EP3584413B1 - Cast and shrink-fit annular part of an aircraft turbine engine - Google Patents

Cast and shrink-fit annular part of an aircraft turbine engine Download PDF

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Publication number
EP3584413B1
EP3584413B1 EP19180983.9A EP19180983A EP3584413B1 EP 3584413 B1 EP3584413 B1 EP 3584413B1 EP 19180983 A EP19180983 A EP 19180983A EP 3584413 B1 EP3584413 B1 EP 3584413B1
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EP
European Patent Office
Prior art keywords
flange
extraction
holes
annular
screws
Prior art date
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Application number
EP19180983.9A
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German (de)
French (fr)
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EP3584413A1 (en
Inventor
Etienne Gérard Joseph CANELLE
Jacques Marcel Arthur Bunel
Faouzi ALIOUAT
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3584413A1 publication Critical patent/EP3584413A1/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
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F05D2230/70—Disassembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the present invention relates to an annular casting and shrink-wrapped part of an aircraft turbomachine.
  • the state of the art includes in particular the documents EP-A1-3 048 270 , WO-A1-2016 / 051080 and EP-B1-1 931 859 .
  • An aircraft turbomachine comprises several annular parts, such as, for example, casings, abradable coating supports, etc., which are coaxial and extend around the longitudinal axis of the turbomachine, which is generally coincident with the axis of rotation of its main rotor or of its main rotors.
  • the abradable housings and supports must be well centered and sealed against each other. For this, they are mounted hooped with each other. This is particularly important for abradable mounts which provide a seal between moving and stationary parts of the engine.
  • a turbomachine can be made by foundry.
  • the foundry operation requires the presence of specific protruding studs on the parts which have a dual function. These studs first serve as a reference for checking the part after manufacture, and also serve during the manufacture of the part. These studs must therefore be kept during the life of the part. They are however relatively bulky and should ideally be located on the workpiece flange to meet the needs of the foundry.
  • one of the shrink-wrapped flanges must include extraction sleeves as well as notches for the passage of extraction sleeves from another flange on which this flange is shrunk.
  • the present invention provides a simple, efficient and economical solution to this problem.
  • the invention relates to a part for a turbomachine, this part having a general annular shape around an axis of revolution, this part comprising a first annular flange for fixing by shrinking and comprising an annular row of screw holes, this part part being produced by foundry and comprising projecting studs necessary for the control and production of the part by casting, characterized in that said studs are located on said flange and each comprise a tapping configured to cooperate with an extraction screw of the flange.
  • the invention is advantageous because it makes it possible to integrate the function of the extraction bushings of the prior art into the foundry pads.
  • the part therefore does not need extraction bushings strictly speaking, which frees space on its fixing flange by shrinking.
  • the pads thus have a dual function.
  • the invention also relates to an assembly comprising a part as described above, and a first annular element extending around said axis, the first flange of the part being shrunk and applied axially against a second annular flange of this first element of so that the threads of said studs are aligned with through holes of the second flange, these holes having a diameter smaller than that of said threads.
  • the present invention also relates to an aircraft turbomachine, comprising a part or an assembly as described above.
  • the extraction screw used in step c) may include the stopper and an extension having a predetermined length L1 which is configured to pass through the threads and part of the holes.
  • the stopper and the extension have a total predetermined length L2.
  • the figure 1 is a partial schematic view of a turbomachine and more exactly of a rear or downstream portion of the turbomachine, the upstream and downstream expressions taking account of the flow of gases in the turbomachine.
  • the gases flow from a fan inside a nacelle towards the interior and around a gas generator which successively comprises low pressure and high pressure compressors, a combustion chamber, high pressure and low pressure turbines, and a gas ejection nozzle.
  • references 10, 12 and 14 respectively denote an annular abradable coating support, an annular bearing support, and an internal casing of the high pressure turbine.
  • the support 10 has a generally cylindrical shape in the example shown and carries an abradable annular coating 16 at its downstream end.
  • the support 10 comprises at its upstream end a first flange 18.
  • the flange 18 comprises two radial faces, respectively upstream 18a and downstream 18b, and a radially internal cylindrical surface 18c for shrinking.
  • the face 18a and the surface 18c are connected to each other.
  • the support 12 has a generally frustoconical shape flared upstream in the example shown, and is here surrounded by the support 10. It comprises at its upstream end a second flange 20.
  • the flange 20 comprises two radial faces, respectively upstream 20a. and downstream support 20b, as well as two cylindrical bearing surfaces, respectively upstream 20c and downstream 20d, for shrinking.
  • the face 20a and the bearing 20c are connected together, and the face 20b and the bearing 20d are connected together ( figure 4 ).
  • the casing 14 has a generally frustoconical shape flared towards the downstream in the example shown and comprises at its upstream end a third flange 22.
  • the flange 22 comprises two radial faces, respectively downstream 22b and upstream 22a support, and a surface radially internal cylindrical hooping 22c.
  • the face 22b and the surface 22c are connected to each other ( figure 4 ).
  • the flanges 18, 20 and 22 comprise aligned holes for the passage of fixing screws 24 whose heads 24a bear for example on the downstream radial face 18b of the first flange 18, and whose threaded bodies receive nuts 24b which bear on the upstream radial face 22a of the third flange 22 ( figure 4 ).
  • the flanges 18, 20, 22 are shrink-wrapped, that is to say they are fixed together by radial clamping one on the other.
  • the part intended to be fixed on another part is heated to expand it and facilitate its engagement on the other part. As it cools, the part retracts and tightens radially against the other part.
  • the flange 18 is shrunk by its surface 18c on the surface 20d of the flange 20, and the flange 22 is shrunk by its surface 22c on the surface 20c of the flange 20.
  • the flange 20 is interposed between the flanges 18, 22 and its radial faces 20a, 20b bear on the flanges 22, 18 respectively and therefore does not include any projections.
  • one of the other parts such as for example the support 10 is produced from a foundry and comprises on its downstream radial face 18b projecting studs 26 (visible at figure 3 ) which are necessary for checking the part and for manufacturing the part.
  • the pads 26 have a general parallelepipedal shape in the example shown.
  • these flanges must be equipped with extraction means, that is to say means capable of generating a sufficient axial separation force between two parts in order to to extract them from one another by defrosting them.
  • these extraction means comprise attached bushings 28, visible at the figure 2 .
  • These bushes 28 are mounted crimped in holes of a flange and receive screws which are intended to bear on a flange adjacent to the flange carrying the bushes, so as to apply the aforementioned separation force.
  • the flange which carries the studs 26 does not include extraction bushings 28 because the function of these bushings is integrated into the plots.
  • the studs 26 indeed include threads 30 for screwing the extraction screw, as can be seen in figure 3 .
  • the threads 30 are through and threaded to cooperate with the extraction screws which are intended to bear on at least one of the other flanges 20, 22 of the assembly.
  • the threads 30 are oriented axially, that is to say parallel to the axis of revolution and assembly of the parts.
  • the extraction screws are screwed from downstream into the threads 30 in the example shown.
  • FIGS. 5a to 5e illustrate disassembly steps of a first embodiment of a method according to the invention, only the support 10 being disassembled and therefore separated from the other two parts (support 12 and casing 14).
  • Each extraction screw 32 has a generally cylindrical shape and comprises a threaded body 32b, one longitudinal end of which is connected to a drive head 32c and of which an opposite longitudinal end comprises an axial extension 32a having a diameter smaller than that of the body.
  • the flange 20 comprises through holes 34 aligned with the threads 30 of the flange 18. These holes 34 are not threaded and have an internal diameter smaller than that of the threads 30, and between the diameter of the extension 32a and the diameter of the body 32b of the screw 32. It is also noted that each thread 30 is connected to a hole 34 by an annular cavity 36 which is located at the interface between the flanges 18, 20. This cavity 36 has a diameter greater than the diameters of the hole 34 and of the thread 30 and comprises a half-portion formed by a hollow on the downstream radial face 20b of the flange 20 and another half-portion formed by a hollow on the upstream radial face 18a of the flange 18 ( figure 4 ).
  • the flange 22 comprises blind holes 38 aligned with the holes 34 and the internal threads 30. These holes 38 are not threaded and here have an internal diameter greater than the internal diameter of the holes 34.
  • the threads 30 are for example three in number regularly distributed around the axis of the support 10. It is therefore understood that the flange 20 in this case comprises three holes 34 and that the flange 22 comprises three holes 38.
  • Each screw 32 is first aligned with the axis of an internal thread 30 and then engaged by its extension 32a in this internal thread 30 ( figures 5a and 5b ).
  • the screw is screwed into the thread by means of a suitable tool in engagement with the drive head 32c, until the extension 32a engages the hole 34 and the end of the body 32b connected to the extension rest on the bottom of the hollow of the downstream radial face 20b of the flange 20 ( figures 5c and 5d ).
  • extension 32a has a length L1 less than the thickness E of the flange 20 (and more exactly, L1 is less than the thickness E 'remaining between the bottom of the forming hollow of the cavity 36 on the face 20b, and the opposite face 20a - figure 5d ) and does not risk coming into contact with the flange 22 during screwing. It is further understood that, for the sole removal of support 10, this extension 32a is not compulsory since it has no particular utility during this extraction.
  • FIG. 6a to 6h illustrate another embodiment of the method according to the invention which here consists in extracting the flanges 18, 22 from the flange 20 and therefore in completely disassembling the assembly.
  • the same screw 32 is used but is here equipped with a stop 40 which is removably mounted on the extension 32a.
  • This stopper has a generally cylindrical shape and is axially aligned with the extension 32a and the body 32b of the screw, the external diameter of this stopper being similar to that of the extension and therefore smaller than that of the body.
  • the total length L2 of the stop 40 and of the extension 32a is greater than the thickness E (E ') of the flange 20 so that the stop and the extension can be engaged in the hole 34 and pass through it. .
  • Each screw 32 is first aligned with the axis of an internal thread 30 then engaged by its extension 32a in this internal thread 30 ( figures 6a and 6b ). The screw is screwed into the tapping until the stop 40 and the extension 32a engage in the hole 34 and this stop rests on the bottom of the blind hole 38 of the downstream radial face 22b of the flange 22 ( figures 6c and 6d ).
  • the screw 32 is screwed again into the tapping 30 until the end of the body 32b connected to the extension 32a bears on the downstream radial face 20b of the flange 20 ( figures 6g ).

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention concerne une pièce annulaire de fonderie et frettée d'une turbomachine d'aéronefThe present invention relates to an annular casting and shrink-wrapped part of an aircraft turbomachine.

ETAT DE L'ARTSTATE OF THE ART

L'état de la technique comprend notamment les documents EP-A1-3 048 270 , WO-A1-2016/051080 et EP-B1-1 931 859 .The state of the art includes in particular the documents EP-A1-3 048 270 , WO-A1-2016 / 051080 and EP-B1-1 931 859 .

Une turbomachine d'aéronef comprend plusieurs pièces annulaires, telles que par exemple des carters, des supports de revêtement abradable, etc., qui sont coaxiaux et s'étendent autour de l'axe longitudinal de la turbomachine, qui est en général confondu avec l'axe de rotation de son rotor principal ou de ses rotors principaux.An aircraft turbomachine comprises several annular parts, such as, for example, casings, abradable coating supports, etc., which are coaxial and extend around the longitudinal axis of the turbomachine, which is generally coincident with the axis of rotation of its main rotor or of its main rotors.

Les carters et les supports abradables doivent être bien centrés et étanches entre eux. Pour cela, ils sont montés frettés les uns avec les autres. C'est particulièrement important pour les supports abradables qui assurent une étanchéité entre des parties mobiles et fixes du moteur.The abradable housings and supports must be well centered and sealed against each other. For this, they are mounted hooped with each other. This is particularly important for abradable mounts which provide a seal between moving and stationary parts of the engine.

Pour démonter ces pièces, il est connu de les équiper de douilles d'extraction. Ces douilles sont installées à intervalles réguliers sur des brides annulaires de fixation des pièces. Des vis dédiées à l'extraction des pièces sont vissées dans ces douilles pour démonter les pièces les unes des autres. Les vis sont en effet utilisées pour que le couple de serrage des vis soit transformé en un effort d'extraction suffisant pour vaincre les efforts de serrage des pièces liés au frettage.In order to dismantle these parts, it is known practice to equip them with extraction sleeves. These bushings are installed at regular intervals on annular workpiece fixing flanges. Dedicated screws for extracting the parts are screwed into these sockets to disassemble the parts from each other. The screws are in fact used so that the tightening torque of the screws is transformed into an extraction force sufficient to overcome the clamping forces of the parts linked to the shrinking.

Ces douilles d'extraction sont en général rapportées et fixées par sertissage sur les brides, à côté des orifices prévus sur cette bride pour le passage des vis de fixation de cette bride. C'est notamment le cas des pièces qui sont réalisées par forgeage.These extraction bushes are generally attached and fixed by crimping on the flanges, next to the orifices provided on this flange for the passage of the fixing screws of this flange. This is particularly the case with parts which are produced by forging.

Cependant, certaines pièces d'une turbomachine peuvent être réalisées par fonderie. Dans ce cas, l'opération de fonderie nécessite la présence de plots spécifiques en saillie sur les pièces qui ont une double fonction. Ces plots servent d'abord de référence au contrôle de la pièce après fabrication, et servent aussi pendant la fabrication de la pièce. Ces plots doivent donc être conservés lors de la vie de la pièce. Ils sont cependant relativement volumineux et doivent idéalement être situés sur la bride de la pièce pour répondre aux besoins de la fonderie.However, some parts of a turbomachine can be made by foundry. In this case, the foundry operation requires the presence of specific protruding studs on the parts which have a dual function. These studs first serve as a reference for checking the part after manufacture, and also serve during the manufacture of the part. These studs must therefore be kept during the life of the part. They are however relatively bulky and should ideally be located on the workpiece flange to meet the needs of the foundry.

Cependant, il est actuellement très difficile voire impossible, pour des raisons d'encombrement, de disposer sur une même bride d'une pièce obtenue de fonderie des orifices de passage des vis de fixation (liaisons boulonnées), des douilles d'extraction, des plots de fonderie, voire également d'autres organes tels que des nervures de rigidification.However, it is currently very difficult or even impossible, for reasons of space, to have on the same flange of a part obtained from foundry passage holes for fixing screws (bolted connections), extraction sleeves, foundry studs, or also other members such as stiffening ribs.

Ce problème est accentué lorsque plus de deux brides sont appliquées et fixées entre elles. Dans un tel cas, l'une des brides frettées doit comprendre des douilles d'extraction ainsi que des encoches de passage de douilles d'extraction d'une autre bride sur laquelle cette bride est frettée.This problem is accentuated when more than two clamps are applied and fixed between them. In such a case, one of the shrink-wrapped flanges must include extraction sleeves as well as notches for the passage of extraction sleeves from another flange on which this flange is shrunk.

La présente invention propose une solution simple, efficace et économique à ce problème.The present invention provides a simple, efficient and economical solution to this problem.

EXPOSE DE L'INVENTIONDISCLOSURE OF THE INVENTION

L'invention concerne une pièce pour une turbomachine, cette pièce ayant une forme générale annulaire autour d'un axe de révolution, cette pièce comportant une première bride annulaire de fixation par frettage et comportant une rangée annulaire d'orifices de passage de vis, cette pièce étant réalisée par fonderie et comportant des plots en saillie nécessaires au contrôle et à la réalisation de la pièce par fonderie, caractérisée en ce que lesdits plots sont situés sur ladite bride et comprennent chacun un taraudage configuré pour coopérer avec une vis d'extraction de la bride.The invention relates to a part for a turbomachine, this part having a general annular shape around an axis of revolution, this part comprising a first annular flange for fixing by shrinking and comprising an annular row of screw holes, this part part being produced by foundry and comprising projecting studs necessary for the control and production of the part by casting, characterized in that said studs are located on said flange and each comprise a tapping configured to cooperate with an extraction screw of the flange.

L'invention est avantageuse car elle permet d'intégrer la fonction des douilles d'extraction de la technique antérieure aux plots de fonderie. La pièce n'a donc pas besoin de douilles d'extraction à proprement parler, ce qui libère de l'espace sur sa bride de fixation par frettage. Les plots ont ainsi une double fonction.The invention is advantageous because it makes it possible to integrate the function of the extraction bushings of the prior art into the foundry pads. The part therefore does not need extraction bushings strictly speaking, which frees space on its fixing flange by shrinking. The pads thus have a dual function.

La pièce selon l'invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • la pièce porte un revêtement annulaire abradable,
  • la bride comprend une première face radiale d'appui sur une autre bride, et une face cylindrique radialement interne de frettage sur une portée cylindrique radialement externe de cette autre bride,
  • les plots sont en saillie sur une seconde face radiale, opposée à ladite première face radiale d'appui.
The part according to the invention may include one or more of the following characteristics, taken in isolation from one another or in combination with one another:
  • the part has an abradable annular coating,
  • the flange comprises a first radial bearing face on another flange, and a radially inner cylindrical face for shrinking on a radially outer cylindrical surface of this other flange,
  • the studs project from a second radial face, opposite to said first radial bearing face.

L'invention concerne également un ensemble comportant une pièce telle que décrite ci-dessus, et un premier élément annulaire s'étendant autour dudit axe, la première bride de la pièce étant frettée et appliquée axialement contre une deuxième bride annulaire de ce premier élément de façon à ce que les taraudages desdits plots soient alignés avec des trous traversants de la deuxième bride, ces trous ayant un diamètre inférieurs à celui desdits taraudages.The invention also relates to an assembly comprising a part as described above, and a first annular element extending around said axis, the first flange of the part being shrunk and applied axially against a second annular flange of this first element of so that the threads of said studs are aligned with through holes of the second flange, these holes having a diameter smaller than that of said threads.

L'ensemble selon l'invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • l'ensemble comprend un seconde élément annulaire s'étendant autour dudit axe et comportant une troisième bride frettée et appliquée axialement contre la deuxième bride, du côté opposé à la première bride, de façon à ce que les taraudages et lesdits trous traversants soient alignés avec des trous borgnes de la troisième bride, ces trous ayant un diamètre supérieur à celui desdits trous traversants,
  • lesdits trous traversants et/ou lesdits trous borgnes sont non taraudés,
  • ledit premier élément est un support de paliers et/ou ledit second élément est un carter de turbine,
  • l'ensemble comprend une cavité annulaire située à l'interface entre la première bride et la deuxième bride, et ladite cavité est configurée pour relier chaque taraudage desdits plots au trou de la deuxième bride,
    • ladite cavité comprend une demi-portion en creux sur une face radiale aval de la deuxième bride et une autre demi-portion en creux sur la première face radiale d'appui de la première bride,
    • ladite deuxième bride a une épaisseur prédéterminée E destinée à être supérieure à une longueur L1 d'un prolongement de la vis.
The assembly according to the invention can comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another:
  • the assembly comprises a second annular element extending around said axis and comprising a third shrink flange and applied axially against the second flange, on the side opposite the first flange, so that the threads and said through holes are aligned with blind holes in the third flange, these holes having a diameter greater than that of said through holes,
  • said through holes and / or said blind holes are not tapped,
  • said first element is a bearing support and / or said second element is a turbine housing,
  • the assembly comprises an annular cavity located at the interface between the first flange and the second flange, and said cavity is configured to connect each thread of said studs to the hole of the second flange,
    • said cavity comprises a hollow half-portion on a downstream radial face of the second flange and another hollow half-portion on the first radial bearing face of the first flange,
    • said second flange has a predetermined thickness E intended to be greater than a length L1 of an extension of the screw.

La présente invention concerne encore une turbomachine d'aéronef, comportant une pièce ou un ensemble tel que décrit ci-dessus.The present invention also relates to an aircraft turbomachine, comprising a part or an assembly as described above.

La présente invention concerne enfin un procédé de démontage d'une pièce dans un ensemble tel que décrit ci-dessus, comprenant les étapes de :

  1. a) insertion d'une vis d'extraction dans le taraudage de chacun des plots de la pièce,
  2. b) vissage des vis d'extraction dans les taraudages jusqu'à ce que leurs extrémités libres prennent appui sur la deuxième bride,
  3. c) poursuite du vissage des vis d'extraction de façon à ce que le couple de serrage de la vis génèrent une force d'extraction de la pièce par rapport à la deuxième bride et au premier élément,
  4. d) retrait de la pièce.
The present invention finally relates to a method of dismantling a part in an assembly as described above, comprising the steps of:
  1. a) insertion of an extraction screw in the tapping of each of the studs of the part,
  2. b) screwing the extraction screws into the threads until their free ends rest on the second flange,
  3. c) continuing to tighten the extraction screws so that the tightening torque of the screw generates an extraction force of the part with respect to the second flange and to the first element,
  4. d) removal of the part.

Le procédé peut comprendre en outre :

  • avant l'étape a),
    une étape de (i) montage d'une butée sur l'extrémité libre de chacune des vis d'extraction, de façon à les rallonger,
  • entre les étapes a) et c), des étapes de
    • (ii) vissage des vis d'extraction dans les taraudages jusqu'à ce que les butées prennent appui sur la troisième bride,
    • iii) poursuite du vissage des vis d'extraction de façon à ce que le couple de serrage de la vis génèrent une force d'extraction de la pièce et du premier élément par rapport à la troisième bride et au deuxième élément,
    • (iv) retrait de la pièce et du premier élément.
The method may further comprise:
  • before step a),
    a step of (i) mounting a stop on the free end of each of the extraction screws, so as to lengthen them,
  • between steps a) and c), steps of
    • (ii) screwing the extraction screws into the threads until the stops bear on the third flange,
    • iii) continuing to tighten the extraction screws so that the tightening torque of the screw generates an extraction force of the part and of the first element with respect to the third flange and the second element,
    • (iv) removal of the part and the first element.

La vis d'extraction utilisée à l'étape c) peut comprendre la butée et un prolongement ayant une longueur prédéterminée L1 qui est configuré pour traverser les taraudages et une partie des trous. De préférence, la butée et le prolongement ont une longueur prédéterminée totale L2.The extraction screw used in step c) may include the stopper and an extension having a predetermined length L1 which is configured to pass through the threads and part of the holes. Preferably, the stopper and the extension have a total predetermined length L2.

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 :

  • la figure 1 est une vue schématique partielle en coupe axiale d'une turbomachine d'aéronef,
  • la figure 2 est une vue schématique partielle en perspective d'une bride annulaire d'une pièce selon la technique antérieure,
  • la figure 3 est une vue schématique partielle en perspective d'une bride annulaire d'une pièce selon l'invention,
  • la figure 4 est une vue très schématique en coupe axiale et en perspective de brides frettées selon une ensemble conforme à l'invention,
  • les figures 5a à 5e sont des vues très schématiques en coupe axiale de l'ensemble de la figure 4, et illustrent des étapes de démontage et en particulier d'extraction d'une première bride, et
  • les figures 6a à 6h sont des vues très schématiques en coupe axiale de l'ensemble de la figure 4, et illustrent des étapes de démontage et en particulier d'extraction d'une deuxième bride puis d'une première bride.
The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial schematic view in axial section of an aircraft turbomachine,
  • the figure 2 is a partial schematic perspective view of an annular flange of a part according to the prior art,
  • the figure 3 is a partial schematic view in perspective of an annular flange of a part according to the invention,
  • the figure 4 is a very schematic view in axial section and in perspective of hooped flanges according to an assembly according to the invention,
  • the figures 5a to 5e are very schematic views in axial section of the whole of the figure 4 , and illustrate steps for disassembling and in particular extracting a first flange, and
  • the figures 6a to 6h are very schematic views in axial section of the whole of the figure 4 , and illustrate steps for dismantling and in particular extracting a second flange and then a first flange.

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

La figure 1 est une vue schématique partielle d'une turbomachine et plus exactement d'une portion arrière ou aval de la turbomachine, les expressions amont et aval tenant compte de l'écoulement des gaz dans la turbomachine. Dans le cas d'une turbomachine classique, par exemple à double corps et double flux, les gaz s'écoulent depuis une soufflante à l'intérieur d'une nacelle vers l'intérieur et autour d'un générateur de gaz qui comprend successivement des compresseurs basse pression et haute pression, une chambre de combustion, des turbines haute pression et basse pression, et une tuyère d'éjection des gaz.The figure 1 is a partial schematic view of a turbomachine and more exactly of a rear or downstream portion of the turbomachine, the upstream and downstream expressions taking account of the flow of gases in the turbomachine. In the case of a conventional turbomachine, for example with a double body and double flow, the gases flow from a fan inside a nacelle towards the interior and around a gas generator which successively comprises low pressure and high pressure compressors, a combustion chamber, high pressure and low pressure turbines, and a gas ejection nozzle.

Dans la figure 1, les références 10, 12 et 14 désignent respectivement un support annulaire de revêtement abradable, un support annulaire de paliers, et un carter interne de la turbine haute pression.In the figure 1 , the references 10, 12 and 14 respectively denote an annular abradable coating support, an annular bearing support, and an internal casing of the high pressure turbine.

Ces trois pièces annulaires sont centrées sur l'axe longitudinal de la turbomachine et sont assemblées les unes aux autres par frettage et fixation de brides.These three annular parts are centered on the longitudinal axis of the turbomachine and are assembled to each other by shrinking and fixing flanges.

Le support 10 a une forme générale cylindrique dans l'exemple représenté et porte un revêtement annulaire abradable 16 à son extrémité aval. Le support 10 comprend à son extrémité amont une première bride 18. La bride 18 comprend deux faces radiales, respectivement amont 18a d'appui et aval 18b, et une surface cylindrique radialement interne 18c de frettage. La face 18a et la surface 18c sont reliées l'une à l'autre.The support 10 has a generally cylindrical shape in the example shown and carries an abradable annular coating 16 at its downstream end. The support 10 comprises at its upstream end a first flange 18. The flange 18 comprises two radial faces, respectively upstream 18a and downstream 18b, and a radially internal cylindrical surface 18c for shrinking. The face 18a and the surface 18c are connected to each other.

Le support 12 a une forme générale tronconique évasée vers l'amont dans l'exemple représenté, et est ici entouré par le support 10. Il comprend à son extrémité amont une deuxième bride 20. La bride 20 comprend deux faces radiales, respectivement amont 20a et aval 20b d'appui, ainsi que deux portées cylindriques, respectivement amont 20c et aval 20d, de frettage. La face 20a et la portée 20c sont reliées ensemble, et la face 20b et la portée 20d sont reliées ensemble (figure 4).The support 12 has a generally frustoconical shape flared upstream in the example shown, and is here surrounded by the support 10. It comprises at its upstream end a second flange 20. The flange 20 comprises two radial faces, respectively upstream 20a. and downstream support 20b, as well as two cylindrical bearing surfaces, respectively upstream 20c and downstream 20d, for shrinking. The face 20a and the bearing 20c are connected together, and the face 20b and the bearing 20d are connected together ( figure 4 ).

Le carter 14 a une forme générale tronconique évasée vers l'aval dans l'exemple représenté et comprend à son extrémité amont une troisième bride 22. La bride 22 comprend deux faces radiales, respectivement aval 22b d'appui et amont 22a, et une surface cylindrique radialement interne 22c de frettage. La face 22b et la surface 22c sont reliées l'une à l'autre (figure 4).The casing 14 has a generally frustoconical shape flared towards the downstream in the example shown and comprises at its upstream end a third flange 22. The flange 22 comprises two radial faces, respectively downstream 22b and upstream 22a support, and a surface radially internal cylindrical hooping 22c. The face 22b and the surface 22c are connected to each other ( figure 4 ).

Les brides 18, 20 et 22 comprennent des orifices alignés de passage de vis de fixation 24 dont les têtes 24a prennent appui par exemple sur la face radiale aval 18b de la première bride 18, et dont les corps filetés reçoivent des écrous 24b qui prennent appui sur la face radiale amont 22a de la troisième bride 22 (figure 4).The flanges 18, 20 and 22 comprise aligned holes for the passage of fixing screws 24 whose heads 24a bear for example on the downstream radial face 18b of the first flange 18, and whose threaded bodies receive nuts 24b which bear on the upstream radial face 22a of the third flange 22 ( figure 4 ).

En plus d'être fixées par boulonnage, les brides 18, 20, 22 sont frettées, c'est-à-dire qu'elles sont fixées ensemble par serrage radial l'une sur l'autre. Pour cela, la pièce destinée à être fixée sur une autre pièce est chauffée pour la dilater et faciliter son engagement sur l'autre pièce. Lors de son refroidissement, la pièce se rétracte et se serre radialement contre l'autre pièce.In addition to being fixed by bolting, the flanges 18, 20, 22 are shrink-wrapped, that is to say they are fixed together by radial clamping one on the other. For this, the part intended to be fixed on another part is heated to expand it and facilitate its engagement on the other part. As it cools, the part retracts and tightens radially against the other part.

Dans l'exemple représenté, la bride 18 est frettée par sa surface 18c sur la portée 20d de la bride 20, et la bride 22 est frettée par sa surface 22c sur la portée 20c de la bride 20.In the example shown, the flange 18 is shrunk by its surface 18c on the surface 20d of the flange 20, and the flange 22 is shrunk by its surface 22c on the surface 20c of the flange 20.

La bride 20 est intercalée entre les brides 18, 22 et ses faces radiales 20a, 20b sont en appui sur les brides 22, 18 respectivement et ne comprend donc pas de saillies.The flange 20 is interposed between the flanges 18, 22 and its radial faces 20a, 20b bear on the flanges 22, 18 respectively and therefore does not include any projections.

Selon l'invention, une des autres pièces telles que par exemple le support 10 est réalisé de fonderie et comprend sur sa face radiale aval 18b des plots 26 en saillie (visibles à la figure 3) qui sont nécessaires au contrôle de la pièce et à la fabrication de la pièce. Les plots 26 ont une forme générale parallélépipédique dans l'exemple représenté.According to the invention, one of the other parts such as for example the support 10 is produced from a foundry and comprises on its downstream radial face 18b projecting studs 26 (visible at figure 3 ) which are necessary for checking the part and for manufacturing the part. The pads 26 have a general parallelepipedal shape in the example shown.

Par ailleurs, du fait du montage par frettage des brides 18, 20, 22, ces brides doivent être équipées de moyens d'extraction c'est-à-dire de moyens aptes à générer une force d'écartement axial suffisante entre deux pièces afin de les extraire l'une de l'autre en les défrettant.Furthermore, due to the mounting by shrinking of the flanges 18, 20, 22, these flanges must be equipped with extraction means, that is to say means capable of generating a sufficient axial separation force between two parts in order to to extract them from one another by defrosting them.

De manière classique, ces moyens d'extraction comprennent des douilles 28 rapportées, visibles à la figure 2. Ces douilles 28 sont montées serties dans des orifices d'une bride et reçoivent des vis qui sont destinées à prendre appui sur une bride adjacente à la bride portant les douilles, de façon à appliquer la force d'écartement précitée.Conventionally, these extraction means comprise attached bushings 28, visible at the figure 2 . These bushes 28 are mounted crimped in holes of a flange and receive screws which are intended to bear on a flange adjacent to the flange carrying the bushes, so as to apply the aforementioned separation force.

Selon l'invention, la bride qui porte les plots 26 ne comporte pas de douilles d'extraction 28 car la fonction de ces douilles est intégrée aux plots. Les plots 26 comportent en effet des taraudages 30 de vissage de vis d'extraction, comme cela est visible à la figure 3.According to the invention, the flange which carries the studs 26 does not include extraction bushings 28 because the function of these bushings is integrated into the plots. The studs 26 indeed include threads 30 for screwing the extraction screw, as can be seen in figure 3 .

Les taraudages 30 sont traversants et filetés pour coopérer avec les vis d'extraction qui sont destinées à prendre appui sur au moins une des autres brides 20, 22 de l'assemblage. Les taraudages 30 sont orientés axialement c'est-à-dire parallèlement à l'axe de révolution et d'assemblage des pièces. Les vis d'extraction sont vissées depuis l'aval dans les taraudages 30 dans l'exemple représenté.The threads 30 are through and threaded to cooperate with the extraction screws which are intended to bear on at least one of the other flanges 20, 22 of the assembly. The threads 30 are oriented axially, that is to say parallel to the axis of revolution and assembly of the parts. The extraction screws are screwed from downstream into the threads 30 in the example shown.

Les figures 5a à 5e illustrent des étapes de démontage d'un premier mode de réalisation d'un procédé selon l'invention, seul le support 10 étant démonté et donc séparé des deux autres pièces (support 12 et carter 14).The figures 5a to 5e illustrate disassembly steps of a first embodiment of a method according to the invention, only the support 10 being disassembled and therefore separated from the other two parts (support 12 and casing 14).

Chaque vis d'extraction 32 a une forme générale cylindrique et comporte un corps fileté 32b dont une extrémité longitudinale est reliée à une tête d'entraînement 32c et dont une extrémité longitudinale opposée comprend un prolongement axial 32a ayant un diamètre inférieur à celui du corps.Each extraction screw 32 has a generally cylindrical shape and comprises a threaded body 32b, one longitudinal end of which is connected to a drive head 32c and of which an opposite longitudinal end comprises an axial extension 32a having a diameter smaller than that of the body.

On constate que la bride 20 comprend des trous traversants 34 alignés avec les taraudages 30 de la bride 18. Ces trous 34 ne sont pas taraudés et ont un diamètre interne inférieur à celui des taraudages 30, et compris entre le diamètre du prolongement 32a et le diamètre du corps 32b de la vis 32. On constate également que chaque taraudage 30 est relié à un trou 34 par une cavité annulaire 36 qui est située à l'interface entre les brides 18, 20. Cette cavité 36 a un diamètre supérieur aux diamètres du trou 34 et du taraudage 30 et comprend une demi-portion formée par un creux sur la face radiale aval 20b de la bride 20 et une autre demi-portion formée par un creux sur la face radiale amont 18a de la bride 18 (figure 4).It can be seen that the flange 20 comprises through holes 34 aligned with the threads 30 of the flange 18. These holes 34 are not threaded and have an internal diameter smaller than that of the threads 30, and between the diameter of the extension 32a and the diameter of the body 32b of the screw 32. It is also noted that each thread 30 is connected to a hole 34 by an annular cavity 36 which is located at the interface between the flanges 18, 20. This cavity 36 has a diameter greater than the diameters of the hole 34 and of the thread 30 and comprises a half-portion formed by a hollow on the downstream radial face 20b of the flange 20 and another half-portion formed by a hollow on the upstream radial face 18a of the flange 18 ( figure 4 ).

La bride 22 comprend des trous borgnes 38 alignés avec les trous 34 et les taraudages 30. Ces trous 38 ne sont pas filetés et ont ici un diamètre interne supérieur au diamètre interne des trous 34.The flange 22 comprises blind holes 38 aligned with the holes 34 and the internal threads 30. These holes 38 are not threaded and here have an internal diameter greater than the internal diameter of the holes 34.

Les taraudages 30 sont par exemple au nombre de trois régulièrement répartis autour de l'axe du support 10. On comprend donc que la bride 20 comprend dans ce cas trois trous 34 et que la bride 22 comprend trois trous 38.The threads 30 are for example three in number regularly distributed around the axis of the support 10. It is therefore understood that the flange 20 in this case comprises three holes 34 and that the flange 22 comprises three holes 38.

Chaque vis 32 est d'abord alignée sur l'axe d'un taraudage 30 puis engagée par son prolongement 32a dans ce taraudage 30 (figures 5a et 5b). La vis est vissée dans le taraudage au moyen d'un outil approprié en prise avec la tête d'entraînement 32c, jusqu'à ce que le prolongement 32a s'engage dans le trou 34 et que l'extrémité du corps 32b reliée au prolongement prenne appui sur le fond du creux de la face radiale aval 20b de la bride 20 (figures 5c et 5d).Each screw 32 is first aligned with the axis of an internal thread 30 and then engaged by its extension 32a in this internal thread 30 ( figures 5a and 5b ). The screw is screwed into the thread by means of a suitable tool in engagement with the drive head 32c, until the extension 32a engages the hole 34 and the end of the body 32b connected to the extension rest on the bottom of the hollow of the downstream radial face 20b of the flange 20 ( figures 5c and 5d ).

Il suffit alors d'appliquer un couple de serrage suffisant à la vis 32 afin qu'une force d'extraction soit appliquée au support (flèche F1) en vue de l'écartement axial des brides 18, 20 jusqu'à ce que la surface 18c de la bride ne soit plus au contact de la portée 20d de la bride 20.It is then sufficient to apply a sufficient tightening torque to the screw 32 so that an extraction force is applied to the support (arrow F1) with a view to the axial separation of the flanges 18, 20 until the surface 18c of the flange is no longer in contact with the seating surface 20d of the flange 20.

Cette opération peut être ici rendue possible par le fait que le prolongement 32a a une longueur L1 inférieure à l'épaisseur E de la bride 20 (et plus exactement, L1 est inférieure à l'épaisseur E' restante entre le fond du creux de formation de la cavité 36 sur la face 20b, et la face 20a opposée - figure 5d) et ne risque pas de venir au contact de la bride 22 lors du vissage. On comprend en outre que, pour le seul démontage du support 10, ce prolongement 32a n'est pas obligatoire puisqu'il n'a pas d'utilité particulière lors de cette extraction.This operation can be made possible here by the fact that the extension 32a has a length L1 less than the thickness E of the flange 20 (and more exactly, L1 is less than the thickness E 'remaining between the bottom of the forming hollow of the cavity 36 on the face 20b, and the opposite face 20a - figure 5d ) and does not risk coming into contact with the flange 22 during screwing. It is further understood that, for the sole removal of support 10, this extension 32a is not compulsory since it has no particular utility during this extraction.

Les figures 6a à 6h illustrent un autre mode de réalisation du procédé selon l'invention qui consiste ici à extraire les brides 18, 22 de la bride 20 et donc à démonter entièrement l'assemblage.The figures 6a to 6h illustrate another embodiment of the method according to the invention which here consists in extracting the flanges 18, 22 from the flange 20 and therefore in completely disassembling the assembly.

Pour cela, la même vis 32 est utilisée mais est ici équipée d'une butée 40 qui est montée de manière amovible sur le prolongement 32a. Cette butée a une forme générale cylindrique et est alignée axialement sur le prolongement 32a et le corps 32b de la vis, le diamètre externe de cette butée étant similaire à celui du prolongement et donc inférieur à celui du corps.For this, the same screw 32 is used but is here equipped with a stop 40 which is removably mounted on the extension 32a. This stopper has a generally cylindrical shape and is axially aligned with the extension 32a and the body 32b of the screw, the external diameter of this stopper being similar to that of the extension and therefore smaller than that of the body.

De préférence, la longueur totale L2 de la butée 40 et du prolongement 32a est supérieure à l'épaisseur E (E') de la bride 20 de façon à ce que la butée et le prolongement puissent être engagés dans le trou 34 et le traverser.Preferably, the total length L2 of the stop 40 and of the extension 32a is greater than the thickness E (E ') of the flange 20 so that the stop and the extension can be engaged in the hole 34 and pass through it. .

Chaque vis 32 est d'abord alignée avec l'axe d'un taraudage 30 puis engagée par son prolongement 32a dans ce taraudage 30 (figures 6a et 6b). La vis est vissée dans le taraudage jusqu'à ce que la butée 40 et le prolongement 32a s'engagent dans le trou 34 et que cette butée prenne appui sur le fond du trou borgne 38 de la face radiale aval 22b de la bride 22 (figures 6c et 6d).Each screw 32 is first aligned with the axis of an internal thread 30 then engaged by its extension 32a in this internal thread 30 ( figures 6a and 6b ). The screw is screwed into the tapping until the stop 40 and the extension 32a engage in the hole 34 and this stop rests on the bottom of the blind hole 38 of the downstream radial face 22b of the flange 22 ( figures 6c and 6d ).

Il suffit alors d'appliquer un couple de serrage suffisant à la vis 32 afin qu'une force d'extraction soit appliquée au support (flèche F2) en vue de l'écartement axial des brides 18, 20, d'une part, de la bride 22, d'autre part, jusqu'à ce que la surface 22c de la bride 22 ne soit plus au contact de la portée 20c de la bride 20.It is then sufficient to apply a sufficient tightening torque to the screw 32 so that an extraction force is applied to the support (arrow F2) with a view to the axial separation of the flanges 18, 20, on the one hand, to the flange 22, on the other hand, until the surface 22c of the flange 22 is no longer in contact with the surface 20c of the flange 20.

La vis 32 est vissée à nouveau dans le taraudage 30 jusqu'à ce que l'extrémité du corps 32b reliée au prolongement 32a prenne appui sur la face radiale aval 20b de la bride 20 (figures 6g).The screw 32 is screwed again into the tapping 30 until the end of the body 32b connected to the extension 32a bears on the downstream radial face 20b of the flange 20 ( figures 6g ).

Il suffit alors d'appliquer un nouveau couple de serrage suffisant à la vis 32 afin qu'une force d'extraction soit appliquée au support (flèche F1) en vue de l'écartement axial des brides 18, 20, jusqu'à ce que la surface 18c de la bride 18 ne soit plus au contact de la portée 20d de la bride 20 (figure 6h).It then suffices to apply a new sufficient tightening torque to the screw 32 so that an extraction force is applied to the support (arrow F1) for the axial separation of the flanges 18, 20, until the surface 18c of the flange 18 is no longer in contact with the surface 20d of the flange 20 ( figure 6h ).

Claims (15)

  1. Part (10) for a turbine engine, this part having a general annular shape about an axis of revolution, this part comprising a first annular shrink-fitted fastening flange (18) and comprising an annular row of orifices for the passage of screws (24), this part being made by casting and comprising protruding pads (26) necessary for the control and the manufacture of the part by casting, characterised in that said pads are located on said flange and in that each comprises an thread (30) configured to engage with an extraction screw (32) of the flange.
  2. Part (10) according to claim 1, wherein the part bears an abradable annular coating (16).
  3. Part (10) according to claim 1 or 2, wherein the flange (18) comprises a first radial face (18a) bearing against another flange (20), and an internal radially cylindrical face (18c) shrink-fitted on a radially external cylindrical bearing (20d) of this other flange.
  4. Part (10) according to claim 3, wherein the pads (26) protrude on a second radial face (18b), opposite said first radial bearing face (18a).
  5. Assembly comprising a part (10) according to one of the preceding claims, and a first annular element (12) extending about said axis, the first flange (18) of the part (10) being shrink-fitted and axially applied against a second annular flange (20) of this first element (12) such that the threads (30) of said pads (26) are aligned with the through-holes (34) of the second flange, these holes having a diameter less than that of said threads.
  6. Assembly according to claim 5, wherein it comprises a second annular element (14) extending about said axis and comprising a third shrink-fitted flange (22) applied axially against the second flange (20), on the opposite side of the first flange (18), such that the threads (30) and said through-holes (34) are aligned with the blind holes (38) of the third flange, these holes having a diameter greater than that of said through holes.
  7. Assembly according to claim 5 or 6, wherein said through-holes (34) and/or said blind holes (38) are not threaded.
  8. Assembly according to one of claims 5 to 7, wherein said first element is a bearing support (12) and/or said second element is a turbine casing (14).
  9. Assembly according to one of claims 5 to 8, characterised in that it comprises an annular cavity (36) located at the interface between the first flange (18) and the second flange (20), and said cavity (36) is configured to connect each thread (30) of said pads (26) to the hole (34) of the second flange (20).
  10. Assembly according to claim 9, characterised in that said cavity (36) comprises a half portion in recess on a downstream radial face (20b) of the second flange (20), and another half portion in recess on the first radial bearing face (18a) of the first flange (18).
  11. Assembly according to one of claims 5 to 10, characterised in that said second flange (20) has a predetermined thickness E intended to be greater than a length L1 of an extension (32a) of the screw (32).
  12. Aircraft turbine engine, comprising a part according to one of the claims 1 to 4 or an assembly according to one of claims 5 to 8.
  13. Method for disassembling a part (10) in an assembly according to one of claims 5 to 8, comprising the steps of:
    a) inserting an extraction screw (32) in the thread (30) of each pad (26) of the part,
    b) screwing the extraction screws into the threads until the free ends thereof come to bear against the second flange (20),
    c) continuing to screw the extraction screws such that the screwing torque of the screws generates an extraction force of the part with respect to the second flange and to the first element (12),
    d) removing the part (10).
  14. Method according to claim 10, further comprising
    - prior to step a),
    a step of (i) mounting an abutment (40) on the free end of each of the extraction screws (32), thereby extending them,
    - between steps a) and c), steps of
    (ii) screwing the extraction screws into the threads (30) until the abutments come to bear against the third flange (22),
    iii) continuing to screw the extraction screws such that the screwing torque of the screws generates an extraction force of the part and of the first element (12) with respect to the third flange (22) and to the second element (14),
    (iv) removing the part (10) and the first element (12).
  15. Method according to claim 14, characterised in that the extraction screw (32) used in step c) comprises the abutment (40) and an extension (32a) having a predetermined length L1 that is configured to pass through the threads (30) and a part of the holes (34); and in that the abutment (40) and the extension (32a) have a total predetermined length L2.
EP19180983.9A 2018-06-20 2019-06-18 Cast and shrink-fit annular part of an aircraft turbine engine Active EP3584413B1 (en)

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FR1855461A FR3082874B1 (en) 2018-06-20 2018-06-20 FOUNDRY AND FREIGHT ANNULAR PART OF AN AIRCRAFT TURBOMACHINE

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US10920619B2 (en) 2021-02-16
US20190390571A1 (en) 2019-12-26
EP3584413A1 (en) 2019-12-25
FR3082874A1 (en) 2019-12-27
FR3082874B1 (en) 2020-09-04

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