EP0651139B1 - Turbomachine with means to control the tip clearance between rotor and stator - Google Patents

Turbomachine with means to control the tip clearance between rotor and stator Download PDF

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Publication number
EP0651139B1
EP0651139B1 EP94402400A EP94402400A EP0651139B1 EP 0651139 B1 EP0651139 B1 EP 0651139B1 EP 94402400 A EP94402400 A EP 94402400A EP 94402400 A EP94402400 A EP 94402400A EP 0651139 B1 EP0651139 B1 EP 0651139B1
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EP
European Patent Office
Prior art keywords
ring
ring sector
shroud
screw
turbomachine according
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.)
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Application number
EP94402400A
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German (de)
French (fr)
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EP0651139A1 (en
Inventor
Daniel Jean Marey
Fabrice Marois
Gérard Gabriel Miraucourt
Jean-Louis Charbonnel
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • 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

Definitions

  • the subject of the present invention is a turbomachine comprising games control means between stator and rotor and, more precisely, between the stator and the top of the rotor moving blades.
  • the major warm-ups to which a aircraft engine turbomachine is subject cause generally thermal expansions that it is higher interest to be able to control to avoid, in in particular, gas leaks between the rotor and the structure of the stator which surrounds it as well as the losses of efficiency, following these gas leaks.
  • Aircraft engines (especially those used for propulsion of jet airplanes) must be able to operate under conditions which can vary quickly. These variations of operating conditions can be a runaway of the cold rotor, a stroke of the throttle, runaway hot rotor, or any other operating conditions well known to man of the job.
  • stator in such a way that it is possible to circulate there gas, taken for example from another location in the machine, at a temperature and flow that produce at will a heating or cooling capable of adjust the expansion of the ferrule and therefore its play with the moving blades.
  • Such a variable temperature air shipment on the structure of the rectifier support allows, by a variation in the speed of expansion and contraction of the structure, to accommodate different engine operating conditions.
  • this is generally made of a single piece; it is therefore a 360 ° housing of circumference.
  • FR-2 683 851, FR-2 516 980 and FR-2 482 661 describe turbomachinery whose stators have double skin housings extending around the rotors on a full circumference, the air heating or cooling between the two crankcase skins.
  • shell elements or shell sectors
  • the shell elements may undergo displacements which harm the circularity of the structure.
  • the document GB-2 115 487 describes stator rings fitted by dovetail in supports.
  • the document FR-2 482 662 describes a stator ring segmented and pierced with orifices.
  • turbomachine comprising a stator whose 360 ° circumference housing and components ferrule are linked via a fixed point and sliding supports ensuring flexibility of the shell circumferential.
  • This turbomachine is characterized by the fact that it has a support ring housed between the casing and the ferrule, integral with said ferrule and comprising a plurality of circular ring sectors each attached to the casing by a fixed point means (10) and at least two sliding support means (11) located on either side else of the fixed point means to ensure the ferrule circumferential flexibility relative to the casing.
  • the turbomachine comprises a ring of support housed between the casing and the ferrule and comprising a plurality of fixed circular ring sectors each on the housing by means of a fixed point and sliding supports having a shaped section of a U whose opening is directed towards the shell, each shell element comprising means hooking able to be introduced into the opening at least one ring sector for securing said ring area and ferrule element.
  • each ring sector has an upstream wing and a wing downstream, each of said upstream and downstream wings comprising first recesses open radially towards the ferrule to provide circumferential flexibility audit ring sector.
  • the upstream wing has, in in addition, second recesses.
  • the turbomachine comprises clamping means in support of on either side of each ring sector to ensure securing said ring sector with the means of attachment of the ferrule element.
  • clamping means comprise a screw and a conical nut inserted inside the sector ring and able to deviate during the introduction of the screw, the base of said nut then being supported on the internal faces of the ring sector.
  • each element of ferrule constitute, with the ends of the wings upstream and downstream of the ring sector in which it is introduced, a dovetail assembly.
  • each means point system has a screw / nut system ensuring a seamless connection of a ring sector with the casing, the nut being introduced inside the ring by the second recess and arranged in support on an internal face of the core of the ring sector.
  • the screw can be, for example, introduced in the ring sector with a neighboring inclination 45 ° to the radial direction.
  • She can, according to another example, to be introduced radially in the ring sector, the nut then having a shape conical, the base of which is directed towards the shell.
  • the screw is then introduced into the sector ring with a longitudinal inclination of angle a, and the supporting parts have an inclined surface at an angle a to the radial direction.
  • the first recesses of the downstream wing are closed by sealing plates.
  • Each ring sector comprises, around the first recesses, grooves in which are positioned and fitted the sealing plates.
  • Each downstream wing of a ring sector can have an extension tab at one end and, at another end, machining ensuring a interlocking with covering of said ring sector in neighboring ring areas.
  • FIG 1 there is shown in section axial, a high pressure compressor having a housing exterior 1 of 360 ° circumference and means of piloting of games conforming to the first mode of realization of the invention.
  • This housing 1 has two envelopes (or two skins) concentric, slightly conical, separated by a volume (shown hatched in Figure 1) in which the heating air circulates or cooling.
  • This two-skin housing is type of that described in the document FR-2 683 851 cited previously; it will therefore not be described further in detail.
  • This casing 1 surrounds a plurality ferrule elements 2 which are substantially conical. These shell elements 2 are arranged end to end and assembled by interlocking joints 3 to form a single continuous ferrule and substantially parallel to the housing 1.
  • Each ferrule element 2 carries a stage stationary stator vanes 4, also called stage rectifier.
  • a stage of movable rotor blades 5 extends between each pair of stages of fixed blades 4.
  • FIG 1 there is also shown the rings 6 according to the first embodiment of the invention, these rings allowing displacements sensitive of the shell elements 2 according to the casing dilations and contractions 1.
  • These rings 6 each have a plurality of ring sectors arranged end to end and fitted into each other others to make continuous rings.
  • each ring 6 has a U-shaped section, the open side of the U being directed towards the shell 2.
  • Each ferrule element 2 has on its external face, i.e. on the face not bearing fixed vanes 4, attachment means 9 of the ring 6.
  • these attachment means 9 consist of a tenon 9a in dovetail adapted to be inserted into the opening of the ring 6.
  • the ends of the wings upstream 7 and downstream 8 of the ring 6 form a mortise 9b suitable for receiving the post 9a.
  • Mortise 9b and tenon 9a thus form a dovetail assembly.
  • clamping means not shown in this FIG. 1, pinch on both sides of the wings upstream 7 and downstream 8 of the ring 6 to ensure a securing of said ring 6 with the ferrule 2.
  • Each ring sector 6 is fixed to the casing by means of a fixed point 10 which will be described more in detail through the following figures.
  • Each ring sector is also fixed on the casing at means of sliding supports not shown on this Figure 1 but described in more detail below the description.
  • FIG 2 shows the angular distribution ferrule elements 2 and ring sectors 6 to inside the casing 1.
  • the ferrule 2 therefore comprises a plurality of shell elements, three of which are shown in Figure 2 and referenced 2a, 2b and 2c.
  • the ring 6 has a plurality of sectors of which four are shown in this figure 2 and referenced 6a, 6b, 6c and 6d.
  • each ring sector has a size equivalent to approximately two shell elements.
  • the ring sector 6a has two sliding supports 11a and 11b on either side of the point fixed 10a and two sliding supports 11c and 11d each of its ends.
  • All of these sliding supports ensure, for each ring sector, one displacement immediate circumferential (represented by arrows in FIG. 2) of the ring sector, and therefore of ferrule elements connected to this ring sector, by relative to the displacement of the housing.
  • each ring sector includes, indeed, a plurality of recesses, namely the recesses 12 only on the upstream wing and the recesses 13 on the upstream wing and on the downstream wing, these recesses providing circumferential flexibility at the ring area.
  • the ring sectors 6a, 6b, ... are assembled with neighboring ring sectors at level from the center of a recess 12.
  • Figure 3 shows a view in perspective of the ring sector 6a of FIG. 2.
  • This figure therefore shows the ring sector 6a cut at a recess 13, the casing 1 on which is fixed the ring sector 6a, as well as the ferrule 2 with its tenon 9a in dovetail around which fits the dovetail ends 9b of the upstream wings 7 and downstream 8.
  • the ring sector 6a is connected to the casing 1 via the point fixed 10a and several sliding supports including three are represented in this figure and referenced 11a, 11b and 11c.
  • This figure shows the recesses 12 of the upstream wing as well as the recesses 13 with their radial slot, these recesses 13 being also present on the downstream wing 8, but not visible on this perspective view of the ring sector 6a.
  • part A of the Figure 4 shows the outer face of the upstream wing 7 of the ring sector 6a.
  • This part A therefore shows the recesses 12 of the upstream wing 7 as well as the recesses 13 of this same upstream wing 7.
  • these recesses 13 include a radial opening 13a, or radial slot, starting from the internal part of the ring sector (i.e. the part of smaller diameter) and ending in the recess 13.
  • These radial slots give the ring 6 a circumferential flexibility.
  • Part B of Figure 4 shows the face internal of the downstream wing 8 of the ring sector 6a.
  • This downstream wing 8 has the recesses 13 with their radial slots 13a as well as screws 15 which pass through the ring sector right through and are fixed in the nuts 14 of the upstream wing 7.
  • Each associated screw 15 to a nut 14 constitutes the clamping means which pinch the ring sector around the dovetail tenon of the ferrule.
  • the sliding support is also represented on this part B of figure 4.
  • the screw 18a of the sliding support is inserted into a sole 18b surmounted by a projection pierced with a hole on the wall of which a thread has been made.
  • This sole 18b is supported on support pieces 19a and 19b arranged on either side of said hole in the sole 18b. These support pieces 19a and 19b are crossed by the screws 15, which secures said support pieces on the downstream wing 8.
  • An opening 21 is, in addition, produced in the core 20 of the ring sector; the sole 18b has, with the projection which surmounts it, a form of "pickaxe" able to pass partly into the opening 21 of the core 20 of the ring sector 6a to be in contact direct with the internal wall of the casing 1.
  • the parts sides of the sole 18b can therefore slide on these support pieces 19a and 19b thus creating a clearance circumference of the ring segment 6a with respect to the housing 1.
  • this sole 18b is a double span nut.
  • the supporting parts 19a and 19b form a angle of about 45 ° to the downstream wing 8 of so as to ensure a better sliding of the sole 18b.
  • This part B of FIG. 4 shows, in in addition, a sealing plate 25 which can be introduced into grooves (or slots) machined around recesses 13 in the downstream wing 8.
  • These grooves, referenced 26, are shown in dotted lines on the figure because they are made on the external face of the downstream wing 8.
  • the sealing plate 25 includes returns (dotted) suitable for entering the grooves 26 for positioning and the fitting of said sealing plates 25 in the downstream wing 8. The positioning of such plates sealing in front of the recesses 13 of the downstream wing 8 of ring sector 6a is intended to prevent possible reintroductions of gases from downstream to upstream of the ring.
  • the seal of the downstream wing of each ring sector is carried out by means of an annular seal 38 bearing on the part downstream of the dovetail assembly.
  • FIG 5 there is shown the means clamping in axial section.
  • these clamping means comprise a screw 15 introduced into the downstream wing 8 of the ring 6 and crossing said ring right through. This screw 15 is fixed in a nut 14 bearing on the external face upstream wing 7.
  • These clamping means allow thus compressing the mortise 9b produced by the wings 7 and 8 of the ring 6 against the tail 9a at the tail dovetail of the ferrule 2.
  • This fixed point 10 consists of a screw / nut system introduced into housing 1 and into ring 6 to secure them. More specifically, this screw / nut system includes a screw 16a introduced in the casing 1 and in the core 20 of the ring 6 by a breakthrough. A nut 16b introduced into the ring 6 by one recesses 12 of the upstream wing 7 ensures the fixing of the screw 16a. The screw 16a thus fixed in the nut 16b secures the ring 6 by its core 20 against the inner wall of the housing 1.
  • the nut 16b is of the lug nut type whose legs are fixed to the ring 6 by the rivets referenced 17a and 17b in Figure 4.
  • the screw 16a is introduced in housing 1 and ring 6 with an inclination longitudinal, the nut 16b having a shape suitable for receive the screw 16a thus inclined while having a solid support against the internal face of the core 20 of the ring 6.
  • the means for hooking the ferrule 2 with the ring 6 consist in a mortise 30b made in each element of ferrule 2 and a lug 30a produced by the ends internal of downstream 8 and upstream wings 7 of sectors ring.
  • the joining without play of each ring sector with the casing 1 is achieved by means a domed screw 32 introduced radially into the housing 1 and in the ring.
  • This screw is introduced in a nut 34 of conical shape whose base, directed towards the shell, is in contact with the internal faces upstream and downstream wings.
  • a lunule 36 is machined on the external face of each ferrule element.
  • screw 32 is tight, its curved end is supported in the lunula 36, the nut 34 rises and, by its taper, spreads the ring area thus realizing the connection without play between the shell element 2 and the ring sector 6.
  • a conical nut 34 is positioned astride two sectors allowing sectors to slide by compared to rings according to variations thermal.
  • This sliding support 11 consists of a screw / nut system in which the nut can move on supporting parts. More precise, this screw / nut system includes an 18a screw inserted in the casing 1 and in the projection of the sole 18b.
  • This sole consists of a base and of the projection located in the middle of the base. An opening 21 is produced in the core 20 of the ring 6, large enough to allow passage of the protrusion of the sole 18b which can thus be in contact with the internal wall of the casing 1.
  • An 18c nut secures the screw 18a in the sole 18b.
  • the base of the sole 18b is resting on two support pieces, of which only the piece support 19a is visible in this figure 8.
  • the projection of the sole 18b passing through the opening 21 of the core 20 and the base of said sole 18b being able to slide on the supporting parts, a circumferential clearance of the ring 6 relative to the casing 1 is then possible.
  • Such sliding supports 11 thus allow the displacement of the ring 6 and therefore of the shell 2 in function of thermal variations.
  • the support piece 19a, as well as all the supporting parts in the ring 6, are maintained integral with the ring by the clamping means 14, 15 which pass through said support pieces in their outer ends.
  • FIG. 9 represents a view in perspective of the support pieces and the sole of a sliding support. We therefore see, in this figure 9, the supporting parts 19a and 19b having a wall, inclined at 45 ° with respect to the radial direction, on which slides the base 18b 'of the sole 18b.
  • Figure 10 shows a view in perspective of the joint between two ring sectors 6a and 6b. This joint is made in the middle of a opening 21 partly machined in the core 20 of the sector ring 6a and partly in the core 20 of the sector ring 6b.
  • downstream wing 8 of the ring sector 6b has an extension tab 22b machined in said downstream wing 8; the downstream wing 8 of the ring sector 6a has a symmetrical extension tab 22a with tab 22b; legs 22a and 22b being complementary so as to fit together one inside the other.
  • Such a joining of sectors ring ensures, by the covering made on the downstream wings, sealing of the ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Domaine techniqueTechnical area

La présente invention a pour objet une turbomachine comportant des moyens de pilotage des jeux entre stator et rotor et, plus précisément, entre le stator et le sommet des aubes mobiles du rotor.The subject of the present invention is a turbomachine comprising games control means between stator and rotor and, more precisely, between the stator and the top of the rotor moving blades.

Elle trouve de nombreuses applications dans le domaine de l'aéronautique.It finds many applications in the field of aeronautics.

Etat de la techniqueState of the art

Les grands échauffements auxquels une turbomachine de moteur d'avion est soumise provoquent généralement des dilatations thermiques qu'il est du plus haut intérêt de pouvoir contrôler pour éviter, en particulier, les fuites de gaz entre le rotor et la structure du stator qui l'entoure ainsi que les pertes de rendement, consécutives à ces fuites de gaz.The major warm-ups to which a aircraft engine turbomachine is subject cause generally thermal expansions that it is higher interest to be able to control to avoid, in in particular, gas leaks between the rotor and the structure of the stator which surrounds it as well as the losses of efficiency, following these gas leaks.

Les moteurs d'avion (notamment ceux utilisés pour la propulsion des avions à réaction) doivent pouvoir fonctionner dans des conditions qui peuvent varier rapidement. Ces variations des conditions de fonctionnement peuvent être un emballement du rotor froid, un coup de manette des gaz, un emballement du rotor chaud, ou toutes autres conditions de fonctionnement bien connues de l'homme du métier.Aircraft engines (especially those used for propulsion of jet airplanes) must be able to operate under conditions which can vary quickly. These variations of operating conditions can be a runaway of the cold rotor, a stroke of the throttle, runaway hot rotor, or any other operating conditions well known to man of the job.

Aussi, il est nécessaire d'obtenir un jeu constant entre la virole du stator et le rotor pendant des fonctionnements variables tels que ceux nommés ci-dessus. Il est en particulier capital que les jeux radiaux entre les extrémités externes des aubes mobiles du rotor et la virole interne du stator, qui porte les aubes fixes de redressement de l'écoulement de l'air entre les aubes mobiles, soient les plus constants possibles.Also, it is necessary to get a set constant between the stator shell and the rotor during variable operations such as those named above. It is particularly important that games radial between the outer ends of the vanes of the rotor and the internal shroud of the stator, which carries the fixed air flow straightening vanes between the moving blades, be the most constant possible.

Or, l'obtention de tels jeux constants est relativement difficile du fait, d'une part, de la dilatation et de la construction mécanique variable du rotor sous l'effet de variations de vitesse et, d'autre part, de la croissance thermique relative entre le stator et le rotor due à une différence des inerties thermiques importante, mais nécessaire.However, obtaining such constant games is relatively difficult due, on the one hand, to the expansion and variable mechanical construction of the rotor under the effect of speed variations and, on the other share of the relative thermal growth between the stator and rotor due to a difference in inertias important thermal, but necessary.

Différents moyens sont connus pour limiter les conséquences d'une usure de la virole du stator due à une dilatation des aubes mobiles supérieure à la dilatation lors d'un fonctionnement dit "normal". Un premier moyen consiste à construire les viroles avec un revêtement en matériau tendre à l'endroit devant lequel les aubes mobiles passent ; ainsi le frottement éventuel de l'extrémité des aubes mobiles qui pourrait se produire lors d'une dilatation plus forte de ces dernières provoquerait une usure du revêtement et une remise en forme du stator à cet emplacement.Various means are known to limit the consequences of wear on the stator shell due at a dilation of the movable blades greater than the expansion during so-called "normal" operation. A first way is to build the ferrules with a soft material covering where the movable blades pass; so friction possible from the end of the moving blades which could occur during stronger expansion of these the latter would cause wear on the coating and restoration of the stator at this location.

Un autre moyen permettant d'obtenir un résultat satisfaisant consiste à construire le stator de telle façon qu'il soit possible d'y faire circuler du gaz, prélevé par exemple à un autre endroit de la machine, à une température et à un débit qui produisent à volonté un échauffement ou un refroidissement apte à régler les dilatations de la virole et donc son jeu avec les aubes mobiles.Another way to get a satisfactory result is to build the stator in such a way that it is possible to circulate there gas, taken for example from another location in the machine, at a temperature and flow that produce at will a heating or cooling capable of adjust the expansion of the ferrule and therefore its play with the moving blades.

Un tel envoi d'air à température variable sur la structure du support de redresseur permet, par une variation de la vitesse de dilatation et de contraction de la structure, d'accomoder différentes conditions de fonctionnement du moteur.Such a variable temperature air shipment on the structure of the rectifier support allows, by a variation in the speed of expansion and contraction of the structure, to accommodate different engine operating conditions.

Pour assurer la dilatation et la contraction de la structure sur toute la circonférence du carter, celui-ci est généralement réalisé d'une seule pièce ; il s'agit donc d'un carter de 360° de circonférence.To ensure expansion and contraction of the structure around the entire circumference of the casing, this is generally made of a single piece; it is therefore a 360 ° housing of circumference.

Les documents FR-2 683 851, FR-2 516 980 et FR-2 482 661 décrivent des turbomachines dont les stators comportent des carters à double peau s'étendant autour des rotors sur une circonférence complète, l'air de chauffage ou de refroidissement circulant entre les deux peaux du carter. Selon de telles turbomachines, les éléments de virole (ou secteurs de virole) sont liés directement au carter. Aussi, lors de dilatations ou de contractions du carter, les éléments de virole peuvent subir des déplacements qui nuisent à la circularité de la structure.Documents FR-2 683 851, FR-2 516 980 and FR-2 482 661 describe turbomachinery whose stators have double skin housings extending around the rotors on a full circumference, the air heating or cooling between the two crankcase skins. According to such turbomachines, shell elements (or shell sectors) are linked directly to the housing. Also, during dilations or crankcase contractions, the shell elements may undergo displacements which harm the circularity of the structure.

Afin de conserver une circularité parfaite des éléments de virole et d'assurer une réaction immédiate de la structure à la dilatation et à la contraction, des moyens d'adaptation des éléments de virole au carter sont connus de l'homme de l'art. Le document GB-2 115 487 décrit des anneaux statoriques emboítés par queue d'aronde dans des supports. Le document FR-2 482 662 décrit un anneau de stator segmenté et percé d'orifices.In order to maintain perfect circularity shell elements and ensure a reaction structure immediately upon expansion and contraction, means of adaptation of the elements of shell to the casing are known to those skilled in the art. The document GB-2 115 487 describes stator rings fitted by dovetail in supports. The document FR-2 482 662 describes a stator ring segmented and pierced with orifices.

Aucun de ces moyens d'adaptation n'assure une liaison souple des éléments de virole par rapport au carter.None of these means of adaptation ensures a flexible connection of the shell elements with respect to to the housing.

Exposé de l'inventionStatement of the invention

La présente invention a justement pour but de remédier à ces inconvénients. A cette fin, elle propose une turbomachine comportant un stator dont le carter de 360° de circonférence et les éléments de virole sont liés par l'intermédiaire d'un point fixe et d'appuis glissants assurant à la virole une souplesse circonférentielle.The object of the present invention is precisely to remedy these drawbacks. To this end, she proposes a turbomachine comprising a stator whose 360 ° circumference housing and components ferrule are linked via a fixed point and sliding supports ensuring flexibility of the shell circumferential.

De façon plus précise, l'invention concerne une turbomachine comportant :

  • une virole constituée d'une pluralité d'éléments de virole en forme de secteurs circulaires portant, chacun sur une face intérieure, des aubes fixes ; et
  • un carter circulaire entourant la virole.
More specifically, the invention relates to a turbomachine comprising:
  • a ferrule made up of a plurality of ferrule elements in the form of circular sectors, each carrying an inner face, fixed vanes; and
  • a circular casing surrounding the ferrule.

Cette turbomachine se caractérise par le fait qu'elle comporte un anneau de support logé entre le carter et la virole, solidaire de ladite virole et comprenant une pluralité de secteurs d'anneau circulaires fixés chacun sur le carter par un moyen de point fixe (10) et au moins deux moyens d'appuis glissants (11) situés de part et d'autre du moyen de point fixe pour assurer à la virole une souplesse circonférentielle par rapport au carter.This turbomachine is characterized by the fact that it has a support ring housed between the casing and the ferrule, integral with said ferrule and comprising a plurality of circular ring sectors each attached to the casing by a fixed point means (10) and at least two sliding support means (11) located on either side else of the fixed point means to ensure the ferrule circumferential flexibility relative to the casing.

Selon un mode de réalisation de l'invention, la turbomachine comporte un anneau de support logé entre le carter et la virole et comprenant une pluralité de secteurs d'anneau circulaires fixés chacun sur le carter par un moyen de point fixe et des moyens d'appuis glissants et ayant une section en forme d'un U dont l'ouverture est dirigée vers la virole, chaque élément de virole comportant des moyens d'accrochage aptes à être introduits dans l'ouverture d'au moins un secteur d'anneau pour solidariser ledit secteur d'anneau et l'élément de virole.According to an embodiment of the invention, the turbomachine comprises a ring of support housed between the casing and the ferrule and comprising a plurality of fixed circular ring sectors each on the housing by means of a fixed point and sliding supports having a shaped section of a U whose opening is directed towards the shell, each shell element comprising means hooking able to be introduced into the opening at least one ring sector for securing said ring area and ferrule element.

Selon ce mode de réalisation, chaque secteur d'anneau comporte une aile amont et une aile aval, chacune desdites ailes amont et aval comprenant des premiers évidements ouverts radialement vers la virole pour assurer une souplesse circonférentielle audit secteur d'anneau. L'aile amont comporte, en outre, des seconds évidements.According to this embodiment, each ring sector has an upstream wing and a wing downstream, each of said upstream and downstream wings comprising first recesses open radially towards the ferrule to provide circumferential flexibility audit ring sector. The upstream wing has, in in addition, second recesses.

Pour ce mode de réalisation, la turbomachine comporte des moyens de serrage en appui de part et d'autre de chaque secteur d'anneau pour assurer une solidarisation dudit secteur d'anneau avec le moyen d'accrochage de l'élément de virole.For this embodiment, the turbomachine comprises clamping means in support of on either side of each ring sector to ensure securing said ring sector with the means of attachment of the ferrule element.

Ces moyens de serrage comportent une vis et un écrou conique introduit à l'intérieur du secteur d'anneau et apte à s'écarter lors de l'introduction de la vis, la base dudit écrou étant alors en appui sur les faces internes du secteur d'anneau.These clamping means comprise a screw and a conical nut inserted inside the sector ring and able to deviate during the introduction of the screw, the base of said nut then being supported on the internal faces of the ring sector.

Les moyens d'accrochage de chaque élément de virole constituent, avec les extrémités des ailes amont et aval du secteur d'anneau dans lequel il est introduit, un assemblage en queue d'aronde.The means of attachment of each element of ferrule constitute, with the ends of the wings upstream and downstream of the ring sector in which it is introduced, a dovetail assembly.

Selon ce mode de réalisation, chaque moyen de point fixe comporte un système de vis/écrou assurant une solidarisation sans jeu d'un secteur d'anneau avec le carter, l'écrou étant introduit à l'intérieur de l'anneau par le second évidement et disposé en appui sur une face interne de l'âme du secteur d'anneau.According to this embodiment, each means point system has a screw / nut system ensuring a seamless connection of a ring sector with the casing, the nut being introduced inside the ring by the second recess and arranged in support on an internal face of the core of the ring sector.

La vis peut être, par exemple, introduite dans le secteur d'anneau avec une inclinaison voisine de 45° par rapport à la direction radiale. Elle peut, selon un autre exemple, être introduite radialement dans le secteur d'anneau, l'écrou ayant alors une forme conique dont la base est dirigée vers la virole.The screw can be, for example, introduced in the ring sector with a neighboring inclination 45 ° to the radial direction. She can, according to another example, to be introduced radially in the ring sector, the nut then having a shape conical, the base of which is directed towards the shell.

Selon ce mode de réalisation, chaque moyen d'appui glissant comporte :

  • une vis introduite dans le secteur d'anneau par une ouverture réalisée dans l'âme dudit secteur d'anneau ;
  • une semelle surmontée d'une saillie qui est percée d'un trou comportant sur la paroi un pas de vis pour recevoir ladite vis et qui traverse l'ouverture de l'âme pour être en contact avec le carter ;
  • deux pièces d'appui disposées de part et d'autre du trou de la semelle et fixées sur le secteur d'anneau de façon à permettre un glissement de la semelle sur les pièces d'appui.
According to this embodiment, each sliding support means comprises:
  • a screw introduced into the ring sector through an opening made in the core of said ring sector;
  • a sole surmounted by a projection which is pierced with a hole comprising on the wall a thread for receiving said screw and which passes through the opening of the core to be in contact with the casing;
  • two support pieces arranged on either side of the hole in the sole and fixed to the ring sector so as to allow the sole to slide on the support pieces.

La vis est alors introduite dans le secteur d'anneau avec une inclinaison longitudinale d'angle a, et les pièces d'appui comportent une surface inclinée d'un angle a par rapport à la direction radiale.The screw is then introduced into the sector ring with a longitudinal inclination of angle a, and the supporting parts have an inclined surface at an angle a to the radial direction.

Avantageusement, les premiers évidements de l'aile aval sont fermés par des plaques d'étanchéité. Chaque secteur d'anneau comporte, autour des premiers évidements, des rainures dans lesquelles sont positionnées et emboítées les plaques d'étanchéité.Advantageously, the first recesses of the downstream wing are closed by sealing plates. Each ring sector comprises, around the first recesses, grooves in which are positioned and fitted the sealing plates.

Chaque aile aval d'un secteur d'anneau peut comporter, à une extrémité, une patte de prolongement et, à une autre extrémité, un usinage assurant un emboítement avec recouvrement dudit secteur d'anneau dans les secteurs d'anneau voisins. Each downstream wing of a ring sector can have an extension tab at one end and, at another end, machining ensuring a interlocking with covering of said ring sector in neighboring ring areas.

Brève description des dessinsBrief description of the drawings

  • la figure 1 représente un compresseur haute pression équipé des moyens de pilotage des jeux entre rotor et stator conformes au premier mode de réalisation de l'invention ;Figure 1 shows a compressor high pressure equipped with games control means between rotor and stator in accordance with the first mode of realization of the invention;
  • la figure 2 représente une coupe diamétrale de la turbomachine selon le premier mode de réalisation, montrant la répartition angulaire des éléments de virole et des secteurs d'anneau à l'intérieur du carter ;Figure 2 shows a section diameter of the turbomachine according to the first mode of realization, showing the angular distribution of ferrule elements and ring sectors to the inside of the housing;
  • la figure 3 représente une vue en perspective d'un secteur d'anneau de la figure 2 ;FIG. 3 represents a view in perspective of a ring sector of FIG. 2;
  • la figure 4 représente une vue partielle de l'aile aval et de l'aile amont d'un secteur d'anneau de la figure 2 ;Figure 4 shows a partial view of the downstream wing and the upstream wing of a ring sector of Figure 2;
  • la figure 5 représente, selon une coupe axiale, les moyens de serrage assurant la solidarisation des secteurs d'anneau et des éléments de virole conformément au premier mode de réalisation ;Figure 5 shows, in a section axial, the clamping means ensuring the joining of the ring sectors and elements of shell in accordance with the first embodiment;
  • la figure 6 représente, selon une coupe axiale, un point fixe conforme au premier mode de réalisation ;Figure 6 shows, in a section axial, a fixed point in accordance with the first mode of production ;
  • la figure 7 représente, en coupe axiale, une variante des moyens de serrage et des moyens d'étanchéité du premier mode de réalisation ; FIG. 7 represents, in axial section, a variant of the clamping means and the means sealing of the first embodiment;
  • la figure 8 représente, en coupe axiale, un appui glissant liant le secteur d'anneau et le carter conformément au premier mode de réalisation ;FIG. 8 represents, in axial section, a sliding support linking the ring sector and the casing according to the first embodiment;
  • la figure 9 représente, selon une vue en perspective, les pièces d'appui et la semelle formant l'appui glissant de la figure 8 ;FIG. 9 represents, in a view in perspective, the supporting parts and the sole forming the sliding support of FIG. 8;
  • la figure 10 représente une vue en perspective de la jointure entre deux secteurs d'anneau de la figure 2.FIG. 10 represents a view in perspective of the joint between two ring sectors in Figure 2.
Exposé détaillé de modes de réalisationDetailed description of embodiments

Sur la figure 1, on a représenté, en coupe axiale, un compresseur haute pression ayant un carter extérieur 1 de 360° de circonférence et des moyens de pilotage des jeux conformes au premier mode de réalisation de l'invention. Ce carter 1 comporte deux enveloppes (ou deux peaux) concentriques, légèrement coniques, séparées par un volume (représenté hâchuré sur la figure 1) dans lequel circule l'air de chauffage ou de refroidissement. Ce carter à deux peaux est du type de celui décrit dans le document FR-2 683 851 cité précédemment ; il ne sera donc pas décrit plus en détail. In Figure 1, there is shown in section axial, a high pressure compressor having a housing exterior 1 of 360 ° circumference and means of piloting of games conforming to the first mode of realization of the invention. This housing 1 has two envelopes (or two skins) concentric, slightly conical, separated by a volume (shown hatched in Figure 1) in which the heating air circulates or cooling. This two-skin housing is type of that described in the document FR-2 683 851 cited previously; it will therefore not be described further in detail.

Ce carter 1 entoure une pluralité d'éléments de virole 2 qui sont sensiblement coniques. Ces éléments de virole 2 sont disposés bout à bout et assemblés par des joints à emboítement 3 pour former une seule virole continue et sensiblement parallèle au carter 1.This casing 1 surrounds a plurality ferrule elements 2 which are substantially conical. These shell elements 2 are arranged end to end and assembled by interlocking joints 3 to form a single continuous ferrule and substantially parallel to the housing 1.

Chaque élément de virole 2 porte un étage d'aubes fixes 4 de stator, nommé aussi étage redresseur. Un étage d'aubes mobiles 5 de rotor s'étend entre chaque paire d'étages d'aubes fixes 4.Each ferrule element 2 carries a stage stationary stator vanes 4, also called stage rectifier. A stage of movable rotor blades 5 extends between each pair of stages of fixed blades 4.

Sur la figure 1, on a représenté de plus les anneaux 6 selon le premier mode de réalisation de l'invention, ces anneaux permettant des déplacements sensibles des éléments de virole 2 en fonction des dilatations et contractions du carter 1. Ces anneaux 6 comportent chacun une pluralité de secteurs d'anneaux disposés bout à bout et emboítés les uns dans les autres pour réaliser des anneaux continus.In Figure 1, there is also shown the rings 6 according to the first embodiment of the invention, these rings allowing displacements sensitive of the shell elements 2 according to the casing dilations and contractions 1. These rings 6 each have a plurality of ring sectors arranged end to end and fitted into each other others to make continuous rings.

Cette figure 1 montre la section d'un anneau 6. Comme on le voit sur la figure, chaque anneau 6 a une section en forme de U, le côté ouvert du U étant dirigé vers la virole 2.This figure 1 shows the section of a ring 6. As seen in the figure, each ring 6 has a U-shaped section, the open side of the U being directed towards the shell 2.

Chaque élément de virole 2 comporte sur sa face externe, c'est-à-dire sur la face ne portant pas les aubes fixes 4, des moyens d'accrochage 9 de l'anneau 6. Selon un mode de réalisation préféré de l'invention, ces moyens d'accrochage 9 consistent en un tenon 9a en queue d'aronde apte à être introduit dans l'ouverture de l'anneau 6. Les extrémités des ailes amont 7 et aval 8 de l'anneau 6 forment une mortaise 9b apte à recevoir le tenon 9a. La mortaise 9b et le tenon 9a forment ainsi un assemblage en queue d'aronde. Des moyens de serrage, non représentés sur cette figure 1, assurent un pincement de part et d'autre des ailes amont 7 et aval 8 de l'anneau 6 pour assurer une solidarisation dudit anneau 6 avec la virole 2.Each ferrule element 2 has on its external face, i.e. on the face not bearing fixed vanes 4, attachment means 9 of the ring 6. According to a preferred embodiment of the invention, these attachment means 9 consist of a tenon 9a in dovetail adapted to be inserted into the opening of the ring 6. The ends of the wings upstream 7 and downstream 8 of the ring 6 form a mortise 9b suitable for receiving the post 9a. Mortise 9b and tenon 9a thus form a dovetail assembly. Of clamping means, not shown in this FIG. 1, pinch on both sides of the wings upstream 7 and downstream 8 of the ring 6 to ensure a securing of said ring 6 with the ferrule 2.

Chaque secteur d'anneau 6 est fixé sur le carter au moyen d'un point fixe 10 qui sera décrit plus en détail au travers des figures suivantes. Chaque secteur d'anneau est en outre fixé sur le carter au moyen d'appuis glissants non représentés sur cette figure 1 mais décrits plus en détails dans la suite de la description.Each ring sector 6 is fixed to the casing by means of a fixed point 10 which will be described more in detail through the following figures. Each ring sector is also fixed on the casing at means of sliding supports not shown on this Figure 1 but described in more detail below the description.

La figure 2, ainsi que les figures suivantes 3 à 10 représentent en détails des éléments constituant le premier mode de réalisation des moyens de pilotage montrés en figure 1.Figure 2, as well as the figures following 3 to 10 represent in detail elements constituting the first embodiment of the means shown in Figure 1.

La figure 2 montre la répartition angulaire des éléments de virole 2 et des secteurs d'anneau 6 à l'intérieur du carter 1. La virole 2 comporte donc une pluralité d'éléments de virole dont trois sont représentés sur la figure 2 et référencés 2a, 2b et 2c. De même, l'anneau 6 comporte une pluralité de secteurs d'anneau dont quatre sont représentés sur cette figure 2 et référencés 6a, 6b, 6c et 6d. Selon le mode de réalisation représenté sur cette figure 2, chaque secteur d'anneau a une taille équivalente à environ deux éléments de virole.Figure 2 shows the angular distribution ferrule elements 2 and ring sectors 6 to inside the casing 1. The ferrule 2 therefore comprises a plurality of shell elements, three of which are shown in Figure 2 and referenced 2a, 2b and 2c. Similarly, the ring 6 has a plurality of sectors of which four are shown in this figure 2 and referenced 6a, 6b, 6c and 6d. Depending on the mode of realization represented in this figure 2, each ring sector has a size equivalent to approximately two shell elements.

Cependant, on tient à préciser que la taille d'un élément de virole et la taille d'un secteur d'anneau sont tout à fait indépendante l'une de l'autre.However, it should be noted that the size of a ferrule element and the size of a sector ring are completely independent one of the other.

Chaque secteur d'anneau 6a, 6b, 6c et 6d est lié au carter 1 par un point fixe référencé, respectivement, 10a, 10b, 10c et 10d. Chaque secteur d'anneau 6a, 6b, 6c et 6d est, en outre, lié au carter par des appuis glissants. Ces appuis glissants sont au nombre de quatre par secteurs d'anneau répartis de la façon suivante :

  • deux appuis glissants répartis de part et d'autre du point fixe ; et
  • deux appuis glissants situés chacun à une extrémité d'un secteur d'anneau.
Each ring sector 6a, 6b, 6c and 6d is linked to the casing 1 by a fixed point referenced, respectively, 10a, 10b, 10c and 10d. Each ring sector 6a, 6b, 6c and 6d is, moreover, linked to the casing by sliding supports. There are four sliding supports per ring sector distributed as follows:
  • two sliding supports distributed on either side of the fixed point; and
  • two sliding supports each located at one end of a ring sector.

Selon le mode de réalisation représenté sur la figure 2, le secteur d'anneau 6a comporte deux appuis glissants 11a et 11b de part et d'autre du point fixe 10a et deux appuis glissants 11c et 11d à chacune de ses extrémités.According to the embodiment shown on Figure 2, the ring sector 6a has two sliding supports 11a and 11b on either side of the point fixed 10a and two sliding supports 11c and 11d each of its ends.

L'ensemble de ces appuis glissants assure, pour chaque secteur d'anneau, un déplacement circonférentiel immédiat (représenté par les flèches sur la figure 2) du secteur d'anneau, et donc des éléments de virole reliés à ce secteur d'anneau, par rapport au déplacement du carter.All of these sliding supports ensure, for each ring sector, one displacement immediate circumferential (represented by arrows in FIG. 2) of the ring sector, and therefore of ferrule elements connected to this ring sector, by relative to the displacement of the housing.

De plus, on a représenté schématiquement sur cette figure 2, les évidements de l'aile amont du secteur d'anneau 6a. Chaque secteur d'anneau comporte, en effet, une pluralité d'évidements, à savoir les évidements 12 uniquement sur l'aile amont et les évidements 13 sur l'aile amont et sur l'aile aval, ces évidements assurant une souplesse circonférentielle au secteur d'anneau. Les secteurs d'anneau 6a, 6b,... sont assemblés avec les secteurs d'anneau voisins au niveau du centre d'un évidement 12.In addition, there is shown schematically in this figure 2, the recesses of the upstream wing of the ring sector 6a. Each ring sector includes, indeed, a plurality of recesses, namely the recesses 12 only on the upstream wing and the recesses 13 on the upstream wing and on the downstream wing, these recesses providing circumferential flexibility at the ring area. The ring sectors 6a, 6b, ... are assembled with neighboring ring sectors at level from the center of a recess 12.

La figure 3 représente une vue en perspective du secteur d'anneau 6a de la figure 2. Cette figure montre donc le secteur d'anneau 6a coupé au niveau d'un évidement 13, le carter 1 sur lequel est fixé le secteur d'anneau 6a, ainsi que la virole 2 avec son tenon 9a en queue d'aronde autour duquel s'emboíte les extrémités en queue d'aronde 9b des ailes amont 7 et aval 8. De façon plus précise, le secteur d'anneau 6a est relié au carter 1 par l'intermédiaire du point fixe 10a et de plusieurs appuis glissants dont trois sont représentés sur cette figure et référencés 11a, 11b et 11c.Figure 3 shows a view in perspective of the ring sector 6a of FIG. 2. This figure therefore shows the ring sector 6a cut at a recess 13, the casing 1 on which is fixed the ring sector 6a, as well as the ferrule 2 with its tenon 9a in dovetail around which fits the dovetail ends 9b of the upstream wings 7 and downstream 8. More specifically, the ring sector 6a is connected to the casing 1 via the point fixed 10a and several sliding supports including three are represented in this figure and referenced 11a, 11b and 11c.

On a représenté sur cette figure, les évidements 12 de l'aile amont ainsi que les évidements 13 avec leur fente radiale, ces évidements 13 étant aussi présents sur l'aile aval 8, mais non visibles sur cette vue en perspective du secteur d'anneau 6a.This figure shows the recesses 12 of the upstream wing as well as the recesses 13 with their radial slot, these recesses 13 being also present on the downstream wing 8, but not visible on this perspective view of the ring sector 6a.

Aussi, on a représenté sur la figure 4, en partie A, une portion de l'aile amont 7 du secteur d'anneau 6a et, en partie B, une portion de l'aile aval 8 de ce même secteur d'anneau 6a.Also, there is shown in Figure 4, in part A, a portion of the upstream wing 7 of the sector ring 6a and, in part B, a portion of the downstream wing 8 of this same ring sector 6a.

De façon plus précise, la partie A de la figure 4 montre la face externe de l'aile amont 7 du secteur d'anneau 6a. Cette partie A montre donc les évidements 12 de l'aile amont 7 ainsi que les évidements 13 de cette même aile amont 7. Comme expliqué précédemment, ces évidements 13 comporte une ouverture radiale 13a, ou fente radiale, partant de la partie interne du secteur d'anneau (c'est-à-dire la partie de plus petit diamètre) et se terminant dans l'évidement 13. Ces fentes radiales confèrent à l'anneau 6 une souplesse circonférentielle.More specifically, part A of the Figure 4 shows the outer face of the upstream wing 7 of the ring sector 6a. This part A therefore shows the recesses 12 of the upstream wing 7 as well as the recesses 13 of this same upstream wing 7. As explained above, these recesses 13 include a radial opening 13a, or radial slot, starting from the internal part of the ring sector (i.e. the part of smaller diameter) and ending in the recess 13. These radial slots give the ring 6 a circumferential flexibility.

Les évidements 12, réalisés dans l'aile amont 7, permettent de diminuer la quantité de matière nécessaire à la réalisation de cet anneau ; il en résulte donc un allègement de l'anneau. En outre, ces évidements 12 assurent une réduction des échanges thermiques entre le milieu ambiant et l'anneau 6.The recesses 12, made in the wing upstream 7, reduce the amount of material necessary for the realization of this ring; it therefore results in a reduction in the ring. In addition, these recesses 12 ensure a reduction in exchanges between the environment and the ring 6.

Sur cette partie A de la figure 4, on a représenté également les écrous 14 des moyens de serrage. On this part A of figure 4, we have also shown the nuts 14 of the means of Tightening.

La partie B de la figure 4 montre la face interne de l'aile aval 8 du secteur d'anneau 6a. Cette aile aval 8 comporte les évidements 13 avec leurs fentes radiales 13a ainsi que des vis 15 qui traversent le secteur d'anneau de part en part et sont fixées dans les écrous 14 de l'aile amont 7. Chaque vis 15 associée à un écrou 14 constitue les moyens de serrage qui assurent le pincement du secteur d'anneau autour du tenon en queue d'aronde de la virole.Part B of Figure 4 shows the face internal of the downstream wing 8 of the ring sector 6a. This downstream wing 8 has the recesses 13 with their radial slots 13a as well as screws 15 which pass through the ring sector right through and are fixed in the nuts 14 of the upstream wing 7. Each associated screw 15 to a nut 14 constitutes the clamping means which pinch the ring sector around the dovetail tenon of the ferrule.

Sur cette partie B, sont aussi représentées les vis du point fixe 10a et de l'appui glissant 11a. Ces vis sont représentées en pointillés car elles ne sont pas visibles sur la face interne de l'aile aval 8. La vis 16a du point fixe 10a est insérée dans le carter 1 et l'aile aval 8 est fixée dans l'écrou 16b qui est en contact avec la face interne de l'aile aval 8. Cet écrou 16b est fixé sur l'aile aval 8 au moyen de deux rivets 17a et 17b.On this part B, are also represented the screws of the fixed point 10a and of the sliding support 11a. These screws are shown in dotted lines because they do not are not visible on the inner face of the downstream wing 8. The screw 16a of the fixed point 10a is inserted in the housing 1 and the downstream wing 8 is fixed in the nut 16b which is in contact with the inner face of the downstream wing 8. This nut 16b is fixed to the downstream wing 8 by means of two rivets 17a and 17b.

Ce point fixe sera décrit de façon plus détaillée dans la suite de la description.This fixed point will be described in more detail detailed in the following description.

L'appui glissant lla est également représenté sur cette partie B de la figure 4. La vis 18a de l'appui glissant est insérée dans une semelle 18b surmontée d'une saillie percée d'un trou sur la paroi duquel un pas de vis a été réalisé. Cette semelle 18b est en appui sur des pièces d'appui 19a et 19b disposées de part et d'autre dudit trou de la semelle 18b. Ces pièces d'appui 19a et 19b sont traversées par les vis 15, ce qui solidarise lesdites pièces d'appui sur l'aile aval 8. Une ouverture 21 est, en outre, réalisée dans l'âme 20 du secteur d'anneau ; la semelle 18b a, avec la saillie qui la surmonte, une forme de "pioche" apte à passer en partie dans l'ouverture 21 de l'âme 20 du secteur d'anneau 6a pour être en contact direct avec la paroi interne du carter 1. Les parties latérales de la semelle 18b peuvent donc glisser sur ces pièces d'appui 19a et 19b créant ainsi un jeu circonférentiel du segment d'anneau 6a par rapport au carter 1.The sliding support is also represented on this part B of figure 4. The screw 18a of the sliding support is inserted into a sole 18b surmounted by a projection pierced with a hole on the wall of which a thread has been made. This sole 18b is supported on support pieces 19a and 19b arranged on either side of said hole in the sole 18b. These support pieces 19a and 19b are crossed by the screws 15, which secures said support pieces on the downstream wing 8. An opening 21 is, in addition, produced in the core 20 of the ring sector; the sole 18b has, with the projection which surmounts it, a form of "pickaxe" able to pass partly into the opening 21 of the core 20 of the ring sector 6a to be in contact direct with the internal wall of the casing 1. The parts sides of the sole 18b can therefore slide on these support pieces 19a and 19b thus creating a clearance circumference of the ring segment 6a with respect to the housing 1.

Selon un mode de réalisation, cette semelle 18b est un écrou à double portée.According to one embodiment, this sole 18b is a double span nut.

Selon un mode de réalisation préféré de l'invention, les pièces d'appui 19a et 19b forment un angle d'environ 45° par rapport à l'aile aval 8 de façon à assurer un meilleur glissement de la semelle 18b.According to a preferred embodiment of the invention, the supporting parts 19a and 19b form a angle of about 45 ° to the downstream wing 8 of so as to ensure a better sliding of the sole 18b.

Cet appui glissant sera décrit de façon plus détaillée en référence aux figures 8 et 9 de la description.This sliding support will be described in a way more detailed with reference to Figures 8 and 9 of the description.

Cette partie B de la figure 4 montre, en outre, une plaque d'étanchéité 25 pouvant être introduite dans des rainures (ou fentes) usinées autour des évidements 13 de l'aile aval 8. Ces rainures, référencées 26, sont représentées en pointillés sur la figure car elles sont réalisées sur la face externe de l'aile aval 8. La plaque d'étanchéité 25 comporte des retours (en pointillés) aptes à s'introduire dans les rainures 26 pour assurer le positionnement et l'emboítement desdites plaques d'étanchéité 25 dans l'aile aval 8. Le positionnement de telles plaques d'étanchéité devant les évidements 13 de l'aile aval 8 du secteur d'anneau 6a a pour but d'empêcher les éventuelles réintroductions des gaz de l'aval vers l'amont de l'anneau.This part B of FIG. 4 shows, in in addition, a sealing plate 25 which can be introduced into grooves (or slots) machined around recesses 13 in the downstream wing 8. These grooves, referenced 26, are shown in dotted lines on the figure because they are made on the external face of the downstream wing 8. The sealing plate 25 includes returns (dotted) suitable for entering the grooves 26 for positioning and the fitting of said sealing plates 25 in the downstream wing 8. The positioning of such plates sealing in front of the recesses 13 of the downstream wing 8 of ring sector 6a is intended to prevent possible reintroductions of gases from downstream to upstream of the ring.

Selon un autre mode de réalisation de l'invention, représenté sur la figure 7, l'étanchéité de l'aile aval de chaque secteur d'anneau est réalisée au moyen d'un joint annulaire 38 en appui sur la partie aval de l'assemblage en queue d'aronde. According to another embodiment of the invention, shown in Figure 7, the seal of the downstream wing of each ring sector is carried out by means of an annular seal 38 bearing on the part downstream of the dovetail assembly.

Sur la figure 5, on a représenté les moyens de serrage en coupe axiale. Comme décrit succinctement précédemment, ces moyens de serrage comportent une vis 15 introduite dans l'aile aval 8 de l'anneau 6 et traversant ledit anneau de part en part. Cette vis 15 est fixée dans un écrou 14 en appui sur la face externe de l'aile amont 7. Ces moyens de serrage permettent ainsi de comprimer la mortaise 9b réalisée par les ailes 7 et 8 de l'anneau 6 contre le tenon 9a en queue d'aronde de la virole 2.In Figure 5, there is shown the means clamping in axial section. As briefly described previously, these clamping means comprise a screw 15 introduced into the downstream wing 8 of the ring 6 and crossing said ring right through. This screw 15 is fixed in a nut 14 bearing on the external face upstream wing 7. These clamping means allow thus compressing the mortise 9b produced by the wings 7 and 8 of the ring 6 against the tail 9a at the tail dovetail of the ferrule 2.

Sur la figure 6, on a représenté un point fixe en coupe axiale. Ce point fixe 10 consiste en un système de vis/écrou introduit dans le carter 1 et dans l'anneau 6 pour les solidariser. De façon plus précise, ce système de vis/écrou comporte une vis 16a introduite dans le carter 1 et dans l'âme 20 de l'anneau 6 par une percée. Un écrou 16b introduit dans l'anneau 6 par l'un des évidements 12 de l'aile amont 7 assure la fixation de la vis 16a. La vis 16a ainsi fixée dans l'écrou 16b assure la solidarisation de l'anneau 6 par son âme 20 contre la paroi interne du carter 1.In Figure 6, a point is shown fixed in axial section. This fixed point 10 consists of a screw / nut system introduced into housing 1 and into ring 6 to secure them. More specifically, this screw / nut system includes a screw 16a introduced in the casing 1 and in the core 20 of the ring 6 by a breakthrough. A nut 16b introduced into the ring 6 by one recesses 12 of the upstream wing 7 ensures the fixing of the screw 16a. The screw 16a thus fixed in the nut 16b secures the ring 6 by its core 20 against the inner wall of the housing 1.

Selon un mode de réalisation de l'invention, l'écrou 16b est du type écrou à pattes dont les pattes sont fixées à l'anneau 6 par les rivets référencés 17a et 17b sur la figure 4.According to an embodiment of the invention, the nut 16b is of the lug nut type whose legs are fixed to the ring 6 by the rivets referenced 17a and 17b in Figure 4.

Selon le mode de réalisation préféré de l'invention, c'est-à-dire le mode de réalisation représenté sur la figure 6, la vis 16a est introduite dans le carter 1 et l'anneau 6 avec une inclinaison longitudinale, l'écrou 16b ayant une forme adaptée pour recevoir la vis 16a ainsi inclinée tout en ayant un appui solide contre la face interne de l'âme 20 de l'anneau 6. According to the preferred embodiment of the invention, i.e. the embodiment shown in Figure 6, the screw 16a is introduced in housing 1 and ring 6 with an inclination longitudinal, the nut 16b having a shape suitable for receive the screw 16a thus inclined while having a solid support against the internal face of the core 20 of the ring 6.

Selon un autre mode de réalisation de l'invention, représenté sur la figure 7, les moyens d'accrochage de la virole 2 avec l'anneau 6 consistent en une mortaise 30b réalisée dans chaque élément de virole 2 et un tenon 30a réalisé par les extrémités internes des ailes aval 8 et amont 7 des secteurs d'anneau. Aussi, la solidarisation sans jeu de chaque secteur d'anneau avec le carter 1 est réalisée au moyen d'une vis bombée 32 introduite radialement dans le carter 1 et dans l'anneau. Cette vis est introduite dans un écrou 34 de forme conique dont la base, dirigée vers la virole, est en contact avec les faces internes des ailes amont et aval. Une lunule 36 est usinée sur la face externe de chaque élément de virole. Aussi, lorsque la vis 32 est serrée, son extrémité bombée prend appui dans la lunule 36, l'écrou 34 monte et, par sa conicité, écarte le secteur d'anneau réalisant ainsi la solidarisation sans jeu entre l'élément de virole 2 et le secteur d'anneau 6.According to another embodiment of the invention, represented in FIG. 7, the means for hooking the ferrule 2 with the ring 6 consist in a mortise 30b made in each element of ferrule 2 and a lug 30a produced by the ends internal of downstream 8 and upstream wings 7 of sectors ring. Also, the joining without play of each ring sector with the casing 1 is achieved by means a domed screw 32 introduced radially into the housing 1 and in the ring. This screw is introduced in a nut 34 of conical shape whose base, directed towards the shell, is in contact with the internal faces upstream and downstream wings. A lunule 36 is machined on the external face of each ferrule element. Also, when screw 32 is tight, its curved end is supported in the lunula 36, the nut 34 rises and, by its taper, spreads the ring area thus realizing the connection without play between the shell element 2 and the ring sector 6.

Egalement à chaque extrémité de secteur, un écrou conique 34 est positionné à cheval sur deux secteurs permettant ainsi aux secteurs de glisser par rapport aux anneaux en fonction des variations thermiques.Also at each end of the sector, a conical nut 34 is positioned astride two sectors allowing sectors to slide by compared to rings according to variations thermal.

Sur la figure 8, on a représenté un appui glissant en coupe axiale. Cet appui glissant 11 consiste en un système de vis/écrou dans lequel l'écrou peut se déplacer sur des pièces d'appui. De façon plus précise, ce système de vis/écrou comporte une vis 18a introduite dans le carter 1 et dans la saillie de la semelle 18b. Cette semelle est constituée d'un socle et de la saillie située au milieu du socle. Une ouverture 21 est réalisée dans l'âme 20 de l'anneau 6, suffisamment importante pour permettre le passage de la saillie de la semelle 18b qui peut ainsi être en contact avec la paroi interne du carter 1.In Figure 8, there is shown a support sliding in axial section. This sliding support 11 consists of a screw / nut system in which the nut can move on supporting parts. More precise, this screw / nut system includes an 18a screw inserted in the casing 1 and in the projection of the sole 18b. This sole consists of a base and of the projection located in the middle of the base. An opening 21 is produced in the core 20 of the ring 6, large enough to allow passage of the protrusion of the sole 18b which can thus be in contact with the internal wall of the casing 1.

Un écrou 18c assure la fixation de la vis 18a dans la semelle 18b. Le socle de la semelle 18b est en appui sur deux pièces d'appui, dont seule la pièce d'appui 19a est visible sur cette figure 8. La saillie de la semelle 18b traversant l'ouverture 21 de l'âme 20 et le socle de ladite semelle 18b étant apte à glisser sur les pièces d'appui, un jeu circonférentiel de l'anneau 6 par rapport au carter 1 est alors possible. De tels appuis glissants 11 permettent ainsi le déplacement de l'anneau 6 et donc de la virole 2 en fonction des variations thermiques.An 18c nut secures the screw 18a in the sole 18b. The base of the sole 18b is resting on two support pieces, of which only the piece support 19a is visible in this figure 8. The projection of the sole 18b passing through the opening 21 of the core 20 and the base of said sole 18b being able to slide on the supporting parts, a circumferential clearance of the ring 6 relative to the casing 1 is then possible. Such sliding supports 11 thus allow the displacement of the ring 6 and therefore of the shell 2 in function of thermal variations.

Selon le mode de réalisation préféré de l'invention, la pièce d'appui 19a, ainsi que toutes les pièces d'appui dans l'anneau 6, sont maintenues solidaires de l'anneau par les moyens de serrage 14, 15 qui traversent lesdites pièces d'appui en leurs extrémités externes.According to the preferred embodiment of the invention, the support piece 19a, as well as all the supporting parts in the ring 6, are maintained integral with the ring by the clamping means 14, 15 which pass through said support pieces in their outer ends.

La figure 9 représente une vue en perspective des pièces d'appui et de la semelle d'un appui glissant. On voit donc, sur cette figure 9, les pièces d'appui 19a et 19b ayant une paroi, inclinée à 45° par rapport à la direction radiale, sur laquelle glisse le socle 18b' de la semelle 18b.FIG. 9 represents a view in perspective of the support pieces and the sole of a sliding support. We therefore see, in this figure 9, the supporting parts 19a and 19b having a wall, inclined at 45 ° with respect to the radial direction, on which slides the base 18b 'of the sole 18b.

Sur cette figure 9, on voit bien la saillie 18b" de la semelle 18b introduite dans l'ouverture 21. Une flèche montre le jeu entre la saillie 18b" et l'âme 20 de l'anneau 6. On a représenté, en outre, de façon schématique, la vis 18a insérée dans la saillie 18b" et fixée par l'écrou 18c.In this figure 9, we can clearly see the projection 18b "of the sole 18b introduced into the opening 21. An arrow shows the clearance between the projection 18b "and the core 20 of ring 6. In addition, there is shown schematic, the screw 18a inserted in the projection 18b "and fixed by nut 18c.

La figure 10 représente une vue en perspective de la jointure entre deux secteurs d'anneau 6a et 6b. Cette jointure est réalisée au milieu d'une ouverture 21 usinée en partie dans l'âme 20 du secteur d'anneau 6a et en partie dans l'âme 20 du secteur d'anneau 6b.Figure 10 shows a view in perspective of the joint between two ring sectors 6a and 6b. This joint is made in the middle of a opening 21 partly machined in the core 20 of the sector ring 6a and partly in the core 20 of the sector ring 6b.

En outre, l'aile aval 8 du secteur d'anneau 6b comporte une patte de prolongement 22b usinée dans ladite aile aval 8 ; l'aile aval 8 du secteur d'anneau 6a comporte une patte de prolongement 22a symétrique à la patte 22b ; les pattes 22a et 22b étant complémentaires de façon à s'emboíter mutuellement l'une dans l'autre. Une telle jointure des secteurs d'anneau assure, par le recouvrement réalisé sur les ailes aval, une étanchéité de l'anneau.In addition, the downstream wing 8 of the ring sector 6b has an extension tab 22b machined in said downstream wing 8; the downstream wing 8 of the ring sector 6a has a symmetrical extension tab 22a with tab 22b; legs 22a and 22b being complementary so as to fit together one inside the other. Such a joining of sectors ring ensures, by the covering made on the downstream wings, sealing of the ring.

Claims (15)

  1. Turbomachine comprising:
    a shroud (2) made up of a number of shroud elements (2a, 2b, ...) in the form of circular sectors each carrying stationary vanes (4) on an interior face; and
    a circular casing (1) surrounding the shroud,
    characterized in that it comprises a support ring (6) housed between the casing and the shroud, secured to the said shroud and comprising a number of circular ring sectors (6a, 6b,...) each fixed to the casing by a fixed-point means (10) and at least two sliding-support means (11) situated one on each side of the fixed-point means so as to give the shroud circumferential flexibility with respect to the casing.
  2. Turbomachine according to Claim 1, characterized in that the ring sectors each have a U-shaped section, the opening of which U faces towards the shroud, and in that each shroud element comprises attachment means (9a) capable of nesting into at least one ring sector in order to secure the said ring sector and the shroud element together.
  3. Turbomachine according to Claim 2, characterized in that, with each ring sector comprising an upstream leg (8) and a downstream leg (7), each of the said upstream and downstream legs comprises first recesses (13) which are open radially towards the shroud in order to give the said ring sector circumferential flexibility.
  4. Turbomachine according to either one of Claims 2 and 3, characterized in that, with each ring sector comprising an upstream leg (8) and a downstream leg (7) the said upstream leg comprises second recesses (12).
  5. Turbomachine according to any one of Claims 2 to 4, characterized in that it comprises clamping means (14, 15) resting on each side of each ring sector in order to secure the said ring sector to the attachment means of the shroud element.
  6. Turbomachine according to Claim 5, characterized in that the clamping means comprise a screw (32) and a conical nut (34) introduced into the ring sector and capable of moving away as the screw is inserted, the base of the said nut then resting on the internal faces of the ring sector.
  7. Turbomachine according to any one of Claims 3 to 6, characterized in that the attachment means of each shroud element constitute, together with the ends of the upstream and downstream legs of the ring sector into which it is introduced, a dovetail-like assembly.
  8. Turbomachine according to Claim 4, characterized in that each fixed-point means comprises a screw/nut system (16a, 16b) which secures a ring sector to the casing without play, the nut being introduced inside the ring through the second recess and placed resting on an internal face of the web (20) of the ring sector.
  9. Turbomachine according to Claim 8, characterized in that the screw is introduced into the ring sector at an inclination of close to 45° with respect to the radial direction.
  10. Turbomachine according to Claim 8, characterized in that the screw is introduced radially into the ring sector and the nut has a conical shape, the base of which faces towards the shroud.
  11. Turbomachine according to any one of Claims 2 to 10, characterized in that each sliding-support means comprises:
    a screw (18a) surmounted by a projection (18b") which is introduced into the ring sector through an opening (21) made in the web of the said ring sector;
    a soleplate (18b) surmounted by a projection (18b") which is pierced with a hole which, on its wall, has a screw thread for receiving the said screw and which passes at least partially through the opening in the web so as to be in contact with the casing;
    two support pieces (19a, 19b) arranged one on each side of the hole in the soleplate and fixed to the ring sector in such a way as to allow the soleplate to slide along the support pieces.
  12. Turbomachine according to Claim 11, characterized in that as the screw is introduced into the ring sector with a longitudinal inclination of angle α, the support pieces comprise a surface inclined by an angle α with respect to the radial direction.
  13. Turbomachine according to any one of Claims 3 to 12, characterized in that the first recesses in the downstream leg are closed by sealing plates (25).
  14. Turbomachine according to Claim 13, characterized in that the downstream leg of each ring sector comprises, around the first recesses, slots (26) in which the sealing plates are positioned and nested.
  15. Turbomachine according to any one of Claims 3 to 14, characterized in that each downstream leg of a ring sector comprises, at one end, an extension tab (22a) and, at another end, a complementary extension tab (22b) allowing the said ring sector to nest into the adjacent ring sectors with overlap.
EP94402400A 1993-10-27 1994-10-26 Turbomachine with means to control the tip clearance between rotor and stator Expired - Lifetime EP0651139B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9312798A FR2711730B1 (en) 1993-10-27 1993-10-27 Turbomachine equipped with means for controlling the clearances between rotor and stator.
FR9312798 1993-10-27

Publications (2)

Publication Number Publication Date
EP0651139A1 EP0651139A1 (en) 1995-05-03
EP0651139B1 true EP0651139B1 (en) 1999-01-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP94402400A Expired - Lifetime EP0651139B1 (en) 1993-10-27 1994-10-26 Turbomachine with means to control the tip clearance between rotor and stator

Country Status (4)

Country Link
US (1) US5616003A (en)
EP (1) EP0651139B1 (en)
DE (1) DE69415765T2 (en)
FR (1) FR2711730B1 (en)

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DE19938274A1 (en) * 1999-08-12 2001-02-15 Asea Brown Boveri Device and method for drawing the gap between the stator and rotor arrangement of a turbomachine
FR2817285B1 (en) 2000-11-30 2003-06-13 Snecma Moteurs STATOR INTERNAL OIL
FR2829176B1 (en) * 2001-08-30 2005-06-24 Snecma Moteurs STATOR CASING OF TURBOMACHINE
FR2875534B1 (en) 2004-09-21 2006-12-22 Snecma Moteurs Sa TURBINE MODULE FOR A GAS TURBINE ENGINE WITH ROTOR COMPRISING A MONOBLOC BODY
FR2875535B1 (en) * 2004-09-21 2009-10-30 Snecma Moteurs Sa TURBINE MODULE FOR GAS TURBINE ENGINE
US9039358B2 (en) 2007-01-03 2015-05-26 United Technologies Corporation Replaceable blade outer air seal design
EP2728124B1 (en) * 2012-10-30 2018-12-12 MTU Aero Engines AG Turbine ring and turbomachine
EP2789804A1 (en) * 2013-04-11 2014-10-15 Alstom Technology Ltd Gas turbine thermal shroud with improved durability
US20180149030A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine shroud with hanger attachment

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Also Published As

Publication number Publication date
US5616003A (en) 1997-04-01
EP0651139A1 (en) 1995-05-03
FR2711730A1 (en) 1995-05-05
FR2711730B1 (en) 1995-12-01
DE69415765T2 (en) 1999-07-29
DE69415765D1 (en) 1999-02-18

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