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EP3158171B1 - Process of manufacturing and reparation of a device within a turbo machine and associated device - Google Patents

Process of manufacturing and reparation of a device within a turbo machine and associated device Download PDF

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Publication number
EP3158171B1
EP3158171B1 EP15733839.3A EP15733839A EP3158171B1 EP 3158171 B1 EP3158171 B1 EP 3158171B1 EP 15733839 A EP15733839 A EP 15733839A EP 3158171 B1 EP3158171 B1 EP 3158171B1
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EP
European Patent Office
Prior art keywords
ring
crown
abradable
annular wall
brazing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15733839.3A
Other languages
German (de)
French (fr)
Other versions
EP3158171A1 (en
Inventor
Thomas Guillaume Mongis
Guillaume Benoît Noël CHAMPION
Pascal Jean-Serge Drouard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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Publication date
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Publication of EP3158171A1 publication Critical patent/EP3158171A1/en
Application granted granted Critical
Publication of EP3158171B1 publication Critical patent/EP3158171B1/en
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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
    • 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
    • F01D11/08—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
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods

Definitions

  • the present invention relates to a method for producing and repairing a turbomachine component, such as a turbine distributor or a stator ring.
  • the state of the art includes in particular the documents EP-A2-2 372 101 , EP-A2-1 985 807 , DE-A1 -102 59 963 , EP-A1 -2159460 and EP-A1 -0119343 .
  • a turbine distributor for example low-pressure, comprises an annular row of blades extending between an internal annular platform and an external annular platform.
  • the distributor is part of the stator of the turbine and is interposed between two rotor wheels.
  • the outer annular platform of the distributor comprises attachment means on a turbine casing and its internal annular platform comprises a cylindrical annular wall for fixing a ring made of abradable material.
  • This crown is for example of the NIDA (honeycomb) type and is intended to cooperate by friction with radially external annular wipers of the rotor of the turbine, in order to limit air leaks between the distributor and the rotor.
  • the abradable crown is fixed to the cylindrical wall by brazing.
  • an abradable crown oversized in the radial direction is attached to the cylindrical wall. After its fixing by brazing on the cylindrical wall, the crown undergoes a grinding operation by machining in order to put it to the correct dimensions.
  • This technology has many drawbacks related in particular to the rectification step.
  • This rectification step results in a long period of immobilization of the turbomachine as well as a specific installation and tooling which are relatively expensive, in particular because the installation must reproduce the positioning of the distributor vis-à-vis the rotor.
  • This ring comprises attachment means on a stator casing and surrounds a rotor wheel. It has an annular support wall for an abradable crown which is intended to cooperate by friction with radially external annular wipers of the rotor wheel, in order to limit air leaks between the housing and the rotor.
  • the abradable crown is fixed by brazing on the annular wall of the ring, and must be rectified. In case of wear it is removed by machining for replacement.
  • the invention proposes a solution to the aforementioned problem which is simple, efficient and economical.
  • the invention provides a method of making a turbomachine member, such as a turbine nozzle, this member comprising an annular wall for supporting an abradable ring, the method comprising a step of fixing the abradable ring by brazing. on the annular wall, characterized in that the abradable crown is finished ribbing, the process not having a crown grinding step after it has been fixed to the annular wall.
  • the method thus differs from the prior art in particular in that it does not include a step of rectifying the crown, subsequent to its attachment to the annular wall. This is made possible by the fact that the abradable crown is already at the finished ribs before its fixation.
  • the invention is thus particularly advantageous because it makes it possible to eliminate the rectification step of the prior art, which is long, expensive and complex to implement.
  • Step a) can be carried out by machining.
  • the annular wall of the distributor is machined so that it has a predetermined radial dimension, called a reference dimension.
  • the present invention also relates to a turbomachine member, comprising an annular support wall for an abradable ring, characterized in that it comprises at least one identification marking of one or more repairs of the member by replacement of the Crown.
  • the abradable crown can be fixed by brazing to a plate which is itself fixed by brazing to the annular wall.
  • the plate and / or the abradable crown can be sectorized.
  • This member can be a turbine distributor or a stator ring.
  • FIG. 1 and 2 illustrate an exemplary embodiment of the method according to the invention for producing a turbomachine member, which is here a distributor 10 for a turbine and more precisely for a low pressure turbine.
  • the distributor 10 comprises two annular platforms, respectively internal 12 and external 14, which are coaxial and extend one inside the other.
  • the platforms 12, 14 are interconnected by an annular row of substantially radial blades 16.
  • the external platform 14 comprises means 18 for hooking onto a stator casing, not shown.
  • the internal platform 12 comprises an annular wall 20, here cylindrical, supporting an abradable crown 22, for example of the honeycomb type.
  • the annular wall 20 extends coaxially and inside another annular wall 24 of the platform 12, and is connected to this other annular wall 24 by a substantially radial wall 26.
  • the outer annular surface of the wall 24 internally defines the flow path of the air flow in the turbine.
  • the abradable crown 22 is preferably sectorized.
  • the abradable ring 22 is fixed to the radially internal surface of the annular wall 20 by brazing, for example by means of a brazing strip interposed between the wall and the ring.
  • the abradable crown 22 is finished ribs before it is fixed by brazing, so as to eliminate any operation of rectifying the crown after its fixing.
  • the ring 22 has a radial thickness r1 and the radial dimension of the distributor, measured between the radially inner and outer ends of the distributor (here between the radially inner end of the ring 22 and the radially outer end of the attachment means 18), is denoted e1.
  • r1 e1 - d1, d1 being the radial side of the distributor without the crown 22 ( figure 1 ), that is to say the radial distance between the radially inner end of the annular wall 20 and the radially outer end of the hooking means 18.
  • the radial thickness of the abradable crown 22 can be deduced from the radial sides of the distributor 10, respectively with and without a crown.
  • each step I and II of replacing a worn crown C1, C2 with a new crown C2, C3 is followed by a step of rectification RI and RII of this new crown.
  • a crown is designated by C, this letter being associated with a number which corresponds to the number of the crown.
  • C1 relates to the first crown or original crown of a distributor
  • C2 relates to the second crown of the distributor, that is to say to the replacement crown of the first crown (during a first repair or repair / replacement step), and so on.
  • the first repair operation I consists in removing the worn crown C1 by machining the crown and an internal peripheral part D 'of the annular support wall of this crown (the radial thickness of which decreases), then fixing by brazing the new C2 crown.
  • This first repair operation I is followed by a step RI of grinding the crown C2 by machining.
  • the second repair operation II consists in removing the worn crown C2 by machining the crown and an internal peripheral part D "of the annular support wall of this crown (the thickness of which decreases further), then in fixing by brazing the new C3 crown.
  • This second repair operation II is followed by a step RII of grinding the crown C3 by machining.
  • the repair method illustrated in figures 3 to 5 and 7 does not include a crown grinding step.
  • the distributor D is produced by attaching and fixing by brazing a first ring C1 on the aforementioned annular wall of the distributor.
  • the first repair operation I consists in removing the worn crown C1 by machining the crown and an internal peripheral part D 'of the annular support wall of this crown (the thickness of which decreases), then fixing by brazing the new crown C2, for example by means of a brazing strip interposed between crown C2 and the wall of distributor D.
  • This maintenance operation is advantageously followed by a step MI of marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired only once. We then obtain the distributor of the figure 3 .
  • the crown C2 has finished ribs and does not undergo any rectification after it has been fixed by brazing.
  • the thickness of material D ' which is withdrawn from the annular wall of the distributor is here controlled so that the radial thickness of the ring C2 makes up for this loss in thickness. It is thus understood that the thickness of the crown C2 is greater than that of the crown C1 and that a radial extra thickness of material is initially advantageously provided on the annular wall to allow the machining operation during the first repair operation.
  • d1 represents here the radial reference dimension of the distributor without crown.
  • the second repair operation II consists in removing the worn crown C2 by machining the crown and an internal peripheral part D "of the annular support wall of this crown (the thickness of which decreases further), then in fixing by brazing the new crown C3 but by means of a sheet metal plate P interposed between the crown C3 and the annular wall of the distributor.
  • a first brazing strip is interposed between the plate P and the annular wall and a second brazing strip is interposed between the crown C3 and the plate P.
  • the plate P is preferably sectorized.
  • This maintenance operation II is advantageously followed by a step MII for marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired twice. We then obtain the distributor of the figure 4 .
  • the crown C3 is with finished ribs and does not undergo any rectification after its fixing by brazing.
  • the thickness of material D "which is removed from the annular wall of the distributor is here controlled so that the radial thickness r1 of the ring C2 and / or the thickness h1 of the plate P makes up for this loss in thickness.
  • of C3 is less than that of C2 and may be identical to that of C1
  • the plate P has, for example, a thickness h1 of approximately 1 mm.
  • the third repair operation III consists in removing the worn crown C3 by machining the crown and an internal peripheral part P 'of the plate P (whose thickness decreases), then in fixing by brazing the new crown C4 on the plate P, for example by means of a brazing strip interposed between the plate and the crown.
  • This maintenance operation III is advantageously followed by a step MIII of marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired three times. We then obtain the distributor of the figure 5 .
  • the crown C4 is with finished ribs and does not undergo any rectification after its fixing by brazing.
  • the thickness of material P 'which is removed from the plate P is here controlled in particular so that the radial dimension d1' of the distributor without the crown C4, is equal to the aforementioned radial reference dimension (cf. figure 3 ).
  • the number of repairs that a turbine distributor can undergo can be limited to three. As a variant and as shown in figure 7 , this number may be higher. For this, it is preferable to provide a plate P of sufficient thickness to allow several successive repairs, each repair leading to a reduction in thickness of this plate by removal of an internal peripheral part P " additional. This avoids having to fix a new plate on the annular wall of the distributor, although this is also possible.
  • the invention can be applied to a stator ring 30 as shown in figure 8 .
  • the different stages represented in figure 7 in particular, being directly applicable to this ring, which can thus undergo several successive repair operations with a view to replacing its abradable crown.
  • the figure 9 shows an alternative embodiment of a repair method according to the invention, which uses the references I, II, III, C1, C2, etc., already used in the above.
  • Z1 is the value of the effective radial dimension of the distributor after removal of the crown C1 and of an internal peripheral part of its annular wall or of the plate.
  • the annular wall of the distributor is machined so that it has the aforementioned radial reference dimension, d1 '. If its effective radial dimension Z1 is greater than this reference value d1 ′, the annular wall is machined until it has this reference value. If, on the other hand, its radial dimension Z1 is lower than this reference value d1 ', the first repair step I cannot be carried out and the distributor must be repaired as if it were a second repair II .
  • the annular wall of the distributor is machined so that it has the radial dimension d1 ".
  • the plate P is machined so that it has the dimension aforementioned reference radial, d1 '.

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

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention concerne un procédé de réalisation et de réparation d'un organe de turbomachine, tel qu'un distributeur de turbine ou un anneau de stator.The present invention relates to a method for producing and repairing a turbomachine component, such as a turbine distributor or a stator ring.

ETAT DE L'ARTSTATE OF THE ART

L'état de l'art comprend notamment les documents EP-A2-2 372 101 , EP-A2-1 985 807 , DE-A1 -102 59 963 , EP-A1 -2159460 et EP-A1 -0119343 .The state of the art includes in particular the documents EP-A2-2 372 101 , EP-A2-1 985 807 , DE-A1 -102 59 963 , EP-A1 -2159460 and EP-A1 -0119343 .

De façon connue, un distributeur de turbine, par exemple basse-pression, comprend une rangée annulaire de pales s'étendant entre une plateforme annulaire interne et une plateforme annulaire externe. Le distributeur fait partie du stator de la turbine et est intercalé entre deux roues de rotor.In a known manner, a turbine distributor, for example low-pressure, comprises an annular row of blades extending between an internal annular platform and an external annular platform. The distributor is part of the stator of the turbine and is interposed between two rotor wheels.

La plateforme annulaire externe du distributeur comprend des moyens d'accrochage sur un carter de turbine et sa plateforme annulaire interne comprend une paroi annulaire cylindrique de fixation d'une couronne en matériau abradable. Cette couronne est par exemple du type NIDA (nid d'abeille) et est destinée à coopérer par frottement avec des léchettes annulaires radialement externes du rotor de la turbine, afin de limiter les fuites d'air entre le distributeur et le rotor.The outer annular platform of the distributor comprises attachment means on a turbine casing and its internal annular platform comprises a cylindrical annular wall for fixing a ring made of abradable material. This crown is for example of the NIDA (honeycomb) type and is intended to cooperate by friction with radially external annular wipers of the rotor of the turbine, in order to limit air leaks between the distributor and the rotor.

Dans la technique actuelle, la couronne abradable est fixée sur la paroi cylindrique par brasage.In the current technique, the abradable crown is fixed to the cylindrical wall by brazing.

En cas d'usure importante de la couronne abradable, il est nécessaire de la remplacer lors d'une opération de réparation. La couronne abradable est retirée par usinage. Avant de fixer une nouvelle couronne abradable, il est nécessaire de retirer toute la brasure de fixation de la couronne usée. En pratique, pour retirer la couronne et sa brasure de fixation, on est obligé d'usiner un peu dans la paroi cylindrique et donc de retirer une partie périphérique interne de la paroi cylindrique. La quantité de matière ainsi retirée dans la paroi cylindrique n'est pas maîtrisée.In the event of significant wear of the abradable crown wheel, it is necessary to replace it during a repair operation. The abradable crown is removed by machining. Before fixing a new abradable crown, it is necessary to remove all the fixing solder from the worn crown. In practice, to remove the crown and its fixing solder, it is necessary to machine a little in the cylindrical wall and therefore to remove an internal peripheral part of the cylindrical wall. The quantity of material thus withdrawn in the cylindrical wall is not controlled.

Dans la technique actuelle, pour compenser cette diminution en épaisseur de la paroi cylindrique, on rapporte sur la paroi cylindrique une couronne abradable surdimensionnée en direction radiale. Après sa fixation par brasage sur la paroi cylindrique, la couronne subit une opération de rectification par usinage afin de la mettre aux bonnes côtes.In the current technique, to compensate for this reduction in thickness of the cylindrical wall, an abradable crown oversized in the radial direction is attached to the cylindrical wall. After its fixing by brazing on the cylindrical wall, the crown undergoes a grinding operation by machining in order to put it to the correct dimensions.

Dans le cas où un distributeur subirait une deuxième opération de réparation consistant à remplacer à nouveau sa couronne abradable usée par une neuve, on comprend que le retrait par usinage de la couronne et de la brasure va entraîner une réduction supplémentaire en épaisseur de la paroi cylindrique. Autrement dit, l'épaisseur de la paroi cylindrique diminue à chaque opération de réparation. La nouvelle couronne abradable est surdimensionnée en épaisseur pour compenser la diminution en épaisseur de la paroi cylindrique.In the event that a distributor would undergo a second repair operation consisting in replacing its worn abradable crown again with a new one, it will be understood that the removal by machining of the crown and of the solder will result in an additional reduction in the thickness of the cylindrical wall. . In other words, the thickness of the cylindrical wall decreases with each repair operation. The new abradable crown is oversized in thickness to compensate for the decrease in thickness of the cylindrical wall.

Actuellement, une seule référence standard de couronne abradable surdimensionnée est utilisée pour la fabrication ou la ou les réparations d'un distributeur et dans chaque cas (fabrication ou réparations), la couronne est rectifiée après sa fixation pour sa mise aux bonnes côtes.Currently, a single standard reference of oversized abradable crown is used for the manufacture or the repair or repairs of a distributor and in each case (manufacture or repairs), the crown is rectified after its fixing for its setting to the correct dimensions.

Cependant, cette technologie présente de nombreux inconvénients en particulier liés à l'étape de rectification. Cette étape de rectification entraîne une durée d'immobilisation importante de la turbomachine ainsi qu'une installation et un outillage spécifiques qui sont relativement coûteux, en particulier parce que l'installation doit reproduire le positionnement du distributeur vis-à-vis du rotor.However, this technology has many drawbacks related in particular to the rectification step. This rectification step results in a long period of immobilization of the turbomachine as well as a specific installation and tooling which are relatively expensive, in particular because the installation must reproduce the positioning of the distributor vis-à-vis the rotor.

Le problème se pose également dans le cas d'un anneau de stator. Cet anneau comprend des moyens d'accrochage sur un carter de stator et entoure une roue de rotor. Il a une paroi annulaire de support d'une couronne abradable qui est destinée à coopérer par frottement avec des léchettes annulaires radialement externes de la roue de rotor, afin de limiter les fuites d'air entre le carter et le rotor. Comme dans le cas précité, la couronne abradable est fixée par brasage sur la paroi annulaire de l'anneau, et doit être rectifiée. En cas d'usure elle est retirée par usinage en vue de son remplacement.The problem also arises in the case of a stator ring. This ring comprises attachment means on a stator casing and surrounds a rotor wheel. It has an annular support wall for an abradable crown which is intended to cooperate by friction with radially external annular wipers of the rotor wheel, in order to limit air leaks between the housing and the rotor. As in the aforementioned case, the abradable crown is fixed by brazing on the annular wall of the ring, and must be rectified. In case of wear it is removed by machining for replacement.

L'invention propose une solution au problème précité qui soit simple, efficace et économique.The invention proposes a solution to the aforementioned problem which is simple, efficient and economical.

EXPOSE DE L'INVENTIONDISCLOSURE OF THE INVENTION

L'invention propose un procédé de réalisation d'un organe de turbomachine, tel qu'un distributeur de turbine, cet organe comportant une paroi annulaire de support d'une couronne abradable, le procédé comprenant une étape de fixation par brasage de la couronne abradable sur la paroi annulaire, caractérisé en ce que la couronne abradable est à côtes finies, le procédé étant dépourvu d'étape de rectification de la couronne après sa fixation sur la paroi annulaire.The invention provides a method of making a turbomachine member, such as a turbine nozzle, this member comprising an annular wall for supporting an abradable ring, the method comprising a step of fixing the abradable ring by brazing. on the annular wall, characterized in that the abradable crown is finished ribbing, the process not having a crown grinding step after it has been fixed to the annular wall.

Le procédé diffère ainsi de la technique antérieure notamment en ce qu'il ne comprend pas d'étape de rectification de la couronne, postérieure à sa fixation sur la paroi annulaire. Ceci est rendu possible grâce au fait que la couronne abradable est déjà aux côtes finies avant sa fixation. L'invention est ainsi particulièrement avantageuse car elle permet de supprimer l'étape de rectification de la technique antérieure, qui est longue, onéreuse et complexe à mettre en œuvre.The method thus differs from the prior art in particular in that it does not include a step of rectifying the crown, subsequent to its attachment to the annular wall. This is made possible by the fact that the abradable crown is already at the finished ribs before its fixation. The invention is thus particularly advantageous because it makes it possible to eliminate the rectification step of the prior art, which is long, expensive and complex to implement.

L'invention propose en outre un procédé de réparation d'un organe de turbomachine, tel qu'un distributeur de turbine, cet organe comportant une paroi annulaire de support d'une couronne abradable, le procédé comprenant des étapes de première réparation consistant à :

  1. a) retirer une première couronne abradable et la brasure de fixation de la couronne à la paroi annulaire, et une partie périphérique interne de la paroi annulaire, et
  2. b) fixer par brasage une deuxième couronne abradable sur la paroi annulaire, caractérisé en ce que la deuxième couronne abradable est à côtes finies, la première réparation étant dépourvue d'étape de rectification de la deuxième couronne après sa fixation sur la paroi annulaire.
The invention further provides a method for repairing a turbomachine member, such as a turbine nozzle, this member comprising an annular support wall for an abradable ring, the method comprising first repair steps consisting of:
  1. a) removing a first abradable crown and the solder for fixing the crown to the annular wall, and an internal peripheral part of the annular wall, and
  2. b) fixing by brazing a second abradable ring on the annular wall, characterized in that the second abradable ring has finished ribs, the first repair being devoid of a step of rectifying the second ring after it has been fixed to the annular wall.

L'étape a) peut être réalisée par usinage. Avantageusement, la paroi annulaire du distributeur est usinée pour qu'elle ait une côte radiale prédéterminée, dite de référence.Step a) can be carried out by machining. Advantageously, the annular wall of the distributor is machined so that it has a predetermined radial dimension, called a reference dimension.

Le procédé de réparation peut comprendre une ou plusieurs des caractéristiques ou étapes suivantes, qui peuvent être prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • l'étape a) est réalisée par usinage ;
  • une partie périphérique interne de la paroi annulaire est retirée à l'étape a), jusqu'à ce que la paroi annulaire ait une côte radiale prédéterminée ;
  • le procédé comprend des étapes de deuxième réparation consistant à :
    • c) retirer la deuxième couronne abradable, la brasure de fixation de cette deuxième couronne, et une partie périphérique interne de la paroi annulaire,
    • d) fixer par brasage une plaque sur la périphérie interne de la paroi annulaire, et
    • e) fixer par brasage une troisième couronne abradable à côtes finies sur la plaque, la troisième couronne abradable ayant une épaisseur radiale différente de celle de la deuxième couronne et qui est déterminée en fonction de l'épaisseur de la plaque et de l'épaisseur de matière retirée de la paroi annulaire ;
  • la plaque est une tôle, qui a par exemple une épaisseur de 1 mm ;
  • la plaque et la troisième couronne sont brasées en même temps ;
  • le procédé comprend des étapes de troisième réparation consistant à :
    • f) retirer la troisième couronne abradable, la brasure de fixation de cette troisième couronne, et une partie périphérique interne de la plaque, et
    • g) fixer par brasage une quatrième couronne abradable à côtes finies sur la plaque ;
  • l'étape f) peut être réalisée par usinage ; avantageusement, la plaque du distributeur est usinée pour qu'elle ait une côte radiale prédéterminée, dite de référence ;
  • la plaque a une côte radiale prédéterminée à la fin de l'étape f), et en ce que la quatrième couronne a une épaisseur radiale identique à celle de la deuxième couronne ;
  • la plaque et/ou la couronne abradable peuvent être sectorisées, et comprendre chacune une rangée annulaire de secteurs disposés circonférentiellement bout à bout ;
  • le procédé comprend une étape de marquage du distributeur après la ou chaque réparation ; cette étape de marquage est particulièrement avantageuse car elle permet à un opérateur de maintenance par exemple de savoir rapidement si l'organe a déjà été réparé et, dans l'affirmative, combien de réparations il a subi.
The repair process may include one or more of the following features or steps, which may be taken in isolation from each other or in combination with each other:
  • step a) is carried out by machining;
  • an internal peripheral part of the annular wall is removed in step a), until the annular wall has a predetermined radial dimension;
  • the method comprises second repair steps consisting of:
    • c) removing the second abradable ring, the solder for fixing this second ring, and an internal peripheral part of the annular wall,
    • d) fixing by brazing a plate on the internal periphery of the annular wall, and
    • e) fixing by brazing a third abradable crown with finished ribs on the plate, the third abradable crown having a radial thickness different from that of the second crown and which is determined according to the thickness of the plate and the thickness of material removed from the annular wall;
  • the plate is a sheet, which has for example a thickness of 1 mm;
  • the plate and the third crown are brazed at the same time;
  • the method comprises third repair steps consisting of:
    • f) removing the third abradable ring, the solder for fixing this third ring, and an internal peripheral part of the plate, and
    • g) fixing by brazing a fourth abradable crown with finished ribs on the plate;
  • step f) can be carried out by machining; advantageously, the distributor plate is machined so that it has a predetermined radial dimension, called reference;
  • the plate has a predetermined radial dimension at the end of step f), and in that the fourth ring has a radial thickness identical to that of the second ring;
  • the plate and / or the abradable crown can be sectorized, and each comprise an annular row of sectors disposed circumferentially end to end;
  • the method comprises a step of marking the dispenser after the or each repair; this marking step is particularly advantageous because it allows a maintenance operator, for example, to quickly know whether the component has already been repaired and, if so, how many repairs it has undergone.

La présente invention concerne encore un organe de turbomachine, comportant une paroi annulaire de support d'une couronne abradable, caractérisé en ce qu'il comprend au moins un marquage d'identification d'une ou plusieurs réparations de l'organe par remplacement de la couronne.The present invention also relates to a turbomachine member, comprising an annular support wall for an abradable ring, characterized in that it comprises at least one identification marking of one or more repairs of the member by replacement of the Crown.

La couronne abradable peut être fixée par brasage à une plaque qui est elle-même fixée par brasage à la paroi annulaire.The abradable crown can be fixed by brazing to a plate which is itself fixed by brazing to the annular wall.

La plaque et/ou la couronne abradable peuvent être sectorisées.The plate and / or the abradable crown can be sectorized.

Cet organe peut être un distributeur de turbine ou un anneau de stator.This member can be a turbine distributor or a stator ring.

DESCRIPTION DES FIGURESDESCRIPTION OF FIGURES

L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés, dans lesquels :

  • les figures 1 et 2 sont des demi-vue schématiques en coupe axiale d'un distributeur de turbine, respectivement avec et sans couronne abradable, et illustrent des étapes d'un procédé de réalisation selon l'invention;
  • les figures 3 à 5 sont des vues schématiques partielles et à plus grande échelle d'un distributeur de turbine, et illustrent des étapes d'un procédé de réparation selon l'invention ;
  • la figure 6 est un organigramme présentant des étapes d'un procédé de réparation selon la technique antérieure ;
  • la figure 7 est un organigramme présentant des étapes d'un procédé de réparation selon l'invention ;
  • la figure 8 est une demi-vue schématique en coupe axiale d'un anneau de stator ; et
  • la figure 9 est un organigramme présentant des étapes d'une variante de réalisation d'un procédé de réparation selon l'invention.
The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings, in which:
  • the figures 1 and 2 are schematic half-views in axial section of a turbine distributor, respectively with and without an abradable crown, and illustrate steps of a production method according to the invention;
  • the figures 3 to 5 are partial schematic views and on a larger scale of a turbine distributor, and illustrate steps of a repair method according to the invention;
  • the figure 6 is a flowchart showing steps of a prior art repair process;
  • the figure 7 is a flowchart showing steps of a repair method according to the invention;
  • the figure 8 is a schematic half-view in axial section of a stator ring; and
  • the figure 9 is a flowchart showing steps of an alternative embodiment of a repair method according to the invention.

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

On se réfère d'abord aux figures 1 et 2 qui illustrent un exemple de réalisation du procédé selon l'invention de réalisation d'un organe de turbomachine, qui est ici un distributeur 10 de turbine et plus précisément de turbine basse pression.We refer first to the figures 1 and 2 which illustrate an exemplary embodiment of the method according to the invention for producing a turbomachine member, which is here a distributor 10 for a turbine and more precisely for a low pressure turbine.

Le distributeur 10 comprend deux plateformes annulaires, respectivement interne 12 et externe 14, qui sont coaxiales et s'étendent l'une à l'intérieur de l'autre. Les plateformes 12, 14 sont reliées entre elles par une rangée annulaire de pales 16 sensiblement radiales.The distributor 10 comprises two annular platforms, respectively internal 12 and external 14, which are coaxial and extend one inside the other. The platforms 12, 14 are interconnected by an annular row of substantially radial blades 16.

La plateforme externe 14 comprend des moyens 18 d'accrochage sur un carter de stator, non représenté.The external platform 14 comprises means 18 for hooking onto a stator casing, not shown.

La plateforme interne 12 comprend une paroi annulaire 20, ici cylindrique, de support d'une couronne abradable 22, par exemple du type nid d'abeille. La paroi annulaire 20 s'étend coaxialement et à l'intérieur d'une autre paroi annulaire 24 de la plateforme 12, et est reliée à cette autre paroi annulaire 24 par une paroi 26 sensiblement radiale. La surface annulaire externe de la paroi 24 définit intérieurement la veine d'écoulement du flux d'air dans la turbine.The internal platform 12 comprises an annular wall 20, here cylindrical, supporting an abradable crown 22, for example of the honeycomb type. The annular wall 20 extends coaxially and inside another annular wall 24 of the platform 12, and is connected to this other annular wall 24 by a substantially radial wall 26. The outer annular surface of the wall 24 internally defines the flow path of the air flow in the turbine.

La couronne abradable 22 est de préférence sectorisée.The abradable crown 22 is preferably sectorized.

La couronne abradable 22 est fixée sur la surface radialement interne de la paroi annulaire 20 par brasage, par exemple au moyen d'un feuillard de brasure intercalé entre la paroi et la couronne.The abradable ring 22 is fixed to the radially internal surface of the annular wall 20 by brazing, for example by means of a brazing strip interposed between the wall and the ring.

Conformément à l'invention, la couronne abradable 22 est aux côtes finies avant sa fixation par brasage, de façon à supprimer toute opération de rectification de la couronne postérieurement à sa fixation.According to the invention, the abradable crown 22 is finished ribs before it is fixed by brazing, so as to eliminate any operation of rectifying the crown after its fixing.

Dans l'exemple représenté, la couronne 22 a une épaisseur radiale r1 et la côte radiale du distributeur, mesurée entre les extrémités radialement interne et externe du distributeur (ici entre l'extrémité radialement interne de la couronne 22 et l'extrémité radialement externe des moyens d'accrochage 18), est notée e1.In the example shown, the ring 22 has a radial thickness r1 and the radial dimension of the distributor, measured between the radially inner and outer ends of the distributor (here between the radially inner end of the ring 22 and the radially outer end of the attachment means 18), is denoted e1.

r1 = e1 - d1, d1 étant la côté radiale du distributeur sans la couronne 22 (figure 1), c'est-à-dire la distance radiale entre l'extrémité radialement interne de la paroi annulaire 20 et l'extrémité radialement externe des moyens d'accrochage 18.r1 = e1 - d1, d1 being the radial side of the distributor without the crown 22 ( figure 1 ), that is to say the radial distance between the radially inner end of the annular wall 20 and the radially outer end of the hooking means 18.

On peut ainsi facilement déduire la valeur de r1 des valeurs de d1 et e1. Autrement dit, on peut déduire l'épaisseur radiale de la couronne abradable 22 à partir des côtés radiales du distributeur 10, respectivement avec et sans couronne.We can thus easily deduce the value of r1 from the values of d1 and e1. In other words, the radial thickness of the abradable crown 22 can be deduced from the radial sides of the distributor 10, respectively with and without a crown.

On se réfère maintenant aux figures 3 à 5 et 7 qui concernent un procédé selon l'invention de réparation d'un organe de turbomachine, qui est ici également un distributeur 10 de turbine.We now refer to figures 3 to 5 and 7 which relate to a method according to the invention for repairing a turbine engine member, which is also here a turbine distributor 10.

Dans la technique antérieure représentée en figure 6, on constate que chaque étape I et II de remplacement d'une couronne usée C1, C2 par une nouvelle couronne C2, C3 est suivie d'une étape de rectification RI et RII de cette nouvelle couronne. Dans ce qui suit, une couronne est désignée par C, cette lettre étant associée à un chiffre qui correspond au numéro de la couronne. Ainsi, C1 se rapporte à la première couronne ou couronne d'origine d'un distributeur, C2 se rapporte à la deuxième couronne du distributeur, c'est-à-dire à la couronne de remplacement de la première couronne (lors d'une première réparation ou étape de réparation/remplacement), et ainsi de suite.In the prior art shown in figure 6 , it can be seen that each step I and II of replacing a worn crown C1, C2 with a new crown C2, C3 is followed by a step of rectification RI and RII of this new crown. In what follows, a crown is designated by C, this letter being associated with a number which corresponds to the number of the crown. Thus, C1 relates to the first crown or original crown of a distributor, C2 relates to the second crown of the distributor, that is to say to the replacement crown of the first crown (during a first repair or repair / replacement step), and so on.

La première opération de réparation I consiste à retirer la couronne usée C1 par usinage de la couronne et d'une partie périphérique interne D' de la paroi annulaire de support de cette couronne (dont l'épaisseur radiale diminue), puis à fixer par brasage la nouvelle couronne C2.The first repair operation I consists in removing the worn crown C1 by machining the crown and an internal peripheral part D 'of the annular support wall of this crown (the radial thickness of which decreases), then fixing by brazing the new C2 crown.

Cette première opération de réparation I est suivie d'une étape RI de rectification de la couronne C2 par usinage.This first repair operation I is followed by a step RI of grinding the crown C2 by machining.

Dans le cas où la deuxième couronne C2 est usée et doit être remplacée, une nouvelle opération de réparation est mise en place. La deuxième opération de réparation II consiste à retirer la couronne usée C2 par usinage de la couronne et d'une partie périphérique interne D" de la paroi annulaire de support de cette couronne (dont l'épaisseur diminue davantage), puis à fixer par brasage la nouvelle couronne C3.If the second ring gear C2 is worn and must be replaced, a new repair operation is put in place. The second repair operation II consists in removing the worn crown C2 by machining the crown and an internal peripheral part D "of the annular support wall of this crown (the thickness of which decreases further), then in fixing by brazing the new C3 crown.

Cette deuxième opération de réparation II est suivie d'une étape RII de rectification de la couronne C3 par usinage.This second repair operation II is followed by a step RII of grinding the crown C3 by machining.

Au contraire, selon la présente invention, le procédé de réparation illustré aux figures 3 à 5 et 7 ne comprend pas d'étape de rectification de couronne.On the contrary, according to the present invention, the repair method illustrated in figures 3 to 5 and 7 does not include a crown grinding step.

Comme décrit dans ce qui précède en référence aux figures 1 et 2, le distributeur D est réalisé en rapportant et fixant par brasage une première couronne C1 sur la paroi annulaire précitée du distributeur.As described in the above with reference to figures 1 and 2 , the distributor D is produced by attaching and fixing by brazing a first ring C1 on the aforementioned annular wall of the distributor.

Dans le cas ou cette première couronne C1 est usée et doit être remplacée, une première opération de réparation I est mise en place. La première opération de réparation I consiste à retirer la couronne usée C1 par usinage de la couronne et d'une partie périphérique interne D' de la paroi annulaire de support de cette couronne (dont l'épaisseur diminue), puis à fixer par brasage la nouvelle couronne C2, par exemple au moyen d'un feuillard de brasure intercalé entre la couronne C2 et la paroi du distributeur D.In the event that this first ring gear C1 is worn and must be replaced, a first repair operation I is put in place. The first repair operation I consists in removing the worn crown C1 by machining the crown and an internal peripheral part D 'of the annular support wall of this crown (the thickness of which decreases), then fixing by brazing the new crown C2, for example by means of a brazing strip interposed between crown C2 and the wall of distributor D.

Cette opération de maintenance est avantageusement suivie d'une étape MI de marquage du distributeur pour pouvoir clairement identifié que le distributeur D a été réparé une seule fois. On obtient alors le distributeur de la figure 3.This maintenance operation is advantageously followed by a step MI of marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired only once. We then obtain the distributor of the figure 3 .

Selon l'invention, la couronne C2 est aux côtes finies et ne subit pas de rectification après sa fixation par brasage. L'épaisseur de matière D' qui est retirée de la paroi annulaire du distributeur est ici maîtrisée pour que l'épaisseur radiale de la couronne C2 rattrape cette perte en épaisseur. On comprend ainsi que l'épaisseur de la couronne C2 est supérieure à celle de la couronne C1 et qu'une surépaisseur radiale de matière est initialement avantageusement prévue sur la paroi annulaire pour autoriser l'opération d'usinage lors de la première opération de réparation I. Autrement dit, en référence aux figures 2 et 3, r1' > r1 et r1' = e1 - d1' et r1' - r1 = d1 - d1'.According to the invention, the crown C2 has finished ribs and does not undergo any rectification after it has been fixed by brazing. The thickness of material D 'which is withdrawn from the annular wall of the distributor is here controlled so that the radial thickness of the ring C2 makes up for this loss in thickness. It is thus understood that the thickness of the crown C2 is greater than that of the crown C1 and that a radial extra thickness of material is initially advantageously provided on the annular wall to allow the machining operation during the first repair operation. I. In other words, with reference to figures 2 and 3 , r1 '> r1 and r1' = e1 - d1 'and r1' - r1 = d1 - d1 '.

d1' représente ici la côte radiale de référence du distributeur sans couronne.d1 'represents here the radial reference dimension of the distributor without crown.

Dans le cas ou la deuxième couronne C2 est usée et doit être remplacée, une deuxième opération de réparation II est mise en place. La deuxième opération de réparation II consiste à retirer la couronne usée C2 par usinage de la couronne et d'une partie périphérique interne D" de la paroi annulaire de support de cette couronne (dont l'épaisseur diminue davantage), puis à fixer par brasage la nouvelle couronne C3 mais par l'intermédiaire d'une plaque en tôle P intercalée entre la couronne C3 et la paroi annulaire du distributeur. Pour cela, un premier feuillard de brasure est intercalé entre la plaque P et la paroi annulaire et un second feuillard de brasure est intercalé entre la couronne C3 et la plaque P. La plaque P est de préférence sectorisée.In the event that the second ring gear C2 is worn and must be replaced, a second repair operation II is put in place. The second repair operation II consists in removing the worn crown C2 by machining the crown and an internal peripheral part D "of the annular support wall of this crown (the thickness of which decreases further), then in fixing by brazing the new crown C3 but by means of a sheet metal plate P interposed between the crown C3 and the annular wall of the distributor. For this, a first brazing strip is interposed between the plate P and the annular wall and a second brazing strip is interposed between the crown C3 and the plate P. The plate P is preferably sectorized.

Cette opération de maintenance II est avantageusement suivie d'une étape MII de marquage du distributeur pour pouvoir clairement identifié que le distributeur D a été réparé deux fois. On obtient alors le distributeur de la figure 4.This maintenance operation II is advantageously followed by a step MII for marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired twice. We then obtain the distributor of the figure 4 .

La couronne C3 est aux côtes finies et ne subit pas de rectification après sa fixation par brasage. L'épaisseur de matière D" qui est retirée de la paroi annulaire du distributeur est ici maîtrisée pour que l'épaisseur radiale r1 de la couronne C2 et/ou l'épaisseur h1 de la plaque P rattrape cette perte en épaisseur. L'épaisseur de C3 est inférieure à celle de C2 et peut être identique à celle de C1. La plaque P a par exemple une épaisseur h1 de 1mm environ.The crown C3 is with finished ribs and does not undergo any rectification after its fixing by brazing. The thickness of material D "which is removed from the annular wall of the distributor is here controlled so that the radial thickness r1 of the ring C2 and / or the thickness h1 of the plate P makes up for this loss in thickness. of C3 is less than that of C2 and may be identical to that of C1 The plate P has, for example, a thickness h1 of approximately 1 mm.

Dans le cas ou la troisième couronne C3 est usée et doit être remplacée, une troisième opération de réparation III est mise en place. La troisième opération de réparation III consiste à retirer la couronne usée C3 par usinage de la couronne et d'une partie périphérique interne P' de la plaque P (dont l'épaisseur diminue), puis à fixer par brasage la nouvelle couronne C4 sur la plaque P, par exemple au moyen d'un feuillard de brasure intercalé entre la plaque et la couronne.In the event that the third crown gear C3 is worn and must be replaced, a third repair operation III is put in place. The third repair operation III consists in removing the worn crown C3 by machining the crown and an internal peripheral part P 'of the plate P (whose thickness decreases), then in fixing by brazing the new crown C4 on the plate P, for example by means of a brazing strip interposed between the plate and the crown.

Cette opération de maintenance III est avantageusement suivie d'une étape MIII de marquage du distributeur pour pouvoir clairement identifié que le distributeur D a été réparé trois fois. On obtient alors le distributeur de la figure 5.This maintenance operation III is advantageously followed by a step MIII of marking the dispenser in order to be able to clearly identify that the dispenser D has been repaired three times. We then obtain the distributor of the figure 5 .

La couronne C4 est aux côtes finies et ne subit pas de rectification après sa fixation par brasage. L'épaisseur de matière P' qui est retirée de la plaque P est ici maîtrisée en particulier pour que la côte radiale d1' du distributeur sans la couronne C4, soit égale à la côte radiale de référence précitée (cf. figure 3). On utilise donc une couronne abradable C4 de même épaisseur r1' que lors de la première opération de maintenance I (figure 3). On comprend ainsi que C1 et C3 sont identiques (C1 = C3) et que C2 et C4 sont également identiques (C2 = C4). Deux références seulement de couronne abradable suffisent donc pour la mise en œuvre du procédé.The crown C4 is with finished ribs and does not undergo any rectification after its fixing by brazing. The thickness of material P 'which is removed from the plate P is here controlled in particular so that the radial dimension d1' of the distributor without the crown C4, is equal to the aforementioned radial reference dimension (cf. figure 3 ). We therefore use an abradable crown C4 of the same thickness r1 'as during the first maintenance operation I ( figure 3 ). It is thus understood that C1 and C3 are identical (C1 = C3) and that C2 and C4 are also identical (C2 = C4). Only two references of an abradable crown are therefore sufficient for the implementation of the method.

Le nombre de réparations que peut subir un distributeur de turbine peut être limité à trois. En variante et comme représenté en figure 7, ce nombre peut être plus élevé. Pour cela, il est préférable de prévoir une plaque P d'épaisseur suffisante pour autoriser plusieurs réparations successives, chaque réparation entraînant une diminution en épaisseur de cette plaque par retrait d'une partie périphérique interne P" supplémentaire. Cela évite d'avoir à fixer une nouvelle plaque sur la paroi annulaire du distributeur, bien que ceci soit aussi envisageable.The number of repairs that a turbine distributor can undergo can be limited to three. As a variant and as shown in figure 7 , this number may be higher. For this, it is preferable to provide a plate P of sufficient thickness to allow several successive repairs, each repair leading to a reduction in thickness of this plate by removal of an internal peripheral part P " additional. This avoids having to fix a new plate on the annular wall of the distributor, although this is also possible.

L'invention peut être appliquée à un anneau de stator 30 tel que représenté en figure 8. Les différentes étapes représentées en figure 7 notamment, étant applicables directement à cet anneau, qui peut ainsi subir plusieurs opérations successives de réparation en vue du remplacement de sa couronne abradable.The invention can be applied to a stator ring 30 as shown in figure 8 . The different stages represented in figure 7 in particular, being directly applicable to this ring, which can thus undergo several successive repair operations with a view to replacing its abradable crown.

La figure 9 représente une variante de réalisation d'un procédé de réparation selon l'invention, qui reprend les références I, II, III, C1, C2, etc., déjà utilisées dans ce qui précède.The figure 9 shows an alternative embodiment of a repair method according to the invention, which uses the references I, II, III, C1, C2, etc., already used in the above.

On peut ici noter qu'au début de chaque opération de réparation I, II, III, une étape de lecture et d'identification d'un marquage éventuel du distributeur a lieu. On peut également noter que, du fait de l'épaisseur de la plaque P utilisée dans la seconde étape de réparation, le nombre de réparations que peut subir le distributeur est ici limité à trois.It can be noted here that at the start of each repair operation I, II, III, a step of reading and identifying a possible marking of the dispenser takes place. It can also be noted that, due to the thickness of the plate P used in the second repair step, the number of repairs that the distributor can undergo is here limited to three.

Z1 est la valeur de la côte radiale effective du distributeur après retrait de la couronne C1 et d'une partie périphérique interne de sa paroi annulaire ou de la plaque. Lors de la première réparation I, la paroi annulaire du distributeur est usinée de façon à ce qu'elle ait la côte radiale de référence précitée, d1'. Si sa côte radiale effective Z1 est plus importante que cette valeur de référence d1', la paroi annulaire est usinée jusqu'à avoir cette valeur de référence. Si, par contre, sa côte radiale Z1 est plus faible que cette valeur de référence d1', la première étape de réparation I ne peut par être effectuée et on doit réparer le distributeur comme s'il s'agissait d'une deuxième réparation II. Lors de la deuxième réparation II, la paroi annulaire du distributeur est usinée de façon à ce qu'elle ait la côte radiale d1 ". Lors de la troisième réparation III, la plaque P est usinée de façon à ce qu'elle ait la côte radiale de référence précitée, d1'.Z1 is the value of the effective radial dimension of the distributor after removal of the crown C1 and of an internal peripheral part of its annular wall or of the plate. During the first repair I, the annular wall of the distributor is machined so that it has the aforementioned radial reference dimension, d1 '. If its effective radial dimension Z1 is greater than this reference value d1 ′, the annular wall is machined until it has this reference value. If, on the other hand, its radial dimension Z1 is lower than this reference value d1 ', the first repair step I cannot be carried out and the distributor must be repaired as if it were a second repair II . During the second repair II, the annular wall of the distributor is machined so that it has the radial dimension d1 ". During the third repair III, the plate P is machined so that it has the dimension aforementioned reference radial, d1 '.

Claims (11)

  1. Method for repairing a turbine-engine component, such as a turbine nozzle (10, D), this component comprising an annular wall supporting an abradable ring (22), the method comprising first-repair steps (I) consisting of:
    a) removing a first abradable ring (C1), the brazing for fixing the ring to the annular wall, and an inner peripheral part (D') of the annular wall, and
    b) fixing a second abradable ring (C2) to the annular wall by brazing,
    characterised in that the second abradable ring has the finished dimensions (r1'), the first repair not having a step of grinding of the second ring after fixing thereof to the annular wall.
  2. Method according to claim 1, characterised in that step a) is carried out by machining.
  3. Method according to claim 2, characterised in that an inner peripheral part of the annular wall is removed at step a) until the annular wall has a predetermined radial dimension (d1').
  4. Method according to any of claims 1 to 3, characterised in that it comprises second-repair steps (II) consisting in:
    c) removing the second abradable ring (C2), the brazing for fixing this second ring, and an inner peripheral part (D') of the annular wall,
    d) fixing a plate (P) to the inner periphery of the annular wall by brazing, and
    e) fixing a third abradable ring (C3) with finished dimensions (r1) to the plate by brazing, the third abradable ring having a radial thickness that is different from that of the second ring (D2) and is determined according to the thickness (h1) of the plate and the thickness of material removed from the annular wall.
  5. Method according to claim 4, characterised in that the plate (P) is a metal sheet, which has for example a thickness (h1) of 1 mm.
  6. Method according to claim 4 or claim 5, characterised in that the plate (P) and the third ring (C3) are brazed at the same time.
  7. Method according to any of claims 4 to 6, characterised in that it comprises third-repair steps (III) consisting in:
    f) removing the third abradable ring (C3), the brazing for fixing this third ring, and an inner peripheral part (P') of the plate (P), and
    g) fixing a fourth abradable ring (C4) with finished dimensions (r1') to the plate.
  8. Method according to claim 7, characterised in that the plate (P) has a predetermined radial dimension (d1') at the end of step f), and in that the fourth ring (C4) has a radial thickness identical to that of the second ring (C2).
  9. Method according to any of claims 1 to 8, characterised in that it comprises a step (MI, MII, Mill) of marking the nozzle (D) after the or each repair.
  10. Turbine-engine component comprising an annular wall supporting an abradable ring (22), characterised in that it comprises at least one marking (MI, MII, Mill) for identifying one or more repairs to the component by replacement of the ring, and in that the abradable ring (22) is fixed by brazing to a plate (P) that is itself fixed by brazing to the annular wall.
  11. Component according to claim 10, characterised in that it is a turbine nozzle (10) or a stator annulus (30).
EP15733839.3A 2014-06-23 2015-06-15 Process of manufacturing and reparation of a device within a turbo machine and associated device Active EP3158171B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1455759A FR3022578B1 (en) 2014-06-23 2014-06-23 PROCESS FOR MAKING AND REPAIRING A TURBINE DISPENSER OF A TURBOMACHINE
PCT/FR2015/051582 WO2015197942A1 (en) 2014-06-23 2015-06-15 Method for creating and repairing a turbomachine component and associated turbomachine component

Publications (2)

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EP3158171A1 EP3158171A1 (en) 2017-04-26
EP3158171B1 true EP3158171B1 (en) 2021-12-08

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EP15733839.3A Active EP3158171B1 (en) 2014-06-23 2015-06-15 Process of manufacturing and reparation of a device within a turbo machine and associated device

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US (1) US10443427B2 (en)
EP (1) EP3158171B1 (en)
CN (1) CN106460536B (en)
BR (1) BR112016029952B1 (en)
CA (1) CA2952750C (en)
FR (1) FR3022578B1 (en)
RU (1) RU2713230C2 (en)
WO (1) WO2015197942A1 (en)

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Publication number Priority date Publication date Assignee Title
CN111561474A (en) * 2020-05-25 2020-08-21 中国航发沈阳发动机研究所 Stator structure and assembling method thereof

Citations (2)

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EP0119343A1 (en) * 1983-03-22 1984-09-26 Gulf And Western Industries, Inc. Turbine engine seal and method for repair thereof
EP2159460A1 (en) * 2008-08-27 2010-03-03 United Technologies Corporation Preforms and related methods for repairing abradable seals of gas turbine engines

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US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US5655701A (en) * 1995-07-10 1997-08-12 United Technologies Corporation Method for repairing an abradable seal
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FR2899274B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
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US8910947B2 (en) * 2010-03-30 2014-12-16 United Technologies Corporation Method of forming a seal element
EP2458157B1 (en) * 2010-11-30 2015-10-14 Techspace Aero S.A. Abradable interior stator ferrule
US8979484B2 (en) * 2012-01-05 2015-03-17 Pratt & Whitney Canada Corp. Casing for an aircraft turbofan bypass engine
FR2989724B1 (en) * 2012-04-20 2015-12-25 Snecma TURBINE STAGE FOR A TURBOMACHINE
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EP0119343A1 (en) * 1983-03-22 1984-09-26 Gulf And Western Industries, Inc. Turbine engine seal and method for repair thereof
EP2159460A1 (en) * 2008-08-27 2010-03-03 United Technologies Corporation Preforms and related methods for repairing abradable seals of gas turbine engines

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Publication number Publication date
CA2952750A1 (en) 2015-12-30
CA2952750C (en) 2022-04-26
BR112016029952A2 (en) 2017-08-22
FR3022578A1 (en) 2015-12-25
CN106460536A (en) 2017-02-22
RU2016152178A (en) 2018-07-23
RU2713230C2 (en) 2020-02-04
WO2015197942A1 (en) 2015-12-30
US10443427B2 (en) 2019-10-15
CN106460536B (en) 2019-01-04
EP3158171A1 (en) 2017-04-26
FR3022578B1 (en) 2016-06-03
BR112016029952B1 (en) 2022-08-02
RU2016152178A3 (en) 2018-12-10
US20170145849A1 (en) 2017-05-25

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