EP3973146B1 - Removable pin on a turbomachine nozzle - Google Patents

Removable pin on a turbomachine nozzle Download PDF

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Publication number
EP3973146B1
EP3973146B1 EP20720100.5A EP20720100A EP3973146B1 EP 3973146 B1 EP3973146 B1 EP 3973146B1 EP 20720100 A EP20720100 A EP 20720100A EP 3973146 B1 EP3973146 B1 EP 3973146B1
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EP
European Patent Office
Prior art keywords
head
abutment
casing
assembly according
flange
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
EP20720100.5A
Other languages
German (de)
French (fr)
Other versions
EP3973146A1 (en
Inventor
Paul Jean-Jacques Michel REVERSEAU
Didier Pierre FABRE
Sabrina BENKACI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3973146A1 publication Critical patent/EP3973146A1/en
Application granted granted Critical
Publication of EP3973146B1 publication Critical patent/EP3973146B1/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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • F05D2250/131—Two-dimensional trapezoidal polygonal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an assembly for a turbomachine. More specifically, the invention relates to the architecture of a turbine and in particular the mounting support for a distributor in a high-pressure turbine.
  • the published patent document FR 3 066 226 A1 discloses in its figure 1 a high-pressure turbine distributor, mounted on an annular casing.
  • the distributor comprises a platform supporting an annular row of stationary vanes.
  • An annular row of pins (denoted 22) allows the circumferential and radial positioning of a flange of the platform to a flange of the housing.
  • a stop (denoted 21) completes the connection between the distributor and the casing, the stop axially maintaining the flanges bearing against each other. The stop rests radially on a support ring (denoted 3).
  • removing the distributor requires removing the stopper and removing the stopper can only be done by removing the support ring, fixed to the casing.
  • the object of the invention is to propose a design for the coupling of the distributor and the high-pressure turbine casing which allows faster maintenance operations, and in particular aimed at eliminating the dismantling of the support ring and of the crankcase.
  • the subject of the invention is an assembly for a turbomachine, comprising: a turbine nozzle comprising an annular platform, an internal radial flange extending radially inwards from the platform, and one or more vanes extending radially outside from the platform; a housing including an outer radial flange; and a stop providing axial retention of the outer radial flange in contact with the inner radial flange; remarkable in that the abutment is formed of a head and a body assembled in a removable manner to the head.
  • the invention also relates to a turbomachine comprising a combustion chamber, the turbomachine being characterized in that it comprises a high-pressure turbine downstream of the combustion chamber, the turbine being equipped with an assembly according to one of the embodiments set forth above.
  • the invention finally relates to a method for maintaining a turbomachine, noteworthy in that the turbomachine is according to the embodiment of the preceding paragraph and in that the method comprises, in this order: a step of removing the body of the stopper; and a step of removing the distributor, during which the head of the abutment remains engaged in the casing and the support ring remains fixed to the casing, the method also preferably comprising a step of reassembling the distributor then a step of fixing the body of the stop on the head of the stop.
  • the measures of the invention are interesting in that only part of the abutment is to be detached from the casing to allow dismantling of the distributor. The assembly of the casing and the support ring is thus preserved. Moreover, as in operation the abutment is not subjected to significant forces, the assembly of the two parts of the abutment can be done by simple means of the quick fastening type.
  • the terms “internal” (or “inner”) and “external” (or “outer”) refer to a positioning relative to the axis of rotation of an axial turbomachine which is also the axis of rotation of the turbine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the stream in the turbomachine.
  • integral is understood as integral in rotation, and in particular rigidly linked.
  • one-piece is equivalent to “made from material” and designates different elements made from the same block of material, as opposed to “attached” which means that an element is attached, after its manufacture, to another element.
  • the figures represent the elements schematically, in particular without all of the assembly or sealing elements. Certain dimensions of the elements drawn, and in particular their radial thicknesses, are exaggerated in order to facilitate understanding of the figures.
  • distributedor is meant a set of circumferentially adjacent angular sectors and forming an annular row of stationary vanes, each of the sectors possibly comprising at least one, for example two or three stationary vanes.
  • the figure 1 schematically represents an axial turbomachine 2.
  • the turbojet engine 2 comprises a low-pressure compressor 4 and a high-pressure compressor 6, a combustion chamber 8 and one or more turbines 9.
  • the mechanical power of the turbine 9 transmitted to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chambers 8.
  • a fan 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • Reduction means such as an epicyclic reducer 22, can reduce the speed of rotation of the fan and/or of the low-pressure compressor with respect to the associated turbine.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the turbine or turbines 9 comprise alternating rotating blades and stationary blades.
  • the term "distributor” will be used to refer to a set of stationary vanes and their support platform.
  • the platform can be an entire ring or a circumferential segment (partial ring).
  • the first distributor downstream of the combustion chambers 8 is indicated by the number 10 on the figure 1 . It is followed by an 11 wheel.
  • the picture 2 is a sectional view partially representing a stage of the turbine 9 according to a known construction.
  • the stage of the turbine 9 is composed of a distributor 10 and an impeller 11.
  • the wheel 11 comprises an annular row of moving blades 110 each mounted in a cell 111 of a disc 112.
  • the distributor 10 comprises an annular row of stationary vanes 101 connected by their internal ends (foot) to a lower platform 102, which is annular.
  • Platform 102 has a flange 103 extending radially inward. This flange 103 makes it possible to make the vanes 101 integral with the annular casing 30, fixed.
  • the blades 101, 110 extend radially in the hot and high pressure air stream 18.
  • the casing 30 comprises an internal spindle 301, an external spindle 302, an external radial flange 303 and an internal radial flange 304.
  • the spindles 301, 302 are coaxial along the axis 14.
  • the outer radial flange 303 is in axial contact with the inner flange 103, the flange 303 being downstream of the flange 103.
  • the flanges 103, 303 are positioned and held radially and circumferentially together by means of pins 32, distributed angularly around of the axis 14.
  • the pins 32 extend axially through the flanges 103, 303.
  • Pin 32 visible in the section of the picture 2 extends along an axis denoted A, parallel to axis 14.
  • a stop 34 This stop extends radially along an axis denoted B.
  • the axes A and B are represented on the picture 2 to facilitate understanding of the invention, but these axes are not in the same plane, the abutment 34 being circumferentially offset with respect to the pins 32.
  • the abutment 34 extends through an orifice 305 provided in the housing 30.
  • a seal 36 housed in the flange 303 prevents air leaks from the vein 18 to the inside.
  • the stop 34 is radially supported by a support ring 40.
  • the support ring 40 is assembled to the casing 30 at its internal flange 304 by screws (not shown) extending along the axis C.
  • support 40 is also radially supported by the internal spindle 301 of the casing 30.
  • the support ring 40 can rest on a lip 306 of the casing 30.
  • the support ring 40 is provided with a layer of abradable 50 to ensure sealing by cooperating with wipers 62 of a rotating flange 60, integral with wheel 11.
  • the picture 2 illustrates the assembly in its assembled state.
  • the abutment 34 can only be removed from the housing 30 after disassembly of the support ring 40.
  • the object of the invention is to reduce the number of dismantling steps required to remove the distributor.
  • the picture 3 shows a partial sectional view of an assembly according to the invention. Pieces similar to the known set shown in figure 2 retain their reference numbers. The invention essentially differs from the known assembly by the design of the abutment.
  • the abutment is referenced 70.
  • This consists of a head 72 and a body 78.
  • the head 72 comprises an internal portion 74 and an external portion 76 which passes through the orifice 305 of the housing 30.
  • the internal portion 74 has a dimension (diameter if it is a cylinder or diagonal if it is a polygon) which is greater than the diameter of the orifice 305 so that the internal portion 74 does not enter the orifice 305.
  • head 72 is supported via its internal portion 74 by the support ring 40, fixed to the crankcase 30.
  • the head 72 is assembled in a removable manner to the body 78.
  • the head 72 and the body 78 are separable from each other, reversibly.
  • the head does not pass through the casing. She is received in accommodation provided for this purpose.
  • the head is welded to the casing or tightly mounted in its housing, so as to remain integral with the casing during dismantling of the body.
  • the body 78 is adapted to be in contact with the flange 103 to prevent the axial separation of the flanges 103, 303.
  • the body radially overlaps the internal flange 103.
  • radial overlap it is meant that geometric points of the body 78 have radial coordinates identical to that of geometric points of the flange 103.
  • the head 72 is at a radial distance from the internal flange 103 in order to allow, once the body 78 has been removed, the axial sliding of the distributor 10 upstream (to the left on the picture 3 ).
  • the figure 4 illustrates an exemplary embodiment of the stop 70.
  • the head 72 comprises in this example an internal thread 761 in which engages a threaded portion 781 of the body 78.
  • the body 78 may have a portion facilitating its gripping for unscrewing purposes , such as a portion with a square section 782.
  • body 78 and outer portion 76 of head 72 have generally axisymmetric shapes around axis B.
  • the figure 4 also partially shows the lip 306 of the casing which is close to the internal portion 74.
  • the figure 5 illustrates the internal portion 74 seen along the V:V direction defined in figure 4 . It shows the substantially polygonal section 741 of the inner portion 74, which in this example is a square.
  • the square 741 can have rounded corners 742.
  • In dotted line is represented a position of the internal portion 74 in contact with the lip 306. Indeed, during the unscrewing of the body 78 blindly - that is to say without maintaining or having access to the head 72 of the stop 70 -, if the internal portion 74 has a polygonal section, the latter can pivot and come to rest on a surface to be stopped in rotation and allow the unscrewing of the body 78 without that the internal portion 74 does not “rotate in a vacuum”.
  • the stopping surface is a surface of the lip 306.
  • the rotation of the internal portion 74 can be stopped by the internal flange 304 of the housing or by a surface of the support ring 40.
  • the contact surface between the support ring 40 and the abutment 70 can also stop the head 72 in rotation: for example, the support ring 40 can be provided with grooves and the internal portion 74 can be equipped with grooves (radial with respect to axis B) which can engage in the grooves.

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

Description

Domaine techniqueTechnical area

L'invention a trait à un ensemble pour turbomachine. Plus spécifiquement, l'invention vise l'architecture d'une turbine et en particulier le support de montage d'un distributeur dans une turbine haute-pression.The invention relates to an assembly for a turbomachine. More specifically, the invention relates to the architecture of a turbine and in particular the mounting support for a distributor in a high-pressure turbine.

Technique antérieurePrior technique

Le document de brevet publié FR 3 066 226 A1 divulgue en sa figure 1 un distributeur de turbine haute-pression, monté sur un carter annulaire. Le distributeur comprend une plateforme supportant une rangée annulaire d'aubes fixes. Une rangée annulaire de pions (notés 22) permet le positionnement circonférentiel et radial d'une bride de la plateforme à une bride du carter. Une butée (notée 21) vient compléter la liaison entre le distributeur et le carter, la butée maintenant axialement les brides en appui l'une contre l'autre. La butée est en appui radial sur un anneau de support (noté 3).The published patent document FR 3 066 226 A1 discloses in its figure 1 a high-pressure turbine distributor, mounted on an annular casing. The distributor comprises a platform supporting an annular row of stationary vanes. An annular row of pins (denoted 22) allows the circumferential and radial positioning of a flange of the platform to a flange of the housing. A stop (denoted 21) completes the connection between the distributor and the casing, the stop axially maintaining the flanges bearing against each other. The stop rests radially on a support ring (denoted 3).

Or, avec l'architecture décrite dans le document susmentionné, retirer le distributeur nécessite le démontage de la butée et démonter la butée ne peut se faire qu'en déposant l'anneau de support, fixé au carter.However, with the architecture described in the aforementioned document, removing the distributor requires removing the stopper and removing the stopper can only be done by removing the support ring, fixed to the casing.

Ainsi, plusieurs étapes de démontage et remontage sont nécessaires pour inspecter le distributeur. Les inconvénients sont évidents en termes de temps d'immobilisation d'une turbomachine en réparation et en termes de risques inhérents à la manutention de ces pièces (endommagement des pièces, risques de blessures des opérateurs, protocole d'inspection et de remontage, etc.).Thus, several disassembly and reassembly steps are necessary to inspect the distributor. The drawbacks are obvious in terms of the downtime of a turbine engine being repaired and in terms of the risks inherent in handling these parts (damage to parts, risk of injury to operators, inspection and reassembly protocol, etc. ).

Exposé de l'inventionDisclosure of Invention Problème techniqueTechnical problem

L'invention a pour objectif de proposer une conception pour l'accouplement du distributeur et du carter de turbine haute-pression qui permette des opérations de maintenance plus rapide, et en particulier visant à s'affranchir du démontage de l'anneau de support et du carter.The object of the invention is to propose a design for the coupling of the distributor and the high-pressure turbine casing which allows faster maintenance operations, and in particular aimed at eliminating the dismantling of the support ring and of the crankcase.

Solution techniqueTechnical solution

L'invention a pour objet un ensemble pour turbomachine, comprenant : un distributeur de turbine comprenant une plateforme annulaire, une bride radiale interne s'étendant radialement vers l'intérieur depuis la plateforme, et une ou plusieurs aubes s'étendant radialement vers l'extérieur depuis la plateforme ; un carter comprenant une bride radiale externe ; et une butée assurant un maintien axial de la bride radiale externe au contact de la bride radiale interne ; remarquable en ce que la butée est formée d'une tête et d'un corps assemblé de manière démontable à la tête.The subject of the invention is an assembly for a turbomachine, comprising: a turbine nozzle comprising an annular platform, an internal radial flange extending radially inwards from the platform, and one or more vanes extending radially outside from the platform; a housing including an outer radial flange; and a stop providing axial retention of the outer radial flange in contact with the inner radial flange; remarkable in that the abutment is formed of a head and a body assembled in a removable manner to the head.

Selon un mode avantageux de l'invention, l'ensemble peut comprendre l'une ou plusieurs des caractéristiques techniques suivantes, selon toute combinaison possible :

  • la tête, respectivement le corps, présente un taraudage et le corps, respectivement la tête, présente un filetage apte à coopérer avec le taraudage. Ainsi, la séparation du corps de la tête se fait par dévissage du corps et/ou de la tête ;
  • le corps est assemblé à la tête au moyen d'un mécanisme à baïonnette. Ce type d'assemblage non permanent permet un démontage rapide, sans outil particulier. Selon un mode de réalisation alternatif, d'autres types d'enclipsage ou de crabotage sont possibles également ;
  • le corps et la tête sont montés serrés l'un dans l'autre. Un serrage type montage au maillet peut suffire car la butée n'est pas soumise à de très grands efforts qui pourraient mener à la désolidarisation de ses deux parties. Le corps peut disposer d'une portion facilitant sa préhension telle une gorge ou une portion non axisymétrique à section polygonale ou cannelée, permettant, à l'aide d'un outil, de désolidariser les deux parties de la butée ;
  • la tête est radialement à distance des brides. Ainsi, seul le corps est en appui contre la bride radiale interne ;
  • la tête est de forme en T et comprend une portion interne à section polygonale et une portion externe axisymétrique. Une telle forme permet le désassemblage ou l'assemblage du corps sur la tête en aveugle, c'est-à-dire sans avoir accès à la tête. À cette fin, une surface du carter ou de l'anneau de support pourra par exemple servir d'arrêt en rotation lorsqu'un côté du polygone de la tête vient en appui sur celle-ci. La section polygonale peut présenter des sommets arrondis. Ceux-ci permettent d'éviter tout endommagement de l'anneau de support ou du carter lors du démontage du corps ;
  • la tête traverse le carter. Alternativement, la tête est logée dans le carter sans le traverser et y est maintenue par exemple par soudage ou assemblage serré ;
  • la butée s'étend selon la direction radiale et des pions s'étendent axialement, chacun des pions traversant la bride du carter et la bride du distributeur.
According to an advantageous mode of the invention, the assembly may include one or more of the following technical characteristics, according to any possible combination:
  • the head, respectively the body, has an internal thread and the body, respectively the head, has a thread capable of cooperating with the internal thread. Thus, the separation of the body from the head is done by unscrewing the body and/or the head;
  • the body is assembled to the head by means of a bayonet mechanism. This type of non-permanent assembly allows rapid dismantling, without any special tools. According to an alternative embodiment, other types of clipping or clutching are also possible;
  • the body and the head are mounted close together. A mallet-type tightening may suffice because the stopper is not subjected to very great forces which could lead to the separation of its two parts. The body may have a portion facilitating its gripping such as a groove or a non-axisymmetric portion with a polygonal or fluted section, allowing, using a tool, to separate the two parts of the abutment;
  • the head is radially remote from the flanges. Thus, only the body bears against the internal radial flange;
  • the head is T-shaped and comprises an internal portion with a polygonal section and an axisymmetric external portion. Such a shape allows disassembly or assembly of the body on the head blind, that is to say without having access to the head. To this end, a surface of the casing or of the support ring could for example serve as a stop in rotation when one side of the polygon of the head comes to rest on the latter. The polygonal section may have rounded corners. These prevent any damage to the support ring or the casing during disassembly of the body;
  • the head goes through the crankcase. Alternatively, the head is housed in the casing without passing through it and is held there for example by welding or tight assembly;
  • the abutment extends in the radial direction and pins extend axially, each of the pins passing through the housing flange and the distributor flange.

L'invention a également pour objet une turbomachine comprenant une chambre de combustion, la turbomachine étant caractérisée en ce qu'elle comprend une turbine haute-pression en aval de la chambre de combustion, la turbine étant équipée d'un ensemble selon l'un des modes de réalisation exposés ci-dessus.The invention also relates to a turbomachine comprising a combustion chamber, the turbomachine being characterized in that it comprises a high-pressure turbine downstream of the combustion chamber, the turbine being equipped with an assembly according to one of the embodiments set forth above.

L'invention porte enfin sur un procédé de maintenance d'une turbomachine, remarquable en ce que la turbomachine est selon le mode de réalisation du paragraphe précédent et en ce que le procédé comprend, dans cet ordre : une étape de dépose du corps de la butée ; et une étape de dépose du distributeur, pendant laquelle la tête de la butée demeure engagée dans le carter et l'anneau de support demeure fixé au carter, le procédé comprenant en outre préférentiellement une étape de remontage du distributeur puis une étape de fixation du corps de la butée sur la tête de la butée.The invention finally relates to a method for maintaining a turbomachine, noteworthy in that the turbomachine is according to the embodiment of the preceding paragraph and in that the method comprises, in this order: a step of removing the body of the stopper; and a step of removing the distributor, during which the head of the abutment remains engaged in the casing and the support ring remains fixed to the casing, the method also preferably comprising a step of reassembling the distributor then a step of fixing the body of the stop on the head of the stop.

Avantages de l'inventionAdvantages of the invention

Les mesures de l'invention sont intéressantes en ce que seule une partie de la butée est à désolidariser du carter pour permettre le démontage du distributeur. On conserver ainsi l'assemblage du carter et de l'anneau de support. De plus, comme en fonctionnement la butée n'est pas soumise à des efforts importants, l'assemblage des deux parties de la butée peut se faire par des moyens simples de type fixation rapide.The measures of the invention are interesting in that only part of the abutment is to be detached from the casing to allow dismantling of the distributor. The assembly of the casing and the support ring is thus preserved. Moreover, as in operation the abutment is not subjected to significant forces, the assembly of the two parts of the abutment can be done by simple means of the quick fastening type.

Brève description des dessinsBrief description of the drawings

  • La figure 1 décrit une turbomachine selon l'invention ;The figure 1 describes a turbomachine according to the invention;
  • La figure 2 représente une vue en coupe partielle d'une turbine connue ;The picture 2 shows a partial sectional view of a known turbine;
  • La figure 3 illustre une vue en coupe partielle d'une turbine selon l'invention ;The picture 3 illustrates a partial sectional view of a turbine according to the invention;
  • La figure 4 montre un mode de réalisation de la butée selon l'invention ;The figure 4 shows an embodiment of the stopper according to the invention;
  • La figure 5 illustre un détail de la butée, vu selon la direction V:V définie en figure 4.The figure 5 illustrates a detail of the stop, seen according to the direction V:V defined in figure 4 .
Description détailléedetailed description

Dans la description qui va suivre, les termes « interne » (ou « intérieur ») et « externe » (ou « extérieur ») renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale qui est également l'axe de rotation de la turbine. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine. Le terme « solidaire » est compris comme solidaire en rotation, et notamment rigidement lié. Le terme « monobloc » est équivalent à « venu de matière » et désigne différents éléments réalisés dans un même bloc de matière, par opposition à « rapporté » qui signifie qu'un élément est rattaché, après sa fabrication, à un autre élément. Les figures représentent les éléments de manière schématique, notamment sans l'intégralité des éléments d'assemblage ou d'étanchéité. Certaines dimensions des éléments dessinés et notamment leurs épaisseurs radiales, sont exagérées afin de faciliter la compréhension des figures.In the following description, the terms "internal" (or "inner") and "external" (or "outer") refer to a positioning relative to the axis of rotation of an axial turbomachine which is also the axis of rotation of the turbine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the stream in the turbomachine. The term “integral” is understood as integral in rotation, and in particular rigidly linked. The term “one-piece” is equivalent to “made from material” and designates different elements made from the same block of material, as opposed to “attached” which means that an element is attached, after its manufacture, to another element. The figures represent the elements schematically, in particular without all of the assembly or sealing elements. Certain dimensions of the elements drawn, and in particular their radial thicknesses, are exaggerated in order to facilitate understanding of the figures.

Par « distributeur », on entend un ensemble de secteurs angulaires circonférentiellement adjacents et formant une rangée annulaire d'aubes fixes, chacun des secteurs pouvant comporter au moins une, par exemple deux ou trois aubes fixes.By "distributor" is meant a set of circumferentially adjacent angular sectors and forming an annular row of stationary vanes, each of the sectors possibly comprising at least one, for example two or three stationary vanes.

La figure 1 représente de manière simplifiée une turbomachine axiale 2. Le turboréacteur 2 comprend un compresseur basse-pression 4 et un compresseur haute-pression 6, une chambre de combustion 8 et une ou plusieurs turbines 9. En fonctionnement, la puissance mécanique de la turbine 9 transmise au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée des chambres de combustion 8.The figure 1 schematically represents an axial turbomachine 2. The turbojet engine 2 comprises a low-pressure compressor 4 and a high-pressure compressor 6, a combustion chamber 8 and one or more turbines 9. In operation, the mechanical power of the turbine 9 transmitted to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chambers 8.

Une soufflante 16 est couplée au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 et en un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine.A fan 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.

Des moyens de démultiplication, tel un réducteur épicycloïdal 22, peuvent réduire la vitesse de rotation de la soufflante et/ou du compresseur basse-pression par rapport à la turbine associée. Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée nécessaire au vol d'un avion.Reduction means, such as an epicyclic reducer 22, can reduce the speed of rotation of the fan and/or of the low-pressure compressor with respect to the associated turbine. The secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.

La ou les turbines 9 comprennent une alternance d'aubes tournantes et d'aubes fixes. On utilisera dans la présente demande la terminologie de « distributeur » pour se référer à un ensemble d'aubes fixes et de leur plateforme de support. La plateforme pouvant être un anneau entier ou un segment circonférentiel (anneau partiel). Le premier distributeur en aval des chambres de combustion 8 est indiqué par le nombre 10 sur la figure 1. Il est suivi d'une roue 11.The turbine or turbines 9 comprise alternating rotating blades and stationary blades. In the present application, the term "distributor" will be used to refer to a set of stationary vanes and their support platform. The platform can be an entire ring or a circumferential segment (partial ring). The first distributor downstream of the combustion chambers 8 is indicated by the number 10 on the figure 1 . It is followed by an 11 wheel.

La figure 2 est une vue en coupe représentant partiellement un étage de la turbine 9 selon une construction connue. L'étage de la turbine 9 est composé d'un distributeur 10 et d'une roue 11.The picture 2 is a sectional view partially representing a stage of the turbine 9 according to a known construction. The stage of the turbine 9 is composed of a distributor 10 and an impeller 11.

La roue 11 comprend une rangée annulaire d'aubes mobiles 110 montées chacune dans une alvéole 111 d'un disque 112.The wheel 11 comprises an annular row of moving blades 110 each mounted in a cell 111 of a disc 112.

Le distributeur 10 comprend une rangée annulaire d'aubes fixes 101 reliées par leurs extrémités internes (pied) à une plateforme inférieure 102, annulaire. La plateforme 102 présente une bride 103 s'étendant radialement vers l'intérieur. Cette bride 103 permet de rendre les aubes 101 solidaires du carter annulaire 30, fixe.The distributor 10 comprises an annular row of stationary vanes 101 connected by their internal ends (foot) to a lower platform 102, which is annular. Platform 102 has a flange 103 extending radially inward. This flange 103 makes it possible to make the vanes 101 integral with the annular casing 30, fixed.

Les aubes 101, 110 s'étendent radialement dans la veine d'air chaud et à haute pression 18.The blades 101, 110 extend radially in the hot and high pressure air stream 18.

Le carter 30 comprend une fusée interne 301, une fusée externe 302, une bride radiale externe 303 et une bride radiale interne 304. Les fusées 301, 302 sont coaxiales selon l'axe 14.The casing 30 comprises an internal spindle 301, an external spindle 302, an external radial flange 303 and an internal radial flange 304. The spindles 301, 302 are coaxial along the axis 14.

La bride radiale externe 303 est au contact axialement de la bride interne 103, la bride 303 étant en aval de la bride 103. Les brides 103, 303 sont positionnées et maintenues radialement et circonférentiellement entre elles par le biais de pions 32, répartis angulairement autour de l'axe 14. Les pions 32 s'étendent axialement au travers des brides 103, 303. Le pion 32 visible dans la coupe de la figure 2 s'étend selon un axe noté A, parallèle à l'axe 14.The outer radial flange 303 is in axial contact with the inner flange 103, the flange 303 being downstream of the flange 103. The flanges 103, 303 are positioned and held radially and circumferentially together by means of pins 32, distributed angularly around of the axis 14. The pins 32 extend axially through the flanges 103, 303. Pin 32 visible in the section of the picture 2 extends along an axis denoted A, parallel to axis 14.

Le maintien axial des brides 103, 303 l'une contre l'autre est assuré par une butée 34. Cette butée s'étend radialement selon un axe noté B. Les axes A et B sont représentés sur la figure 2 pour faciliter la compréhension de l'invention mais ces axes ne sont pas dans le même plan, la butée 34 étant circonférentiellement décalée par rapport aux pions 32. La butée 34 s'étend au travers d'un orifice 305 aménagé dans le carter 30.The axial holding of the flanges 103, 303 against each other is ensured by a stop 34. This stop extends radially along an axis denoted B. The axes A and B are represented on the picture 2 to facilitate understanding of the invention, but these axes are not in the same plane, the abutment 34 being circumferentially offset with respect to the pins 32. The abutment 34 extends through an orifice 305 provided in the housing 30.

Un joint d'étanchéité 36 logé dans la bride 303 évite les fuites d'air depuis la veine 18 vers l'intérieur.A seal 36 housed in the flange 303 prevents air leaks from the vein 18 to the inside.

La butée 34 est radialement supportée par un anneau de support 40. L'anneau de support 40 est assemblé au carter 30 au niveau de sa bride interne 304 par une visserie (non représentée) s'étendant selon l'axe C. L'anneau de support 40 est également radialement supporté par la fusée interne 301 du carter 30. Enfin, l'anneau de support 40 peut être en appui sur une lèvre 306 du carter 30. L'anneau de support 40 est muni d'une couche d'abradable 50 pour assurer une étanchéité en coopérant avec des léchettes 62 d'un flasque tournant 60, solidaire de la roue 11.The stop 34 is radially supported by a support ring 40. The support ring 40 is assembled to the casing 30 at its internal flange 304 by screws (not shown) extending along the axis C. support 40 is also radially supported by the internal spindle 301 of the casing 30. Finally, the support ring 40 can rest on a lip 306 of the casing 30. The support ring 40 is provided with a layer of abradable 50 to ensure sealing by cooperating with wipers 62 of a rotating flange 60, integral with wheel 11.

La figure 2 illustre l'ensemble dans son état monté. Afin de déposer le distributeur 10, il est nécessaire de déposer d'abord la butée 34. Or, la butée 34 ne peut être enlevée du carter 30 qu'après désassemblage de l'anneau de support 40. L'objectif de l'invention est de réduire le nombre d'étapes de démontage nécessaire à la dépose du distributeur.The picture 2 illustrates the assembly in its assembled state. In order to remove the distributor 10, it is necessary to first remove the abutment 34. However, the abutment 34 can only be removed from the housing 30 after disassembly of the support ring 40. The object of the invention is to reduce the number of dismantling steps required to remove the distributor.

Ainsi, la figure 3 représente une vue en coupe partielle d'un ensemble selon l'invention. Les pièces similaires à l'ensemble connu représenté en figure 2 conservent leurs numéros de référence. L'invention diffère essentiellement de l'ensemble connu par la conception de la butée.Thus, the picture 3 shows a partial sectional view of an assembly according to the invention. Pieces similar to the known set shown in figure 2 retain their reference numbers. The invention essentially differs from the known assembly by the design of the abutment.

Sur la figure 3, la butée est référencée 70. Celle-ci se compose d'une tête 72 et d'un corps 78. La tête 72 comprend une portion interne 74 et une portion externe 76 qui traverse l'orifice 305 du carter 30. La portion interne 74 a une dimension (diamètre si c'est un cylindre ou diagonale si c'est un polygone) qui est supérieure au diamètre de l'orifice 305 de sorte à ce que la portion interne 74 ne pénètre pas dans l'orifice 305. La tête 72 est supportée via sa portion interne 74 par l'anneau de support 40, fixé au carter 30.On the picture 3 , the abutment is referenced 70. This consists of a head 72 and a body 78. The head 72 comprises an internal portion 74 and an external portion 76 which passes through the orifice 305 of the housing 30. The internal portion 74 has a dimension (diameter if it is a cylinder or diagonal if it is a polygon) which is greater than the diameter of the orifice 305 so that the internal portion 74 does not enter the orifice 305. head 72 is supported via its internal portion 74 by the support ring 40, fixed to the crankcase 30.

Selon l'invention, la tête 72 est assemblée de manière démontable au corps 78. Dit autrement, la tête 72 et le corps 78 sont séparables l'un de l'autre, de façon réversible.According to the invention, the head 72 is assembled in a removable manner to the body 78. In other words, the head 72 and the body 78 are separable from each other, reversibly.

Dans un mode de réalisation alternatif et non illustré, la tête ne traverse pas le carter. Elle est reçue dans un logement prévu à cet effet. La tête est soudée au carter ou montée serrée dans son logement, de sorte à rester solidaire du carter lors du démontage du corps.In an alternative and not illustrated embodiment, the head does not pass through the casing. She is received in accommodation provided for this purpose. The head is welded to the casing or tightly mounted in its housing, so as to remain integral with the casing during dismantling of the body.

Le corps 78 est apte à être au contact de la bride 103 pour empêcher la désolidarisation axiale des brides 103, 303. Ainsi, le corps chevauche radialement la bride interne 103. Par chevauchement radial, on entend que des points géométriques du corps 78 ont des coordonnées radiales identiques à celle de points géométriques de la bride 103. La tête 72 est à distance radiale de la bride interne 103 afin de permettre, une fois le corps 78 déposé, le coulissement axial du distributeur 10 vers l'amont (vers la gauche sur la figure 3).The body 78 is adapted to be in contact with the flange 103 to prevent the axial separation of the flanges 103, 303. Thus, the body radially overlaps the internal flange 103. By radial overlap, it is meant that geometric points of the body 78 have radial coordinates identical to that of geometric points of the flange 103. The head 72 is at a radial distance from the internal flange 103 in order to allow, once the body 78 has been removed, the axial sliding of the distributor 10 upstream (to the left on the picture 3 ).

La figure 4 illustre un exemple de réalisation de la butée 70. La tête 72 comprend dans cet exemple un taraudage 761 dans lequel s'engage une portion filetée 781 du corps 78. Le corps 78 peut disposer d'une portion facilitant sa préhension à des fins de dévissage, comme par exemple une portion à section carrée 782.The figure 4 illustrates an exemplary embodiment of the stop 70. The head 72 comprises in this example an internal thread 761 in which engages a threaded portion 781 of the body 78. The body 78 may have a portion facilitating its gripping for unscrewing purposes , such as a portion with a square section 782.

Mis à part la section 782, le corps 78 et la portion externe 76 de la tête 72 ont des formes généralement axisymétriques autour de l'axe B.Apart from section 782, body 78 and outer portion 76 of head 72 have generally axisymmetric shapes around axis B.

La figure 4 montre aussi partiellement la lèvre 306 du carter qui est à proximité de la portion interne 74.The figure 4 also partially shows the lip 306 of the casing which is close to the internal portion 74.

La figure 5 illustre la portion interne 74 vue selon la direction V:V définie en figure 4. On y observe la section sensiblement polygonale 741 de la portion interne 74, qui dans cet exemple est un carré. Le carré 741 peut disposer de coins arrondis 742. En trait pointillé est représentée une position de la portion interne 74 en contact de la lèvre 306. En effet, lors du dévissage du corps 78 à l'aveugle - c'est-à-dire sans maintenir ou avoir accès à la tête 72 de la butée 70 -, si la portion interne 74 a une section polygonale, celle-ci peut pivoter et venir en appui sur une surface pour être arrêtée en rotation et permettre le dévissage du corps 78 sans que la portion interne 74 ne « tourne dans le vide ». Dans l'exemple illustré, la surface d'arrêt est une surface de la lèvre 306.The figure 5 illustrates the internal portion 74 seen along the V:V direction defined in figure 4 . It shows the substantially polygonal section 741 of the inner portion 74, which in this example is a square. The square 741 can have rounded corners 742. In dotted line is represented a position of the internal portion 74 in contact with the lip 306. Indeed, during the unscrewing of the body 78 blindly - that is to say without maintaining or having access to the head 72 of the stop 70 -, if the internal portion 74 has a polygonal section, the latter can pivot and come to rest on a surface to be stopped in rotation and allow the unscrewing of the body 78 without that the internal portion 74 does not “rotate in a vacuum”. In the example shown, the stopping surface is a surface of the lip 306.

L'homme du métier comprendra qu'alternativement à la lèvre 306, la rotation de la portion interne 74 peut être arrêtée par la bride interne 304 du carter ou par une surface de l'anneau de support 40.Those skilled in the art will understand that alternatively to the lip 306, the rotation of the internal portion 74 can be stopped by the internal flange 304 of the housing or by a surface of the support ring 40.

Alternativement ou en complément, la surface de contact entre l'anneau de support 40 et la butée 70 peut également arrêter la tête 72 en rotation : par exemple, l'anneau de support 40 peut être pourvu de cannelures et la portion interne 74 peut être équipée de gorges (radiales par rapport à l'axe B) qui peuvent s'engager dans les cannelures.Alternatively or in addition, the contact surface between the support ring 40 and the abutment 70 can also stop the head 72 in rotation: for example, the support ring 40 can be provided with grooves and the internal portion 74 can be equipped with grooves (radial with respect to axis B) which can engage in the grooves.

Claims (10)

  1. A turbomachine assembly (2), comprising:
    - a turbine (9) distributor (10) comprising an annular platform (102), an inner radial flange (103) extending radially inwardly from the platform (102), and one or more blades (101) extending radially outwardly from the platform (102);
    - a casing (30) comprising a radially outer flange (303); and
    - an abutment (70) axially holding the outer radial flange (303) in contact with the inner radial flange (103);
    characterized in that the abutment (70) is constituted by a head (72) and a body (78), the body (78) being removably connected to the head (72).
  2. Assembly according to claim 1, characterized in that the head (72), respectively the body (78), has an internal thread (761) and the body (78), respectively the head (72), has a thread (781) able to cooperate with the internal thread (761).
  3. Assembly according to claim 1, characterized in that the body (78) is connected to the head (72) by means of a bayonet mechanism.
  4. An assembly according to claim 1, characterized in that the body (78) and the head (72) are tightly fitted together.
  5. Assembly according to any of claims 1 to 4, characterized in that the head (72) is radially spaced apart from the flanges (103, 303).
  6. Assembly according to any of claims 1 to 5, characterized in that the head (72) is T-shaped and comprises an inner portion (74) with a polygonal cross-section (741) and an axisymmetric outer portion (76).
  7. Assembly according to any of claims 1 to 6, characterized in that the head (72) passes through the casing (30).
  8. Assembly according to any of claims 1 to 7, characterized in that the abutment (70) extends in the radial direction and a plurality of pins (32) extend axially, each of the pins (32) passing through the flange (303) of the casing (30) and through the flange (103) of the distributor (10).
  9. Turbomachine (2) comprising a combustion chamber (8), the turbomachine (2) being characterized in that it comprises a high-pressure turbine (9) downstream of the combustion chamber (8), the turbine (9) being equipped with an assembly according to any of claims 1 to 8.
  10. Method of servicing a turbomachine (2), characterized in that the turbomachine (2) is as claimed in claim 9, and in that the method comprises, in this order:
    - a step of removing the body (78) of the abutment (70); and
    - a step of removing the distributor (10), during which the head (72) of the abutment (70) remains engaged in the casing (30) and the support ring (40) remains fixed to the casing (30),
    the method additionally preferably comprising a step of reassembling the distributor (10) and then a step of fixing the body (78) of the abutment (70) to the head (72) of the abutment (70).
EP20720100.5A 2019-05-21 2020-04-27 Removable pin on a turbomachine nozzle Active EP3973146B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905298A FR3096397B1 (en) 2019-05-21 2019-05-21 REMOVABLE PIONE ON TURBOMACHINE DISTRIBUTOR
PCT/EP2020/061624 WO2020233947A1 (en) 2019-05-21 2020-04-27 Removable pin on a turbomachine nozzle

Publications (2)

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EP3973146A1 EP3973146A1 (en) 2022-03-30
EP3973146B1 true EP3973146B1 (en) 2022-12-21

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US (1) US11603775B2 (en)
EP (1) EP3973146B1 (en)
CN (1) CN113811669B (en)
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3117147B1 (en) * 2020-12-09 2022-10-28 Safran Aircraft Engines Turbine stator assembly with radial degree of freedom between a distributor and a sealing ring

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GB715086A (en) * 1953-02-06 1954-09-08 Rolls Royce Improvements relating to separable joints
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FR2743603B1 (en) * 1996-01-11 1998-02-13 Snecma DEVICE FOR JOINING SEGMENTS FROM A CIRCULAR DISTRIBUTOR TO A TURBOMACHINE HOUSING
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FR3066226B1 (en) 2017-05-10 2020-07-17 Safran Aircraft Engines STATOR RING LOCK UNDER HIGH PRESSURE DISTRIBUTOR

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WO2020233947A1 (en) 2020-11-26
CN113811669A (en) 2021-12-17
FR3096397B1 (en) 2021-04-16
US20220195891A1 (en) 2022-06-23
FR3096397A1 (en) 2020-11-27
CN113811669B (en) 2024-07-16
EP3973146A1 (en) 2022-03-30
US11603775B2 (en) 2023-03-14

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