EP0146449B1 - Arrangement for centering an inner stator shroud supported by changeable blades - Google Patents
Arrangement for centering an inner stator shroud supported by changeable blades Download PDFInfo
- Publication number
- EP0146449B1 EP0146449B1 EP84402381A EP84402381A EP0146449B1 EP 0146449 B1 EP0146449 B1 EP 0146449B1 EP 84402381 A EP84402381 A EP 84402381A EP 84402381 A EP84402381 A EP 84402381A EP 0146449 B1 EP0146449 B1 EP 0146449B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bushes
- arrangement
- ring
- pivots
- sectors
- 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.)
- Expired
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 230000000295 complement effect Effects 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims description 2
- 239000003831 antifriction material Substances 0.000 claims 1
- 230000000903 blocking effect Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 description 4
- 210000003462 vein Anatomy 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000010079 rubber tapping Methods 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 208000037516 chromosome inversion disease Diseases 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
Definitions
- the invention relates. to stators with fins with variable setting of compressors.
- the stators of this type consist of fins mounted with possibilities of rotation about their longitudinal axis in the compressor casing, their pitch angle relative to the axis of the motor being controlled by a mechanism external to the casing constituted for example by 'a synchronism ring whose movement is transmitted to the head pivots of the fins by means of rods.
- these fins are generally connected together by an inner ring divided into a plurality of sectors, the upper face of which defines the internal wall of the vein and which support sealing means such as that a seal cooperating with the wipers of a labyrinth seal integral with the rotor in order to limit the internal leakage rates between the downstream and the upstream of the stator stage.
- the invention relates in particular to the foot connection point of the internal fin-ring.
- This connection is made by means of a pivot of feet movable in a bearing bush housed in a radial bore of the ring; in order to preserve the free expansion of the ring in operation, it has a certain freedom of sliding along the pivots of the fin feet.
- the quality of the games between wipers and abradable is determining for the output and the performance of the machine.
- the radial positioning and the rigidity of the ring are ensured by the radiating arrangement of the fins.
- the clearances are thus determined with precision.
- the fins can show, during assembly, a slope in a plane transverse to the axis of the engine, more or less marked; moreover, the play between pivot and bushing is not zero; this leads to a certain dispersion of the radial position of each sector which is not compensated for when these sectors are joined by the seal-wear and wear carrier rails since the rigidity of the assembly is insufficient.
- the ring may have circularity and centering defects with respect to the rotor.
- the extreme positions of the ring sectors are difficult to estimate; in the absence of a stop, in particular between the platform of the fins and the ring sectors, the lower corners of the fins can come into contact with the wall of the ring with the consequence of possible deterioration of the fins when they are controlled for travel around of their axis by the control system.
- a first improvement consisted in reducing the number of sectors constituting the ring and the rail in order to limit the effects thereof due to the splitting and in introducing at the head of each fin under the control lever a shim limiting the radial position of the fin, the thickness of this shim being determined as a function of the residual clearance of the attachment point.
- GB-A-749577 describes an assembly of an inner ring of the stator with the possibility of adjustment; the fins are fixed to the ring by means of a bolt mounted eccentrically in an axial bore of the feet of the fin via a sleeve with eccentric internal and external axes. It is therefore possible, by this means, to adjust the position of the ring relative to the fins and to the rotor; unfortunately, such a system cannot be applied to a stator whose fins are of variable setting.
- adjustment means are distributed over each ring sector making it possible to position them radially.
- These means are constituted by pivot bushings provided with an external thread cooperating with a complementary tapping of their housing in the ring sector, so that the bushings being in abutment against the lower edge of the platform of the fins, a displacement radial sector is obtained by rotation of the sockets in their housing.
- a locking means is provided to prevent any untimely rotation once the adjustment has been made.
- this locking means is constituted by a radial and circumferential flange secured to the outer face of the seal and wear seal carrier rail, abutting against one of the faces of the prismatic base from the socket.
- FIG. 1 there is shown in axial section a compressor part of a gas turbine engine.
- a stator stage separates two stages of movable vanes 3 mounted on a drum-shaped rotor.
- the stator is formed of a ring of fins 2 extending radially from the casing 1 on which they are mounted to rotate about their longitudinal axis by means of a head pivot 4 journalled in a bearing of the casing 1, with the interposition of a socket 22.
- This pivot 4 is connected to a timing control mechanism, not shown.
- the fins are provided with a pivot of feet 5 movable in a socket 6 fixed in a radial bore of the ring sector 7.
- the edges of the rail 8 are curved in the form of hooks and engage with two lateral flanges of the ring.
- This rail 8 serves as a support for a material forming a seal and wear seal 9 which cooperates in known manner, with the wipers 10 of the labyrinth seal integral with the rotor, to limit leaks due to the difference in pressures prevailing on the part and on the other side of the stator stage.
- the radial position of the sectored ring 7 cannot be determined with precision because of the manufacturing and mounting tolerances; in operation, the ring sectors can slide along the pivots modifying the clearance between seal and wear seal and labyrinth seal on the one hand, the clearance between the inner edges of the fins and the wall of the vein d on the other hand: when the latter clearance becomes zero, the operation of the fin timing control is thwarted, causing the latter to deteriorate.
- the pivot 5 of the fin 2 pivots in a bush 12 made of a self-lubricating material such as graphite; this socket is itself supported by a second socket 14 provided with an external thread cooperating with a complementary tapping of its. housing in the ring sector 7.
- Panes 15 are cut at the enlarged base of the sleeve 14 which has in this way a cross section of polygonal shape, for example hexagonal (FIG. 4) and which opens into a peripheral groove 16, of the inner face of the ring (7).
- This groove provides around the base of the sleeve a space allowing on the one hand, the use of a tool on the other hand, sufficient relative displacement of the sleeve in the sector; in particular the socket must be able to come to bear against the internal shoulder of the platform 21.
- This platform is engaged in a recess extending the tapped part of the housing of the socket 14.
- the rail 8 has a radial flange 81, peripheral, on its upper face which is received in the groove 16 of the ring and against which one of the sections of the base of the socket abuts.
- the ring is thus reconstituted step by step and the sectors joined to each other by fitting segments of the seal and wear-bearing rail 8.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
L'invention se rapporte. aux stators à ailettes à calage variable de compresseurs.The invention relates. to stators with fins with variable setting of compressors.
Les stators de ce type sont constitués d'ailettes montées avec possibilités de rotation autour de leur axe longitudinal dans le carter du compresseur, leur angle de calage par rapport à l'axe du moteur étant commandé par un mécanisme extérieur au carter constitué par exemple d'un anneau de synchronisme dont le mouvement est transmis aux pivots de tête des ailettes par l'intermédiaire de biellettes.The stators of this type consist of fins mounted with possibilities of rotation about their longitudinal axis in the compressor casing, their pitch angle relative to the axis of the motor being controlled by a mechanism external to the casing constituted for example by 'a synchronism ring whose movement is transmitted to the head pivots of the fins by means of rods.
A leur extrémité inférieure, près de l'axe du moteur, ces ailettes sont généralement reliées entre elles par un anneau intérieur divisé en une pluralité de secteurs dont la face supérieure définit la paroi interne de la veine et qui supportent des moyens d'étanchéité tel qu'une garniture d'étanchéité coopérant avec les léchettes d'un joint labyrinthe solidaire du rotor afin de limiter les débits de fuite interne entre l'aval et l'amont de l'étage statorique.At their lower end, near the axis of the engine, these fins are generally connected together by an inner ring divided into a plurality of sectors, the upper face of which defines the internal wall of the vein and which support sealing means such as that a seal cooperating with the wipers of a labyrinth seal integral with the rotor in order to limit the internal leakage rates between the downstream and the upstream of the stator stage.
L'invention concerne en particulier le point de liaison pieds de l'ailette-anneau interne. Cette liaison est réalisée au moyen d'un pivot de pieds mobile dans une douille de palier logée dans un alésage radial de l'anneau ; afin de conserver la libre dilatation de l'anneau en fonctionnement, celui-ci possède une certaine liberté de coulissement le long des pivots de pieds d'ailette.The invention relates in particular to the foot connection point of the internal fin-ring. This connection is made by means of a pivot of feet movable in a bearing bush housed in a radial bore of the ring; in order to preserve the free expansion of the ring in operation, it has a certain freedom of sliding along the pivots of the fin feet.
La qualité des jeux entre léchettes et abradable est déterminante pour le rendement et la performance de la machine. Dans l'hypothèse de tolérances de réalisation à 100 %, le positionnement radial et la rigidité de l'anneau sont assurés par la disposition rayonnante des ailettes. Les jeux sont ainsi déterminés avec précision. En réalité, les ailettes peuvent accuser, au montage, un devers dans un plan transversal à l'axe du moteur, plus ou moins marqué ; de plus, le jeu entre pivot et douille n'est pas nul ; ceci conduit à une certaine dispersion de la position radiale de chaque secteur qui n'est pas compensée lorsque ces secteurs sont réunis par les rails porte-garniture d'étanchéité et d'usure car la rigidité de l'ensemble est insuffisante. Ainsi, l'anneau peut présenter des défauts de circularité et, de centrage par rapport au rotor. En outre, en fonctionnement les positions extrêmes des secteurs d'anneaux sont difficiles à estimer ; en l'absence de butée notamment entre la plateforme des ailettes et les secteurs d'anneau, les coins inférieurs des ailettes peuvent venir en contact avec la paroi de l'anneau avec comme conséquence une détérioration possible des ailettes lors de leur commande de débattement autour de leur axe par le système de commande.The quality of the games between wipers and abradable is determining for the output and the performance of the machine. In the hypothesis of 100% production tolerances, the radial positioning and the rigidity of the ring are ensured by the radiating arrangement of the fins. The clearances are thus determined with precision. In reality, the fins can show, during assembly, a slope in a plane transverse to the axis of the engine, more or less marked; moreover, the play between pivot and bushing is not zero; this leads to a certain dispersion of the radial position of each sector which is not compensated for when these sectors are joined by the seal-wear and wear carrier rails since the rigidity of the assembly is insufficient. Thus, the ring may have circularity and centering defects with respect to the rotor. In addition, in operation the extreme positions of the ring sectors are difficult to estimate; in the absence of a stop, in particular between the platform of the fins and the ring sectors, the lower corners of the fins can come into contact with the wall of the ring with the consequence of possible deterioration of the fins when they are controlled for travel around of their axis by the control system.
Une première amélioration a consisté à réduire le nombre des secteurs constituant l'anneau et le rail afin d'en limiter les effets dus au fractionnement et à introduire en tête de chaque ailette sous le levier de commande une cale limitant la position radiale de l'ailette, l'épaisseur de cette cale étant déterminée en fonction du jeu résiduel du point d'attache. Enfin, en disposant une entretoise faisant office de butée entre le pivot de pied et le rail, on peut limiter les variations de position radiale des secteurs.A first improvement consisted in reducing the number of sectors constituting the ring and the rail in order to limit the effects thereof due to the splitting and in introducing at the head of each fin under the control lever a shim limiting the radial position of the fin, the thickness of this shim being determined as a function of the residual clearance of the attachment point. Finally, by having a spacer acting as a stop between the foot pivot and the rail, it is possible to limit the variations in the radial position of the sectors.
Cependant, outre les difficultés à réaliser par cette méthode un centrage satisfaisant de l'anneau par rapport au rotor sa mise en oeuvre complique les opérations de maintenance en raison du risque d'inversion des cales ou des entretoises au cours d'un remontage.However, in addition to the difficulties in achieving by this method a satisfactory centering of the ring relative to the rotor, its implementation complicates the maintenance operations due to the risk of inversion of the wedges or spacers during reassembly.
On connaît par ailleurs le brevet US-A-3 079 128 où le pivot de pieds se termine par un filetage, de façon à bloquer radialement le secteur d'anneau entre un écrou serré sur le pivot et la plateforme de l'ailette. Une telle réalisation présente l'inconvénient de ne pas se prêter à un réglage en position du secteur d'anneau nécessitant la reprise en place, par usinage, de la garniture d'étanchéité et d'usure ; de plus, l'anneau ne possède aucune liberté de glissement permettant d'absorber les dilatations différentielles en fonctionnement.We also know the patent US-A-3,079,128 where the pivot of the legs ends in a thread, so as to radially block the ring sector between a nut tightened on the pivot and the platform of the fin. Such an embodiment has the drawback of not lending itself to an adjustment in position of the ring sector requiring the resumption in place, by machining, of the seal and wear; moreover, the ring does not have any freedom of sliding making it possible to absorb the differential expansions in operation.
Le brevet GB-A-749577 décrit un montage d'anneau intérieur du stator avec possibilité de réglage ; les ailettes sont fixées à l'anneau au moyen d'un boulon monté excentré dans un alésage axial des pieds de l'ailette par l'intermédiaire d'un manchon à axes interne et externe excentrés. On peut donc, par ce moyen, effectuer un réglage de la position de l'anneau par rapport aux ailettes et au rotor ; malheureusement, un tel système ne peut s'appliquer à un stator dont les ailettes sont à calage variable.GB-A-749577 describes an assembly of an inner ring of the stator with the possibility of adjustment; the fins are fixed to the ring by means of a bolt mounted eccentrically in an axial bore of the feet of the fin via a sleeve with eccentric internal and external axes. It is therefore possible, by this means, to adjust the position of the ring relative to the fins and to the rotor; unfortunately, such a system cannot be applied to a stator whose fins are of variable setting.
L'invention se propose donc de réaliser les objectifs recherchés, c'est-à-dire :
- - limiter les variations de position radiale de l'anneau,
- - éliminer les risques de contact entre coins inférieurs des ailettes et anneau interne,
- - faciliter le réglage en position de l'anneau.
- - limit variations in the radial position of the ring,
- - eliminate the risk of contact between the lower corners of the fins and the inner ring,
- - facilitate the adjustment in position of the ring.
Conformément à l'invention, des moyens de réglage sont répartis sur chaque secteur d'anneau permettant de les positionner radialement. Ces moyens sont constitués par des douilles de pivot pourvues d'un filetage extérieur coopérant avec un taraudage complémentaire de leur logement dans le secteur d'anneau, de sorte que les douilles étant en appui contre le bord inférieur de la plateforme des ailettes, un déplacement radial du secteur est obtenu par rotation des douilles dans leur logement. Un moyen de verrouillage est prévu pour éviter toute rotation inopportune une fois le réglage effectué.According to the invention, adjustment means are distributed over each ring sector making it possible to position them radially. These means are constituted by pivot bushings provided with an external thread cooperating with a complementary tapping of their housing in the ring sector, so that the bushings being in abutment against the lower edge of the platform of the fins, a displacement radial sector is obtained by rotation of the sockets in their housing. A locking means is provided to prevent any untimely rotation once the adjustment has been made.
Selon une caractéristique supplémentaire de l'invention, ce moyen de verrouillage est constitué par une bride radiale et circonférentielle solidaire de la face extérieure du rail porte-garniture d'étanchéité et d'usure, venant en butée contre une des faces de la base prismatique de la douille.According to an additional characteristic of the invention, this locking means is constituted by a radial and circumferential flange secured to the outer face of the seal and wear seal carrier rail, abutting against one of the faces of the prismatic base from the socket.
L'invention ressortira mieux de la description qui va suivre donnant un exemple non limitatif de réalisation en relation avec les dessins annexés sur lesquels :
- la figure 1 est une coupe axiale d'une partie de compresseur montrant une liaison pivot de pieds-anneau sans moyen de réglage,
- la figure 2 est une vue agrandie de la liaison pivot de pieds-anneau présentant un moyen de réglage caractéristique de l'invention,
- la figure 3 est une vue semblable présentant un mode de réalisation légèrement différent,
- la figure 4 est une vue en coupe partielle selon la ligne III de la figure 3.
- FIG. 1 is an axial section of a compressor part showing a pivot connection of feet-ring without means of adjustment,
- FIG. 2 is an enlarged view of the pivot link of the feet-ring having an adjustment means characteristic of the invention,
- FIG. 3 is a similar view showing a slightly different embodiment,
- FIG. 4 is a partial sectional view along line III of FIG. 3.
En se reportant à la figure 1, on voit représentée en coupe axiale une partie de compresseur d'un moteur à turbine à gaz. A l'intérieur du carter 1, un étage de stator sépare deux étages d'aubes mobiles 3 montées sur un rotor en forme de tambour. Le stator est formé d'une couronne d'ailettes 2 s'étendant radialement à partir du carter 1 sur lequel elles sont montées à rotation autour de leur axe longitudinal par l'intermédiaire d'un pivot de tête 4 tourillonnant dans un palier du carter 1, avec interposition d'une douille 22. Ce pivot 4 est relié à un mécanisme de commande de calage, non représenté. A leur autre extrémité, en se dirigeant vers l'axe du moteur, les ailettes sont pourvues d'un pivot de pieds 5 mobile dans une douille 6 fixée dans un alésage radial du secteur d'anneau 7. L'anneau définit par sa face extérieure la paroi interne de la veine du compresseur, les secteurs le constituant sont réunis par un rail 8 divisé également en segments dont le nombre est inférieur à celui des secteurs. Les bords du rail 8 sont recourbés en forme de crochets et viennent en prise avec deux brides latérales de l'anneau.Referring to Figure 1, there is shown in axial section a compressor part of a gas turbine engine. Inside the
Ce rail 8 sert de support à un matériau formant garniture d'étanchéité et d'usure 9 qui coopère de façon connue, avec les léchettes 10 du joint labyrinthe solidaire du rotor, pour limiter les fuites dues à la différence des pressions régnant de part et d'autre de l'étage statorique.This
Comme évoquée précédemment, la position radiale de l'anneau sectorisé 7 ne peut être déterminée avec précision à cause des tolérances de fabrication et de montage ; en fonctionnement, les secteurs d'anneau peuvent coulisser le long des pivots modifiant le jeu entre garniture d'étan- chéïté et d'usure et joint labyrinthe d'une part, le jeu entre bords intérieurs des ailettes et la paroi de la veine d'autre part : lorsque ce dernier jeu devient nul, le fonctionnement de la commande du calage des ailettes est contrarié entraînant la détérioration de ces dernières.As mentioned above, the radial position of the sectored
Enfin le mauvais positionnement de l'anneau, déterminant pour la veine, est cause de perturbation du fonctionnement aérodynamique du compresseur.Finally the bad positioning of the ring, determining for the vein, is cause of disturbance of the aerodynamic functioning of the compressor.
Conformément à l'invention, on remédie à ces défauts en ménageant un point de réglage à chaque extrémité des secteurs.According to the invention, these defects are remedied by providing an adjustment point at each end of the sectors.
En se reportant à la figure 2, on voit représentée une forme de réalisation de l'invention, les éléments restant inchangés par rapport à la figure 1 portant la même référence.Referring to Figure 2, there is shown an embodiment of the invention, the elements remaining unchanged from Figure 1 having the same reference.
Le pivot 5 de l'ailette 2 tourillonne dans une douille 12 constituée d'un matériau autolubrifiant tel que le graphite ; cette douille est elle-même supportée par une deuxième douille 14 pourvue d'un filetage extérieur coopérant avec un taraudage complémentaire de son. logement dans le secteur d'anneau 7. Des pans 15 sont taillés à la base élargie de la douille 14 qui présente de cette façon une section transversale de forme polygonale par exemple hexagonale (figure 4) et qui débouche dans une rainure 16, périphérique, de la face intérieure de l'anneau (7). Cette rainure ménage autour de la base de la douille un espace permettant d'une part, l'utilisation d'un outil d'autre part, un déplacement relatif suffisant de la douille dans le secteur ; notamment la douille doit pouvoir venir s'appuyer contre l'épaulement intérieur de la plateforme 21. Cette plateforme est engagée dans un évidement prolongeant la partie taraudée du logement de la douille 14.The
Afin d'éviter en fonctionnement toute rotation inopportune de la douille 14 une patte-frein rapportée sur l'anneau intérieur en assure le verrouillage ; à cet effet, le rail 8 comporte une bride 81 radiale, périphérique, sur sa face supérieure qui vient se loger dans la rainure 16 de l'anneau et contre laquelle un des pans de la base de la douille vient en butée.In order to avoid inopportune rotation of the
Dans la figure 3, au lieu d'utiliser une douille de carbone 12 entre le pivot 5 et la douille 14, on a recouvert le pivot 5 d'un revêtement antifriction 17 tel que le Téflon par exemple.In FIG. 3, instead of using a
Le montage et le réglage en position de l'anneau intérieur sont réalisés de la façon suivante :
- Après avoir disposé les ailettes dans le carter,
douilles 22 démontées, les secteurs aux extrémités de chacun desquels on a prévu un point de réglage sont mis en place par introduction despivots 5 dans leur palier ; lesdouilles 22 sont ensuite remontées sur les pivots de tête 4. Pour faciliter le montage, on donne auxdouilles 14 une position initiale dévissée de sorte que l'on obtient une position quelconque de l'anneau. Le calage point par point est obtenu par vissage/dévissage desdouilles 14, celles-ci étant en contact avec laplateforme 21 correspondante. Cette opération s'effectue en corrélation avec un contrôle de la côte au positionnement désiré. On prend soin de terminer la rotation desdouilles 14 sur un pan parallèle au bord de larainure 16 en prévision du montage de labride 81.
- After having disposed the fins in the casing, disassembled
sockets 22, the sectors at the ends of each of which an adjustment point has been provided are put in place by introduction of thepivots 5 in their bearing; thesockets 22 are then reassembled on the head pivots 4. To facilitate assembly, thesockets 14 are given an initial unscrewed position so that any position of the ring is obtained. The point by point setting is obtained by screwing / unscrewing thesockets 14, the latter being in contact with the correspondingplatform 21. This operation is carried out in correlation with a coast control at the desired positioning. Care is taken to complete the rotation of thesockets 14 on a panel parallel to the edge of thegroove 16 in anticipation of the mounting of theflange 81.
On notera que si la base de la douille 14 est taillée en 6 pans et que le pas de filetage est de 0,5 mm, la précision de réglage par chaque sixième de tour de la douille est de 0,08 mm.It will be noted that if the base of the
L'anneau est ainsi reconstitué de proche en proche et les secteurs solidarisés entre eux par mise en place des segments de rail porte-garniture d'étanchéité et d'usure 8.The ring is thus reconstituted step by step and the sectors joined to each other by fitting segments of the seal and wear-
En résumé, grâce à cette solution :
- - on parvient à maîtriser la géométrie de l'anneau et à assurer la continuité de la paroi interne de la veine en éliminant les ressauts circonférentiels entre secteurs,
- - il est permis d'employer des tolérances de fabrication qui normalement seraient incompatibles avec les jeux demandés,
- - enfin, on garantit les jeux entre rotors et stators dans des écarts réduits.
- - we manage to control the geometry of the ring and ensure the continuity of the internal wall of the vein by eliminating the projections circumferential between sectors,
- - it is allowed to use manufacturing tolerances which would normally be incompatible with the required clearances,
- - Finally, the clearance between rotors and stators is guaranteed in reduced distances.
Claims (7)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8319538A FR2556410B1 (en) | 1983-12-07 | 1983-12-07 | DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR |
FR8319538 | 1983-12-07 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0146449A1 EP0146449A1 (en) | 1985-06-26 |
EP0146449B1 true EP0146449B1 (en) | 1986-11-12 |
Family
ID=9294921
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP84402381A Expired EP0146449B1 (en) | 1983-12-07 | 1984-11-22 | Arrangement for centering an inner stator shroud supported by changeable blades |
Country Status (5)
Country | Link |
---|---|
US (1) | US4604030A (en) |
EP (1) | EP0146449B1 (en) |
JP (1) | JPS60145500A (en) |
DE (1) | DE3461318D1 (en) |
FR (1) | FR2556410B1 (en) |
Families Citing this family (55)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2582720B1 (en) * | 1985-05-29 | 1989-06-02 | Snecma | PROCESS FOR PRODUCING A TURBOMACHINE BLADE PIVOT AND A STATOR BLADE COMPRISING SAME |
FR2603340B1 (en) * | 1986-09-03 | 1988-11-04 | Snecma | TURBOMACHINE COMPRISING A DEVICE FOR ADJUSTING THE GAMES OF A LABYRINTH JOINT BETWEEN ROTOR AND STATOR AND OF THE GAS VEIN ALIGNMENT AND METHOD OF APPLICATION |
US4792277A (en) * | 1987-07-08 | 1988-12-20 | United Technologies Corporation | Split shroud compressor |
US4925364A (en) * | 1988-12-21 | 1990-05-15 | United Technologies Corporation | Adjustable spacer |
US4990056A (en) * | 1989-11-16 | 1991-02-05 | General Motors Corporation | Stator vane stage in axial flow compressor |
CA2082709A1 (en) * | 1991-12-02 | 1993-06-03 | Srinivasan Venkatasubbu | Variable stator vane assembly for an axial flow compressor of a gas turbine engine |
FR2685033B1 (en) * | 1991-12-11 | 1994-02-11 | Snecma | STATOR DIRECTING THE AIR INLET INSIDE A TURBOMACHINE AND METHOD FOR MOUNTING A VANE OF THIS STATOR. |
DE4217099C1 (en) * | 1992-05-22 | 1993-11-04 | Magnet Motor Gmbh | ELECTRIC ROTATIONAL MOTOR WITH RETARDER BRAKE |
US5421703A (en) * | 1994-05-25 | 1995-06-06 | General Electric Company | Positively retained vane bushing for an axial flow compressor |
FR2723614B1 (en) | 1994-08-10 | 1996-09-13 | Snecma | DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES. |
FR2742799B1 (en) * | 1995-12-20 | 1998-01-16 | Snecma | INTERNAL END END OF PIVOTING VANE |
FR2742800B1 (en) | 1995-12-20 | 1998-01-16 | Snecma | ARRANGEMENT OF INTERNAL ENDS OF A VARIABLE SETTING BLADE STAGE |
US5921749A (en) * | 1996-10-22 | 1999-07-13 | Siemens Westinghouse Power Corporation | Vane segment support and alignment device |
US6139261A (en) * | 1999-04-16 | 2000-10-31 | General Electric Company | Bushing assembly with removable wear sleeve |
US6682299B2 (en) * | 2001-11-15 | 2004-01-27 | General Electric Company | Variable stator vane support arrangement |
DE10225679A1 (en) * | 2002-06-10 | 2003-12-18 | Rolls Royce Deutschland | Bearing ring for mounting of blade roots of variable stator blades in HP compressor of gas turbine, is divided into individual segments with box section construction and with free ends bevelled in relation to circumferential direction |
US7220098B2 (en) * | 2003-05-27 | 2007-05-22 | General Electric Company | Wear resistant variable stator vane assemblies |
US20050084190A1 (en) * | 2003-10-15 | 2005-04-21 | Brooks Robert T. | Variable vane electro-graphitic bushing |
FR2875270B1 (en) * | 2004-09-10 | 2006-12-01 | Snecma Moteurs Sa | RETENTION OF CENTERING KEYS OF STATOR UNDER RINGS WITH VARIABLE SETTING OF A GAS TURBINE ENGINE |
GB0504588D0 (en) * | 2005-03-05 | 2005-04-13 | Rolls Royce Plc | Pivot ring |
EP1788199A3 (en) * | 2005-11-22 | 2011-02-23 | General Electric Company | Variable stator vane assembly with a wear resistant coating |
DE102006024085B4 (en) * | 2006-05-23 | 2020-04-16 | MTU Aero Engines AG | Turbo compressor in axial design |
FR2920469A1 (en) * | 2007-08-30 | 2009-03-06 | Snecma Sa | TURBOMACHINE VARIABLE CALIBRATION |
FR2928961B1 (en) | 2008-03-19 | 2015-11-13 | Snecma | SECTORIZED DISPENSER FOR A TURBOMACHINE. |
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US8480423B2 (en) * | 2011-08-16 | 2013-07-09 | Tyco Electronics Corporation | Contact region of an electrically conductive member |
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US9404376B2 (en) * | 2013-10-28 | 2016-08-02 | General Electric Company | Sealing component for reducing secondary airflow in a turbine system |
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EP3109520B1 (en) * | 2015-06-24 | 2020-05-06 | MTU Aero Engines GmbH | Seal carrier, guide blade assembly and fluid flow engine |
ITUB20155442A1 (en) * | 2015-11-11 | 2017-05-11 | Ge Avio Srl | STADIUM OF A GAS TURBINE ENGINE PROVIDED WITH A LABYRINTH ESTATE |
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US10502077B2 (en) * | 2016-03-17 | 2019-12-10 | United Technologies Corporation | Vane retainer |
DE102016215807A1 (en) * | 2016-08-23 | 2018-03-01 | MTU Aero Engines AG | Inner ring for a vane ring of a turbomachine |
DE112018001703T5 (en) | 2017-03-30 | 2019-12-24 | Mitsubishi Hitachi Power Systems, Ltd. | VARIABLE STATOR BLADE AND COMPRESSOR |
DE102017109952A1 (en) * | 2017-05-09 | 2018-11-15 | Rolls-Royce Deutschland Ltd & Co Kg | Rotor device of a turbomachine |
US10634000B2 (en) | 2017-06-23 | 2020-04-28 | Rolls-Royce North American Technologies Inc. | Method and configuration for improved variable vane positioning |
GB201715165D0 (en) * | 2017-09-20 | 2017-11-01 | Rolls Royce Plc | Bearing assembly |
DE102018210601A1 (en) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE |
FR3083564B1 (en) * | 2018-07-05 | 2021-07-09 | Safran Aircraft Engines | IMPELLER WITH AN ABRADABLE ELEMENT WITH ADJUSTABLE RADIAL POSITION |
FR3085060B1 (en) | 2018-08-17 | 2020-10-09 | Safran Aircraft Engines | VARIABLE TIMING BLADE GUIDE RING AND RING MOUNTING PROCEDURE |
DE102018213983A1 (en) * | 2018-08-20 | 2020-02-20 | MTU Aero Engines AG | Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine |
CN110656981B (en) * | 2019-10-09 | 2022-03-25 | 莱芜钢铁集团有限公司 | TRT stationary blade adjustable mechanism positioning method |
US11566535B2 (en) * | 2020-05-21 | 2023-01-31 | Raytheon Technologies Corporation | Low friction, wear resistant variable vane bushing |
CN114278435B (en) * | 2020-09-28 | 2023-05-16 | 中国航发商用航空发动机有限责任公司 | Compressor, gas turbine engine, adjustable vane assembly, and method of assembly |
FR3123885B1 (en) * | 2021-06-15 | 2023-06-16 | Safran Aircraft Engines | NON-FULL TURBOMACHINE RECTIFIER EQUIPPED WITH STATOR BLADES FIXED TO PIVOTS AND CORRESPONDING TURBOMACHINE |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB749577A (en) * | 1952-07-10 | 1956-05-30 | Havilland Engine Co Ltd | Improvements in or relating to blade ring assemblies for axial flow compressors or turbines |
GB736800A (en) * | 1952-07-10 | 1955-09-14 | Havilland Engine Co Ltd | Improvements in or relating to stationary blade rings of axial flow turbines or compressors |
GB757230A (en) * | 1953-12-01 | 1956-09-19 | Havilland Engine Co Ltd | Improvements in or relating to stator blade ring assemblies for axial flow compressors and the like |
FR1214261A (en) * | 1957-10-28 | 1960-04-07 | Canadian Patents Dev | Gas turbojet channel wall |
US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
US3325087A (en) * | 1965-04-28 | 1967-06-13 | David R Davis | Stator casing construction for gas turbine engines |
US3529904A (en) * | 1968-10-28 | 1970-09-22 | Westinghouse Electric Corp | Diaphragm seal structure |
DE2152365C3 (en) * | 1971-02-03 | 1973-12-06 | Carrier Corp., Syracuse, N.Y. (V.St.A.) | Device for supporting the inner ends of rotatably mounted guide vanes of an axial flow machine |
US3999883A (en) * | 1975-07-02 | 1976-12-28 | General Motors Corporation | Variable turbomachine stator |
US3990810A (en) * | 1975-12-23 | 1976-11-09 | Westinghouse Electric Corporation | Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine |
SE402622B (en) * | 1977-03-31 | 1978-07-10 | Svenska Flaektfabriken Ab | RIVER REGULATOR |
DE2810240C2 (en) * | 1978-03-09 | 1985-09-26 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Adjustable grille for turbines with axial flow, in particular high-pressure turbines for gas turbine engines |
US4214852A (en) * | 1978-04-20 | 1980-07-29 | General Electric Company | Variable turbine vane assembly |
US4286921A (en) * | 1979-12-13 | 1981-09-01 | Westinghouse Electric Corp. | Locking structure for an alignment bushing of a combustion turbine engine |
FR2524934B1 (en) * | 1982-04-08 | 1986-12-26 | Snecma | SAFETY STOP DEVICE FOR VARIABLE SETTING STATOR BLADE PIVOT |
-
1983
- 1983-12-07 FR FR8319538A patent/FR2556410B1/en not_active Expired
-
1984
- 1984-11-22 EP EP84402381A patent/EP0146449B1/en not_active Expired
- 1984-11-22 DE DE8484402381T patent/DE3461318D1/en not_active Expired
- 1984-11-27 US US06/675,214 patent/US4604030A/en not_active Expired - Lifetime
- 1984-12-05 JP JP59257265A patent/JPS60145500A/en not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
DE3461318D1 (en) | 1987-01-02 |
US4604030A (en) | 1986-08-05 |
JPS60145500A (en) | 1985-07-31 |
EP0146449A1 (en) | 1985-06-26 |
FR2556410B1 (en) | 1986-09-12 |
FR2556410A1 (en) | 1985-06-14 |
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