket, with the new flange, is inserted into the cavity of the blade, through the first opening, so as to place the peripheral interposing element between the wall of the jacket and the wall of the first opening and
  • we fix the collar on the rim.

Un tel procédé présente l'avantage de sa simplicité de mise en oeuvre.Such a method has the advantage of its simplicity of implementation.

On note que l'invention s'applique particulièrement bien à un ensemble dont la chemise est ouverte des deux côtés, la portion d'extrémité opposée à la collerette étant guidée dans une ouverture dont la paroi forme glissière, mais il va de soi que l'invention s'applique également à un ensemble dont la chemise n'est ouverte que du côté de la collerette, sans être nécessairement guidée dans une glissière à son autre extrémité.It is noted that the invention is particularly applicable to an assembly whose jacket is open on both sides, the end portion opposite the flange being guided in an opening whose wall form slider, but it goes without saying that the The invention also applies to an assembly whose jacket is open only on the side of the collar, without necessarily being guided in a slide at its other end.

L'invention sera mieux comprise à l'aide de la description suivante des formes de réalisation préférées de l'invention, en référence aux planches annexées, sur lesquelles :

  • la figure 1 représente une vue en perspective schématique d'une portion du distributeur de l'invention ;
  • la figure 2 représente une vue en coupe schématique de l'ensemble de l'invention ;
  • la figure 3 représente une vue en coupe schématique de l'élément d'interposition selon une première forme de réalisation de l'ensemble de l'invention ;
  • la figure 4 représente une vue en coupe schématique de l'élément d'interposition selon une deuxième forme de réalisation de l'ensemble de l'invention et
  • la figure 5 représente une vue en coupe schématique de l'élément d'interposition selon une troisième forme de réalisation de l'ensemble de l'invention.
The invention will be better understood with the aid of the following description of the preferred embodiments of the invention, with reference to the attached plates, in which:
  • Figure 1 shows a schematic perspective view of a portion of the dispenser of the invention;
  • Figure 2 shows a schematic sectional view of the assembly of the invention;
  • FIG. 3 represents a schematic sectional view of the interposition element according to a first embodiment of the assembly of the invention;
  • FIG. 4 represents a schematic sectional view of the interposition element according to a second embodiment of the assembly of the invention and
  • Figure 5 shows a schematic sectional view of the interposer according to a third embodiment of the assembly of the invention.

En référence aux figures 1 et 2, un distributeur 1 comporte une pluralité d'aubes fixes 2, formant une grille redressant le flux d'air passant dans la veine de gaz du moteur. La flèche de la figure 2 représente le sens de circulation du gaz, de l'amont vers l'aval. Cette veine est délimitée par une virole externe 3 et une virole interne 4, supportant les aubes 2.With reference to FIGS. 1 and 2, a distributor 1 comprises a plurality of stationary blades 2, forming a grid that straighten the flow of air passing through the gas stream of the engine. The arrow in Figure 2 shows the flow direction of the gas, from upstream to downstream. This vein is delimited by an outer shell 3 and an inner shell 4, supporting the blades 2.

Chaque aube 2 est creuse et comporte une cavité centrale 5 au sein de laquelle est insérée une chemise de refroidissement 6. Sur la figure 1, la chemise de refroidissement 6 la plus à gauche a été représentée partiellement sortie de la cavité 5 de son aube 2 de réception, afin d'aider à la compréhension de la forme des divers éléments. On décrira par la suite un ensemble particulier d'une aube 2 et d'une chemise 6, étant entendu que tous les ensembles 2, 6 du distributeur 1 sont similaires dans leur structure.Each blade 2 is hollow and comprises a central cavity 5 within which is inserted a cooling jacket 6. In Figure 1, the leftmost cooling jacket 6 has been shown partially out of the cavity 5 of its blade 2 reception, to help understand the shape of the various elements. We will describe later a particular set of a dawn 2 and a jacket 6, it being understood that all the sets 2, 6 of the distributor 1 are similar in their structure.

La cavité 5 de l'aube 2 ménage une ouverture externe 7 et une ouverture interne 8, respectivement dans les viroles externe 3 et interne 4 du distributeur. Pour être montée dans l'aube 2, la chemise 6 est insérée par l'ouverture externe 7.The cavity 5 of the blade 2 has an external opening 7 and an internal opening 8, respectively in the outer and inner ring 3 4 of the distributor. To be mounted in the blade 2, the jacket 6 is inserted through the external opening 7.

La chemise 6 comporte un corps creux 9 percé, ici du côté amont, d'une pluralité d'orifices 10 par lesquels est projeté, contre la paroi interne de l'aube 2, de l'air alimenté dans le corps 9 de la chemise 6 au niveau d'un tuyau d'alimentation 11 situé à proximité de l'ouverture externe 7 de l'aube 2. En l'espèce, la paroi interne de l'aube 2 comporte, face à ces orifices 10, une pluralité d'ailettes 11 formant perturbateurs, pour un meilleur refroidissement de l'aube 2, de manière connue. La chemise 6 comporte par ailleurs, sur sa surface externe, une pluralité de bossages 12 - également représentés schématiquement sur la figure 2, bien que cette dernière soit en coupe - dont la fonction est de permettre le positionnement de la chemise 2 dans la cavité 5 de l'aube 2.The jacket 6 comprises a hollow body 9 pierced, here on the upstream side, with a plurality of orifices 10 through which is projected, against the inner wall of the blade 2, air fed into the body 9 of the jacket 6 at a supply pipe 11 located near the outer opening 7 of the blade 2. In this case, the inner wall of the blade 2 comprises, facing these orifices 10, a plurality of disruptive fins 11, for better cooling of the blade 2, in known manner. The liner 6 further includes, on its outer surface, a plurality of bosses 12 - also shown schematically in Figure 2, although the latter is in section - whose function is to allow the positioning of the liner 2 in the cavity 5 of dawn 2.

La chemise 6 comporte, du côté externe, une collerette 13. Cette collerette 13 est ici obtenue par formage de la tôle formant la chemise 6. Elle pourrait également être rapportée sur cette dernière. La collerette 13 est agencée pour venir en appui sur le rebord 14 formé par le distributeur autour de l'ouverture externe 7 ménagée par la cavité 5 de l'aube 2. La collerette 13 est fixée à ce rebord 14, par brasage ou soudage, comme on le détaillera plus loin.The liner 6 comprises, on the external side, a flange 13. This flange 13 is here obtained by forming the sheet forming the liner 6. It could also be reported on the latter. The flange 13 is arranged to bear on the flange 14 formed by the distributor around the outer opening 7 formed by the cavity 5 of the blade 2. The flange 13 is fixed to this rim 14, by soldering or welding, as will be detailed below.

De son côté interne, la chemise 6 comporte une portion d'extrémité 15, dans le prolongement de son corps 6, insérée dans l'ouverture interne 8 ménagée par l'aube 2, dont la paroi 8' forme glissière pour guider cette portion d'extrémité 15, de manière connue. Du fait de cette liberté de mouvement, les différences de dilatation thermique entre l'aube 2 et la chemise 6 peuvent être absorbées.On its internal side, the liner 6 comprises an end portion 15, in the extension of its body 6, inserted into the internal opening 8 formed by the blade 2, whose wall 8 'slider form to guide this portion of end 15, in known manner. Due to this freedom of movement, the differences in thermal expansion between the blade 2 and the liner 6 can be absorbed.

L'ensemble de l'aube 2 et de la chemise 6 comporte par ailleurs, à proximité de la collerette 13, un élément d'interposition 16. La fonction de l'élément d'interposition 16 est de créer une perte de charge à proximité de la collerette 13, pour éviter ou du moins limiter les fuites d'air, dans un sens ou dans l'autre. Cet élément d'interposition 16 est périphérique autour de la chemise 6. Il peut être solidaire, soit de la chemise 6, soit du distributeur 1. Il se situe à proximité de la collerette 13, c'est-à-dire qu'il se situe dans une zone dans laquelle ses effets peuvent être combinés à ceux de la collerette 13. Autrement dit, les pertes de charge générées par l'élément d'interposition 16 doivent être suffisantes pour éviter les fuites d'air par les éventuels interstices existant entre la collerette 13 et le rebord 14. En l'espèce, l'élément d'interposition 16 est situé, sous la collerette 13, au niveau de la paroi 7' de l'ouverture externe 7, qui se prolonge par le rebord 14 où est fixée la collerette 13.The assembly of the blade 2 and the liner 6 further includes, near the collar 13, an interposing element 16. The function of the interposing element 16 is to create a pressure drop in the vicinity collar 13, to avoid or at least limit air leakage, in one direction or the other. This interposing element 16 is peripheral around the jacket 6. It can be secured to either the jacket 6 or the distributor 1. It is located at close to the flange 13, that is to say that it is in an area in which its effects can be combined with those of the collar 13. In other words, the pressure losses generated by the interposition element 16 must be sufficient to prevent air leakage through the possible gaps between the flange 13 and the flange 14. In this case, the interposing element 16 is located, under the flange 13, at the wall 7 'of the external opening 7, which is extended by the flange 14 where the flange 13 is fixed.

Trois formes de réalisation particulières de l'élément d'interposition vont maintenant être décrites, en relation avec les figures 3 à 5. Dans ces trois formes de réalisation, l'élément d'interposition 16 est représenté solidaire de la chemise 6, mais il va de soi que l'homme du métier transposera sans difficultés à un élément d'interposition 16 solidaire de la paroi 7' de l'ouverture externe 7 ménagée par l'aube 2. Sur les trois figures, l'élément d'interposition est désigné par la même référence 16.Three particular embodiments of the interposition element will now be described, in relation to FIGS. 3 to 5. In these three embodiments, the interposition element 16 is shown integral with the jacket 6, but It goes without saying that the skilled person will transpose without difficulty to an interposing element 16 secured to the wall 7 'of the outer opening 7 formed by the blade 2. In the three figures, the interposing element is designated by the same reference 16.

En référence à la figure 3, l'élément d'interposition 16 comporte, selon une première forme de réalisation, un jonc 16 périphérique, ou lamelle périphérique, fixé autour de la chemise 6, sous la collerette 13. Ce jonc 16, métallique, est agencé pour s'étendre radialement sur une distance inférieure à celle séparant la paroi de la chemise 16 de la paroi 7' de l'ouverture externe 7 à cet endroit, de préférence affleurant avec cette dernière. Par radialement, on entend radialement par rapport à l'axe global de la chemise, c'est-à-dire par rapport à sa direction longitudinale entre la collerette 13 et la portion d'extrémité 15. La perte de charge ainsi créée est suffisante pour éviter ou limiter de manière satisfaisante les fuites entre la collerette 13 et le rebord 14. Dans cette forme de réalisation, l'élément d'interposition forme une chicane, pour les écoulements d'air, sur toute la périphérie de la chemise 6.With reference to FIG. 3, the interposition element 16 comprises, according to a first embodiment, a peripheral ring 16, or peripheral strip, fixed around the jacket 6, under the collar 13. This ring 16, metallic, is arranged to extend radially to a distance less than that separating the wall of the liner 16 from the wall 7 'of the outer opening 7 at this point, preferably flush with the latter. By radially, is meant radially with respect to the overall axis of the liner, that is to say with respect to its longitudinal direction between the flange 13 and the end portion 15. The pressure loss thus created is sufficient to avoid or limit satisfactorily leaks between the flange 13 and the flange 14. In this embodiment, the interposing element forms a baffle, for the air flows, over the entire periphery of the jacket 6.

En référence à la figure 4, l'élément d'interposition 16 comporte, selon une deuxième forme de réalisation, une lamelle 16 périphérique, présentant une certaine élasticité. Cette lamelle 16, métallique, présente une dimension radiale qui peut éventuellement être supérieure à la distance moyenne séparant la paroi de la chemise 6 de la paroi 7' de l'ouverture externe 7 à cet endroit. Lors de l'introduction de la chemise 6 dans l'ouverture 7, il n'est pas préjudiciable que la chemise 6 ne soit pas parfaitement centrée par rapport à l'ouverture 7. La lamelle 16 prend appui sur les portions de paroi 7' de l'ouverture 7 dont la chemise 6 est plus proche et se courbe élastiquement vers l'extérieur lors de l'introduction de la chemise 6, compensant ainsi le jeu. Il peut d'ailleurs être prévu que la dimension de la lamelle 16 soit telle que la lamelle entre en contact avec la paroi 7' de l'ouverture 7 sur l'ensemble de la périphérie de la chemise 6, formant ainsi un joint d'étanchéité.Referring to Figure 4, the interposing element 16 comprises, according to a second embodiment, a strip 16 peripheral, having a certain elasticity. This lamella 16, metal, has a radial dimension which may possibly be greater than the average distance between the wall of the liner 6 of the wall 7 'of the outer opening 7 at this location. When inserting the liner 6 in the opening 7, it is not detrimental that the liner 6 is not perfectly centered with respect to the opening 7. The sipe 16 bears on the wall portions 7 ' of opening 7 whose shirt 6 is closer and elastically bends outwards during the introduction of the liner 6, thus compensating for the play. It may also be provided that the dimension of the sipe 16 is such that the sipe comes into contact with the wall 7 'of the opening 7 over the entire periphery of the liner 6, thereby forming a seal.

Grâce à cette forme de réalisation, il est possible de ménager un jeu entre la chemise 6 et la paroi 7' de l'ouverture externe 7. Un tel jeu autorise un montage plus simple de la chemise 6. Lors de son introduction dans l'aube 2, la chemise 6 est guidée, au niveau de sa portion d'extrémité 15, dans la glissière 8 située du côté interne de l'aube 2. Ce guidage se fait librement car il n'est pas gêné par un défaut d'alignement de l'ouverture interne 8 et de l'ouverture externe 7, du fait de la présence d'un jeu au niveau de cette dernière. Un tel jeu n'est pas préjudiciable au montage car il est compensé par l'élasticité de la lamelle 16. Ainsi, la lamelle 16 peut passer dans l'ouverture 7 et remplir sa fonction de limitation des fuites. Grâce à la lamelle 16, la présence d'un jeu n'implique pas de fuites ; le jeu et les avantages qu'il implique sont donc autorisés par la présence de la lamelle 16.With this embodiment, it is possible to provide a clearance between the liner 6 and the wall 7 'of the outer opening 7. Such a game allows a simpler mounting of the liner 6. When introduced into the blade 2, the liner 6 is guided, at its end portion 15, in the slide 8 located on the inner side of the blade 2. This guidance is done freely because it is not hindered by a defect of alignment of the inner opening 8 and the outer opening 7, due to the presence of a game at the latter. Such a game is not detrimental to the assembly because it is compensated by the elasticity of the blade 16. Thus, the blade 16 can pass through the opening 7 and fulfill its function of limiting leaks. With the blade 16, the presence of a game does not involve leaks; the game and the advantages that it implies are therefore authorized by the presence of the slat 16.

Dans cette forme de réalisation, l'élément d'interposition 16 peut, soit remplir la fonction d'une chicane, soit remplir la fonction d'un joint d'étanchéité, soit les deux, selon qu'il touche la paroi 7' de l'ouverture externe 7 (fonction de joint) ou qu'il ne la touche pas (fonction de chicane). Dans tous les cas, il induit une perte de charge à son niveau. Lorsqu'il remplit les deux fonctions, l'élément d'étanchéité 16 remplit sur certaines portions - où la lamelle 16 n'est pas en contact avec la paroi 7' de l'ouverture 7 - une fonction de chicane et sur d'autres portions - où la lamelle 16 est en contact avec la paroi 7' de l'ouverture 7 - une fonction de joint d'étanchéité.In this embodiment, the interposing element 16 can either perform the function of a baffle, or perform the function of a seal, or both, depending on whether it touches the wall 7 'of external opening 7 (seal function) or not touching it (baffle function). In all cases, it induces a loss of load at its level. When it performs both functions, the sealing element 16 fills on certain portions - where the strip 16 is not in contact with the wall 7 'of the opening 7 - a baffle function and on others portions - where the blade 16 is in contact with the wall 7 'of the opening 7 - a seal function.

En référence à la figure 5, l'élément d'interposition 16 comporte, selon une troisième forme de réalisation, un ressort périphérique 16. Ce ressort 16, métallique, comporte une lamelle, dont les bordures sont fixées à la surface de la chemise 6, la lamelle présentant une section en forme de U évasé entre les deux bordures fixées. De même que précédemment, un tel élément formant ressort 16 permet de compenser un éventuel jeu au niveau de l'ouverture externe 7 et peut, selon les zones de la chemise 6, remplir une fonction de joint d'étanchéité et/ou de chicane, selon que le ressort 16 est en contact ou non avec la paroi 7' de l'ouverture 7.With reference to FIG. 5, the interposing element 16 comprises, according to a third embodiment, a peripheral spring 16. This spring 16, made of metal, comprises a lamella, the edges of which are fixed to the surface of the jacket 6 , the slat having a U-shaped section flared between the two fixed edges. As above, such a spring member 16 compensates for a possible play at the outer opening 7 and may, depending on the areas of the jacket 6, perform a seal function and / or baffle, depending on whether the spring 16 is in contact or not with the wall 7 'of the opening 7.

L'élément d'interposition a été présenté selon trois formes de réalisations préférées, mais il va de soi qu'il est possible d'envisager d'autres structures, dans la mesure où elles s'étendent entre la paroi de la chemise 6 et celle de l'ouverture 7 pour créer une perte de charge. On pourrait d'ailleurs combiner plusieurs éléments d'interposition et créer une sorte de joint labyrinthe.The interposing element has been presented according to three preferred embodiments, but it goes without saying that it is possible to envisage other structures, insofar as they extend between the wall of the jacket 6 and that of the opening 7 to create a pressure drop. We could also combine several elements of interposition and create a kind of labyrinth seal.

Grâce à l'élément d'interposition 16, les fuites d'air au niveau de la collerette 13 sont, si ce n'est complètement évitées, du moins largement limitées. La collerette 13 peut être fixée au rebord 14 par brasage. Dans un tel cas, une éventuelle lacune de matériau de brasure n'est pas rédhibitoire car l'élément d'interposition interdit ou limite les fuites. L'utilisation d'un élément d'interposition permet également la mise en oeuvre d'un procédé de montage particulier de la chemise 6 dans l'aube 2, dans lequel :

  • on insère la chemise 6 dans la cavité 5 de l'aube 2, par l'ouverture externe 7 et
  • on soude par points la collerette 13 sur le rebord 14.
Thanks to the interposition element 16, the air leaks at the flange 13 are, if not completely avoided, at least largely limited. The flange 13 can be fixed to the flange 14 by soldering. In such a case, a possible gap in solder material is not unacceptable because the interposing element prohibits or limits leaks. The use of an interposing element also makes it possible to implement a particular method of mounting the jacket 6 in the blade 2, in which:
  • the jacket 6 is inserted into the cavity 5 of the blade 2, through the external opening 7 and
  • the flange 13 is welded in points on the flange 14.

Un tel procédé de montage est très rapide et peu onéreux. En effet, au lieu d'être brasée sur toute sa circonférence, la collerette 13 est simplement soudée en une pluralité de points (on parle généralement de "pointage"). L'ensemble est viable en fonctionnement car les points de soudure sont suffisants pour assurer la tenue de la chemise 6 sur l'aube 2, tandis que l'élément d'interposition 16 assure l'étanchéité ou du moins la limitation des fuites au niveau de la collerette 13. On note que la fixation par soudage par points entre la chemise 6 et le rebord 14 est suffisamment résistante car les contraintes mécaniques au niveau d'une chemise de distributeur ne sont pas trop importantes.Such a mounting method is very fast and inexpensive. Indeed, instead of being soldered over its entire circumference, the collar 13 is simply welded in a plurality of points (usually referred to as "pointing"). The assembly is viable in operation because the weld points are sufficient to ensure the holding of the liner 6 on the blade 2, while the interposing element 16 seals or at least the limitation of leaks at the It should be noted that the point-welding fastening between the liner 6 and the flange 14 is sufficiently strong because the mechanical stresses at the level of a distributor liner are not too great.

Ainsi, le mode de fixation peut librement être adapté en fonction des contraintes mécaniques d'une part, des contraintes de temps et de coût de montage d'autre part. Cette liberté d'adaptation est conférée par la présence d'un élément d'interposition entre la paroi de la chemise 6 et la paroi 7' de l'ouverture 7, qui permet de choisir entre un brasage et un soudage par points.Thus, the method of attachment can freely be adapted according to mechanical constraints on the one hand, time constraints and mounting cost on the other hand. This freedom of adaptation is conferred by the presence of an interposing element between the wall of the liner 6 and the wall 7 'of the opening 7, which makes it possible to choose between brazing and spot welding.

En cas de réparation du distributeur 1, il est possible, pour chaque ensemble d'une aube 2 et d'une chemise 6, de mettre en oeuvre un procédé de réparation dans lequel :

  • on arase la collerette 13 de la chemise 6, jusqu'au rebord 14, sans araser l'élément d'interposition 16,
  • on enlève la chemise 6 du corps central 5 de l'aube 2, par l'ouverture 7,
  • on rapporte une nouvelle collerette sur la chemise 6,
  • on insère la chemise 6, avec la nouvelle collerette, dans la cavité 5 de l'aube 2, par l'ouverture externe 7, de manière à placer l'élément d'interposition 16 périphérique entre la paroi de la chemise 6 et la paroi 7' de l'ouverture 7 et
  • on fixe la collerette 13 sur le rebord 14.
In case of repair of the distributor 1, it is possible, for each set of a blade 2 and a jacket 6, to implement a repair method in which:
  • the flange 13 of the jacket 6 is flared to the flange 14, without striking the interposition element 16,
  • the liner 6 of the central body 5 of the blade 2 is removed through the opening 7,
  • we report a new collar on the shirt 6,
  • the liner 6, with the new flange, is inserted into the cavity 5 of the blade 2, through the external opening 7, so as to place the peripheral element 16 between the wall of the liner 6 and the wall 7 'of opening 7 and
  • the flange 13 is fixed on the flange 14.

L'étape d'arasement de la collerette 13 peut être mise en oeuvre par usinage, ou de préférence par défonçage par une machine à électro-érosion (ce type de défonçage est bien connu de l'homme du métier sous son acronyme anglais de défonçage EDM, signifiant "Electro-Discharge Machine"). Le défonçage à opérer est très rapidement mis en oeuvre, car il suffit de défoncer la collerette 13, qui ne présente pas, en général, une très grande épaisseur. Il est simple ensuite, une fois la chemise 6 enlevée de la cavité centrale 5 de l'aube 2, de rapporter une collerette sur le corps 9 de la chemise 6, par exemple par soudage, pour reformer une nouvelle chemise. Cette dernière peut alors être de nouveau insérée dans la cavité centrale 5 de l'aube 2.The step of leveling the flange 13 may be implemented by machining, or preferably by ripping by an EDM machine (this type of routing is well known to those skilled in the art under its English acronym EDM, meaning "Electro-Discharge Machine"). The routing to be operated is very quickly implemented, because it suffices to break down the flange 13, which does not have, in general, a very large thickness. It is simple then, once the liner 6 removed from the central cavity 5 of the blade 2, to report a flange on the body 9 of the liner 6, for example by welding, to reform a new liner. The latter can then be inserted again in the central cavity 5 of the blade 2.

Claims (12)

Ensemble d'une aube (2) et d'une chemise (6) de refroidissement de l'aube (2), l'aube (2) comportant une cavité centrale (5), avec au moins une première ouverture (7), dans laquelle s'étend la chemise (6), la chemise (6) comportant une collerette (13) fixée sur le rebord (14) de l'ouverture (7), caractérisé par le fait qu'il comporte, à proximité de la collerette (13), un élément d'interposition (16) périphérique entre la paroi de la chemise (6) et la paroi (7') de l'ouverture (7).Set of a blade (2) and a jacket (6) for cooling the blade (2), the blade (2) having a central cavity (5), with at least a first opening (7), in which the liner (6) extends, the liner (6) having a collar (13) fixed on the rim (14) of the opening (7), characterized in that it comprises, close to the flange (13), an interposing element (16) peripheral between the wall of the liner (6) and the wall (7 ') of the opening (7). Ensemble selon la revendication 1, dans lequel l'élément d'interposition (16) crée une perte de charge, en remplissant la fonction d'une chicane et/ou d'un joint d'étanchéité.An assembly according to claim 1, wherein the interposer (16) creates a pressure drop, fulfilling the function of a baffle and / or a seal. Ensemble selon l'une des revendications 1 ou 2, dans lequel, la cavité centrale (5) ménageant une deuxième ouverture (8), la chemise (6) comporte une portion d'extrémité (15), opposée à la collerette (13), qui est guidée dans la deuxième ouverture (8), dont la paroi (8') forme glissière à cet effet.Assembly according to one of claims 1 or 2, wherein, the central cavity (5) having a second opening (8), the liner (6) has an end portion (15), opposite the flange (13). , which is guided in the second opening (8), the wall (8 ') slider form for this purpose. Ensemble selon la revendication 3, dans lequel un jeu est ménagé entre la chemise (6) et la paroi (7') de la première ouverture (7).An assembly according to claim 3, wherein a clearance is provided between the liner (6) and the wall (7 ') of the first opening (7). Ensemble selon l'une des revendications 1 à 4, dans lequel l'élément d'interposition comporte un jonc périphérique (16) formant une chicane.Assembly according to one of claims 1 to 4, wherein the interposing element comprises a peripheral ring (16) forming a baffle. Ensemble selon l'une des revendications 1 à 4, dans lequel l'élément d'interposition comporte une lamelle élastique (16).Assembly according to one of claims 1 to 4, wherein the interposing element comprises an elastic strip (16). Ensemble selon l'une des revendications 1 à 4, dans lequel l'élément d'interposition comporte un ressort périphérique (16).Assembly according to one of claims 1 to 4, wherein the interposing element comprises a peripheral spring (16). Ensemble selon l'une des revendications 1 à 7, dans lequel la collerette (13) est fixée au rebord (14) par soudage par points.Assembly according to one of claims 1 to 7, wherein the flange (13) is fixed to the flange (14) by spot welding. Distributeur de turbomachine comportant une pluralité d'ensembles d'une aube (2) et d'une chemise (6) selon l'une des revendications 1 à 8.Turbomachine distributor comprising a plurality of sets of a blade (2) and a jacket (6) according to one of claims 1 to 8. Turbomachine, comportant un distributeur selon la revendication 9.Turbomachine, comprising a distributor according to claim 9. Procédé de montage d'une chemise de refroidissement (6) dans une aube (2) creuse de distributeur de turbomachine, pour former l'ensemble de l'une des revendications 1 à 8, l'aube (2) comportant une cavité centrale (5), avec au moins une première ouverture (7), et la chemise (6) comportant une collerette (13), dans lequel : - on insère la chemise (6) dans la cavité (5) de l'aube (2), par la première ouverture (7), de manière à placer un élément d'interposition (16) périphérique entre la paroi de la chemise (6) et la paroi (7') de la première ouverture (7) et - on soude par points la collerette (13) sur le rebord (14). Method for mounting a cooling jacket (6) in a hollow turbine engine nozzle blade (2), to form the assembly of one of Claims 1 to 8, the blade (2) comprising a central cavity ( 5), with at least a first opening (7), and the liner (6) having a flange (13), wherein: the jacket (6) is inserted into the cavity (5) of the blade (2), through the first opening (7), so as to place a peripheral interposition element (16) between the wall of the jacket ( 6) and the wall (7 ') of the first opening (7) and - The flange (13) is welded on the flange (14) by points. Procédé de réparation d'un ensemble selon l'une des revendications 1 à 8, dans lequel: - on arase la collerette (13) de la chemise (6), jusqu'au rebord (14), sans araser l'élément d'interposition (16), - on enlève la chemise (6) du corps central (5) de l'aube (2), par la première ouverture (7), - on rapporte une nouvelle collerette sur la chemise (6), - on insère la chemise (6), avec la nouvelle collerette (13), dans la cavité (5) de l'aube (2), par la première ouverture (7), de manière à placer l'élément d'interposition (16) périphérique entre la paroi de la chemise (6) et la paroi (7') de la première ouverture (7) et - on fixe la collerette (13) sur le rebord (14). A method of repairing an assembly according to one of claims 1 to 8, wherein: - the flange (13) of the liner (6) is flared to the flange (14) without striking the interposition element (16), the liner (6) of the central body (5) of the blade (2) is removed by the first opening (7), a new flange is reported on the jacket (6), the jacket (6), with the new flange (13), is inserted into the cavity (5) of the blade (2), through the first opening (7), so as to place the interposition element ( 16) between the wall of the liner (6) and the wall (7 ') of the first opening (7) and - Fixing the flange (13) on the flange (14).
EP07290365.1A 2006-03-29 2007-03-26 Turbomachine nozzle Active EP1840331B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0602716A FR2899271B1 (en) 2006-03-29 2006-03-29 DUSTBOARD AND COOLING SHIELD ASSEMBLY, TURBOMACHINE DISPENSER COMPRISING THE ASSEMBLY, TURBOMACHINE, METHOD OF ASSEMBLING AND REPAIRING THE ASSEMBLY

Publications (2)

Publication Number Publication Date
EP1840331A1 true EP1840331A1 (en) 2007-10-03
EP1840331B1 EP1840331B1 (en) 2017-05-31

Family

ID=37429322

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290365.1A Active EP1840331B1 (en) 2006-03-29 2007-03-26 Turbomachine nozzle

Country Status (7)

Country Link
US (1) US7819628B2 (en)
EP (1) EP1840331B1 (en)
JP (1) JP2007263115A (en)
CN (1) CN101122243B (en)
CA (1) CA2582638C (en)
FR (1) FR2899271B1 (en)
RU (1) RU2439334C2 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955145A1 (en) * 2010-01-14 2011-07-15 Snecma HIGH PRESSURE TURBINE DISPENSER OF A TURBOREACTOR
FR2976616A1 (en) * 2011-06-17 2012-12-21 Snecma Ventilation system for hollow blade of turbine nozzle for e.g. turbojet engine for airplane, has tubular sleeve, air intake casing and plate that are assembled with each other to form single-piece component before assembling in blade
EP2613004A3 (en) * 2012-01-09 2017-06-28 General Electric Company Turbine nozzle assembly methods
WO2023012421A1 (en) * 2021-08-05 2023-02-09 Safran Aircraft Engines Cooling jacket of a hollow blade of a distributor

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2919897B1 (en) * 2007-08-08 2014-08-22 Snecma TURBINE DISPENSER SECTOR
FR2970666B1 (en) 2011-01-24 2013-01-18 Snecma PROCESS FOR PERFORATING AT LEAST ONE WALL OF A COMBUSTION CHAMBER
EP2540969A1 (en) 2011-06-27 2013-01-02 Siemens Aktiengesellschaft Impingement cooling of turbine blades or vanes
US9011079B2 (en) * 2012-01-09 2015-04-21 General Electric Company Turbine nozzle compartmentalized cooling system
US20130223987A1 (en) * 2012-02-29 2013-08-29 Scott Stafford Turbine Nozzle Insert
US20140356155A1 (en) * 2013-06-03 2014-12-04 General Electric Company Nozzle Insert Rib Cap
US10822976B2 (en) * 2013-06-03 2020-11-03 General Electric Company Nozzle insert rib cap
EP3022394B1 (en) * 2013-07-19 2018-05-30 General Electric Company Turbine nozzle with impingement baffle
CN106255806B (en) * 2014-05-08 2019-05-31 西门子股份公司 Turbine assembly and corresponding operation method
EP2949872A1 (en) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine with a seal for separating working fluid and coolant fluid of the turbomachine and use of the turbomachine
EP3149311A2 (en) 2014-05-29 2017-04-05 General Electric Company Turbine engine and particle separators therefore
US11033845B2 (en) * 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
RU2581010C1 (en) * 2014-11-18 2016-04-10 Акционерное общество "Научно-производственный центр газотурбостроения "Салют" (АО "НПЦ газотурбостроения "Салют") Method of repair of control gear of guide vanes of turbine compressor of bypass gas turbine engine
US10450880B2 (en) * 2016-08-04 2019-10-22 United Technologies Corporation Air metering baffle assembly
DE102016216858A1 (en) * 2016-09-06 2018-03-08 Rolls-Royce Deutschland Ltd & Co Kg Blade for a turbomachine and method for assembling a blade for a turbomachine
US10677091B2 (en) * 2016-11-17 2020-06-09 Raytheon Technologies Corporation Airfoil with sealed baffle
US10577943B2 (en) 2017-05-11 2020-03-03 General Electric Company Turbine engine airfoil insert
DE102017208678A1 (en) 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Turbine blade with sheet metal insert
US10815806B2 (en) * 2017-06-05 2020-10-27 General Electric Company Engine component with insert
EP3421722A1 (en) * 2017-06-29 2019-01-02 Siemens Aktiengesellschaft Turbine assembly for impingement cooling and method of assembling
FR3074521B1 (en) 2017-12-06 2019-11-22 Safran Aircraft Engines TURBINE DISPENSER SECTOR FOR AN AIRCRAFT TURBOMACHINE
FR3076852B1 (en) * 2018-01-16 2020-01-31 Safran Aircraft Engines TURBOMACHINE RING
FR3094034B1 (en) 2019-03-20 2021-03-19 Safran Aircraft Engines VENTILATION TUBULAR SHIRT FOR A TURBOMACHINE DISTRIBUTOR
PL431184A1 (en) * 2019-09-17 2021-03-22 General Electric Company Polska Spółka Z Ograniczoną Odpowiedzialnością Turboshaft engine set
US11261748B2 (en) 2019-11-08 2022-03-01 Raytheon Technologies Corporation Vane with seal
US11174794B2 (en) * 2019-11-08 2021-11-16 Raytheon Technologies Corporation Vane with seal and retainer plate
US11156105B2 (en) * 2019-11-08 2021-10-26 Raytheon Technologies Corporation Vane with seal
CN112228905B (en) * 2020-10-13 2022-01-21 西北工业大学 Channel structure capable of restraining flow distribution deviation of supercritical fluid
FR3129429A1 (en) 2021-11-24 2023-05-26 Safran Aircraft Engines TURBINE DISTRIBUTOR SECTOR FOR AN AIRCRAFT TURBOMACHINE
FR3130314A1 (en) 2021-12-14 2023-06-16 Safran Aircraft Engines TURBINE DISTRIBUTOR SECTOR FOR AN AIRCRAFT TURBOMACHINE

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE685320A (en) * 1965-05-03 1967-01-16
FR2094033A1 (en) * 1970-06-04 1972-02-04 Westinghouse Electric Corp
FR2205097A5 (en) * 1972-10-31 1974-05-24 Avco Corp
US5630700A (en) * 1996-04-26 1997-05-20 General Electric Company Floating vane turbine nozzle
EP1496205A1 (en) * 2003-06-30 2005-01-12 Snecma Moteurs Cooled blade for a gas turbine engine
EP1544414A1 (en) * 2003-12-17 2005-06-22 General Electric Company Inboard cooled nozzle doublet
EP1626162A1 (en) * 2004-08-11 2006-02-15 United Technologies Corporation Temperature tolerant vane assembly

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1125660A (en) * 1979-06-29 1982-06-15 David L. Brown Cooled vane structure for a combustion turbine engine
US4381173A (en) * 1980-08-25 1983-04-26 United Technologies Corporation Coolable rotor blade assembly for an axial flow rotary machine
US5145315A (en) * 1991-09-27 1992-09-08 Westinghouse Electric Corp. Gas turbine vane cooling air insert
JPH06129204A (en) * 1992-10-19 1994-05-10 Mitsubishi Heavy Ind Ltd Gas turbine cooling structure for gas turbine stator vane
JP3324256B2 (en) * 1994-02-01 2002-09-17 石川島播磨重工業株式会社 Turbine vane assembly method
JP3480069B2 (en) * 1994-10-11 2003-12-15 石川島播磨重工業株式会社 Fixed cooling wing of jet engine
US6453557B1 (en) * 2000-04-11 2002-09-24 General Electric Company Method of joining a vane cavity insert to a nozzle segment of a gas turbine
EP1191189A1 (en) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gas turbine blades
US6561757B2 (en) * 2001-08-03 2003-05-13 General Electric Company Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE685320A (en) * 1965-05-03 1967-01-16
FR2094033A1 (en) * 1970-06-04 1972-02-04 Westinghouse Electric Corp
FR2205097A5 (en) * 1972-10-31 1974-05-24 Avco Corp
US5630700A (en) * 1996-04-26 1997-05-20 General Electric Company Floating vane turbine nozzle
EP1496205A1 (en) * 2003-06-30 2005-01-12 Snecma Moteurs Cooled blade for a gas turbine engine
EP1544414A1 (en) * 2003-12-17 2005-06-22 General Electric Company Inboard cooled nozzle doublet
EP1626162A1 (en) * 2004-08-11 2006-02-15 United Technologies Corporation Temperature tolerant vane assembly

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955145A1 (en) * 2010-01-14 2011-07-15 Snecma HIGH PRESSURE TURBINE DISPENSER OF A TURBOREACTOR
WO2011086305A1 (en) * 2010-01-14 2011-07-21 Snecma Dispenser for a high-pressure turbine of a jet engine
GB2488958A (en) * 2010-01-14 2012-09-12 Snecma Dispenser for a high-pressure turbine of a jet engine
GB2488958B (en) * 2010-01-14 2016-04-13 Snecma A high-pressure turbine nozzle for a turbojet
US9328618B2 (en) 2010-01-14 2016-05-03 Snecma High-pressure turbine nozzle for a turbojet
FR2976616A1 (en) * 2011-06-17 2012-12-21 Snecma Ventilation system for hollow blade of turbine nozzle for e.g. turbojet engine for airplane, has tubular sleeve, air intake casing and plate that are assembled with each other to form single-piece component before assembling in blade
EP2613004A3 (en) * 2012-01-09 2017-06-28 General Electric Company Turbine nozzle assembly methods
WO2023012421A1 (en) * 2021-08-05 2023-02-09 Safran Aircraft Engines Cooling jacket of a hollow blade of a distributor
FR3126020A1 (en) * 2021-08-05 2023-02-10 Safran Aircraft Engines Distributor Hollow Blade Cooling Jacket

Also Published As

Publication number Publication date
US20070231150A1 (en) 2007-10-04
RU2007111392A (en) 2008-10-10
FR2899271B1 (en) 2008-05-30
JP2007263115A (en) 2007-10-11
RU2439334C2 (en) 2012-01-10
CA2582638C (en) 2015-04-28
FR2899271A1 (en) 2007-10-05
US7819628B2 (en) 2010-10-26
EP1840331B1 (en) 2017-05-31
CN101122243A (en) 2008-02-13
CA2582638A1 (en) 2007-09-29
CN101122243B (en) 2011-04-20

Similar Documents

Publication Publication Date Title
EP1840331B1 (en) Turbomachine nozzle
EP2252773B1 (en) Stator of a turbomachine
JP5064133B2 (en) CMC vane insulator and vane assembly
EP1783326B1 (en) Cooling arrangement for a gas turbine blade, gas turbine blade, turbine and gas turbine engine equipped with the same
CA2834213C (en) Sealing device for a turbomachine turbine nozzle
EP1811131B1 (en) Set of fixed sectorised diffuser inserts for a turbomachine compressor
WO2017060604A1 (en) Turbine ring assembly with axial retention
FR2501781A1 (en) TURBINE BLADE, IN PARTICULAR DRAWING TURBINE DIRECTOR FOR GAS TURBINE PROPULSION ASSEMBLY
CA2925438C (en) Rotary assembly for a turbomachine
EP2025872A2 (en) Turbine manifold sector
CA2472324C (en) Cooled blade of a gas turbine starter
JP2008196488A (en) Bling nozzle/carrier joint portion design for steam turbine
JP4248868B2 (en) Auxiliary seal for string hinge seal in gas turbine and its mounting method
FR3070715A1 (en) SEALING TAP INTER SEGMENTS OF AIRCRAFT TURBOMACHINE
CA2641438C (en) Cooled turbomachine blade
US11346246B2 (en) Brazed in heat transfer feature for cooled turbine components
FR3100838A1 (en) TURBOMACHINE SEALING RING
EP4111036B1 (en) Nozzle vane for turbomachine, corresponding high or low pressure nozzle for turbomachine, turbomachine and method of manufacturing a vane of a nozzle for turbomachine
EP3853445B1 (en) Turbine seal
FR3101107A1 (en) DAWN FOR AN AIRCRAFT TURBOMACHINE
FR3137716A1 (en) TURBINE DISTRIBUTOR FOR AN AIRCRAFT TURBOMACHINE
FR3129987A1 (en) COMBUSTION GAS EXHAUST PIPE FOR AN AIRCRAFT TURBOMACHINE
FR3100572A1 (en) TURBINE RING SECTOR
FR3037926A1 (en) TURBOMACHINE EXHAUST HOUSING WITH IMPROVED DESIGN

Legal Events

Date Code Title Description
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

17P Request for examination filed

Effective date: 20070405

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN AIRCRAFT ENGINES

17Q First examination report despatched

Effective date: 20161128

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602007051148

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0005180000

Ipc: F01D0009040000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/18 20060101ALI20170309BHEP

Ipc: F01D 9/06 20060101ALI20170309BHEP

Ipc: F01D 9/04 20060101AFI20170309BHEP

Ipc: F01D 25/12 20060101ALI20170309BHEP

Ipc: F01D 11/00 20060101ALI20170309BHEP

INTG Intention to grant announced

Effective date: 20170322

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007051148

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007051148

Country of ref document: DE

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

26N No opposition filed

Effective date: 20180301

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

Ref country code: DE

Payment date: 20240220

Year of fee payment: 18

Ref country code: GB

Payment date: 20240221

Year of fee payment: 18

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

Ref country code: FR

Payment date: 20240220

Year of fee payment: 18