EP1777375A1 - Bearing device of a variable guide vane in an axial turbomachine - Google Patents

Bearing device of a variable guide vane in an axial turbomachine Download PDF

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Publication number
EP1777375A1
EP1777375A1 EP06076731A EP06076731A EP1777375A1 EP 1777375 A1 EP1777375 A1 EP 1777375A1 EP 06076731 A EP06076731 A EP 06076731A EP 06076731 A EP06076731 A EP 06076731A EP 1777375 A1 EP1777375 A1 EP 1777375A1
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EP
European Patent Office
Prior art keywords
housing
pivot
platform
blade
bearing
Prior art date
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Granted
Application number
EP06076731A
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German (de)
French (fr)
Other versions
EP1777375B1 (en
Inventor
Claude Robert Louis Lejars
Didier Raymond Charles Riby
Thierry Jean-Maurice Niclot
Richard Emile Staessen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1777375A1 publication Critical patent/EP1777375A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical

Abstract

The turbine stator guide for a blade (22) with a platform (23) and a pivot (24) located inside the turbine housing (3) includes a bearing (23b1, 26b1) that is integral with the platform. The bearing is in the form of an annular rib (26b1) that fits into a matching groove (23b1), the rib projecting from a flange (26b) adjoining the cylindrical portion (26a) of a bush located between the pivot and housing and adjacent to the end of the pivot sleeve (25). The position of the blade is controlled by a lever on the end of its pivot.

Description

La présente invention se rapporte au domaine des turbomachines telles qu'un compresseur axial d'un moteur à turbine à gaz, et vise en particulier les aubes de stator à calage variable.The present invention relates to the field of turbomachines such as an axial compressor of a gas turbine engine, and aims in particular the variable-pitch stator vanes.

Un système articulé, comme les aubes de redresseur à calage variable d'un compresseur de moteur à turbine à gaz, comprend des pièces en mouvement relatif les unes par rapport aux autres. Sur les figures 1 et 2, on a représenté de façon schématique, une aube 1 de redresseur à calage variable montée dans le carter 3 de la machine. L'aube comprend une pale 12, une platine ou plateforme 13 et une tige formant pivot 14. Le pivot 14 est logé dans un alésage ou orifice radial ménagé dans la paroi du carter 3 par l'intermédiaire de différents paliers. Un des paliers, le palier bas est constitué d'une douille 4 en contact glissant avec la partie basse de la tige formant pivot 14, directement ou par l'intermédiaire d'une frette 14'. La douille 4 est solidaire du carter et comprend une portion 4' logée dans le fond d'un lamage usiné dans la paroi de ce carter. Elle est en contact radialement avec la plateforme 13. La partie haute du pivot 14 est retenue dans un palier haut formé d'une douille 5. La face opposée de la plateforme 13 par rapport à la douille forme la base de la pale et est balayée par les gaz traversant la turbomachine. Un écrou 15 maintient l'aube dans son logement. Un levier 19, lui même actionné par des organes de commande, commande la rotation de l'aube autour de l'axe XX de la tige pour mettre celle-ci dans la position requise par rapport à la direction du flux gazeux. Les mouvements relatifs résultent du glissement des surfaces en contact entre elles.An articulated system, such as the variable pitch stator vanes of a gas turbine engine compressor, includes moving parts relative to one another. FIGS. 1 and 2 show diagrammatically a blade 1 of variable-pitch rectifier mounted in the casing 3 of the machine. The blade comprises a blade 12, a plate or platform 13 and a pivot rod 14. The pivot 14 is housed in a bore or radial orifice formed in the wall of the casing 3 via different bearings. One of the bearings, the low bearing is constituted by a sleeve 4 in sliding contact with the lower part of the pivot rod 14, directly or via a hoop 14 '. The bushing 4 is integral with the housing and comprises a portion 4 'housed in the bottom of a countersink machined in the wall of this housing. It is in radial contact with the platform 13. The upper part of the pivot 14 is retained in a high bearing formed of a bush 5. The opposite face of the platform 13 with respect to the bush forms the base of the blade and is swept by the gases passing through the turbomachine. A nut 15 keeps the blade in its housing. A lever 19, itself actuated by control members, controls the rotation of the blade around the axis XX of the rod to put it in the required position relative to the direction of the gas flow. The relative movements result from the sliding of the surfaces in contact with each other.

Un exemple de réalisation d'un tel système avec incorporation de douilles entre l'aube et le carter est décrit dans la demande de brevet EP 1 584 827 au nom de la demanderesse.An embodiment of such a system incorporating bushings between the blade and the housing is described in the patent application. EP 1 584 827 in the name of the plaintiff.

Dans le cas d'un compresseur de moteur à turbine à gaz, la pale 12 est soumise aux efforts aérodynamiques selon la flèche A. Dans le cas d'un tel montage en porte à faux, il s'ensuit que l'application d'un moment sur les deux paliers bas et haut, associée à la rotation de calage autour de l'axe XX sur une amplitude de plus de 40 degrés, entraîne une usure des douilles. Cette usure provoque une inclinaison de l'aubage qui peut être dommageable pour le compresseur.In the case of a gas turbine engine compressor, the blade 12 is subjected to aerodynamic forces according to the arrow A. In the case of such a cantilever assembly, it follows that the application of a moment on the two low and high bearings, associated with the rotation of rotation around the axis XX on an amplitude of more than 40 degrees, causes a wear of the bushes. This wear causes an inclination of the vane which can be harmful for the compressor.

Le présent déposant s'est fixé comme objectif d'assurer le guidage des aubes de stator à calage variable de type à montage en porte à faux en prévenant ces inconvénients, à savoir :

  • L'usure des douilles du dispositif de guidage créant une inclinaison excessive des aubes sous l'effort aérodynamique.
The present applicant has set itself the objective of guiding the variable-pitch stator vanes of the cantilever mounting type by preventing these disadvantages, namely:
  • The wear of the guiding bushings creating an excessive inclination of the vanes under the aerodynamic force.

L'augmentation des efforts de manoeuvre des aubes de stator à calage variable.Increasing the operating forces of variable-pitch stator vanes.

L'invention parvient à ces objectifs avec un dispositif de guidage caractérisé par le fait que l'aube comprend une pale, une plateforme et un pivot par lequel l'aube est montée dans le carter de la turbomachine, par le fait qu'il comprend une douille avec une partie en forme de disque entre le carter et la plateforme, une nervure annulaire étant ménagée sur ladite partie en forme de disque coopérant avec une rainure complémentaire ménagée sur la plateforme, de manière à former un palier lisse entre elles.The invention achieves these objectives with a guiding device characterized in that the blade comprises a blade, a platform and a pivot through which the blade is mounted in the casing of the turbomachine, in that it comprises a sleeve with a disc-shaped portion between the housing and the platform, an annular rib being provided on said disc-shaped portion cooperating with a complementary groove on the platform, so as to form a smooth bearing therebetween.

Par le moyen de l'invention, on réduit la distance entre le point d'application de l'effort aérodynamique et le palier du dispositif de guidage du pivot situé au bas du pivot. Cette diminution de hauteur réduit le moment appliqué à l'aube. Il s'ensuit que l'effort de réaction au niveau du pivot pour s'opposer au moment est plus faible. Ainsi les efforts de matage aux contacts entre le pivot de l'aube et la douille sont plus faibles d'où une usure réduite.By means of the invention, the distance between the point of application of the aerodynamic force and the bearing of the pivot guide device located at the bottom of the pivot is reduced. This decrease in height reduces the moment applied at dawn. It follows that the reaction force at the pivot to oppose the moment is lower. Thus the matting efforts at the contacts between the pivot of the blade and the bushing are lower, resulting in reduced wear.

Le dispositif comprend éventuellement un palier haut entre la partie haute du pivot et son logement dans le carter.The device optionally comprises a high bearing between the upper part of the pivot and its housing in the housing.

Conformément à un mode de réalisation avantageux, le dispositif de guidage comprend un palier bas entre la partie basse du pivot et son logement dans le carter. Il permet de réduire encore les charges sur les douilles en les répartissant.According to an advantageous embodiment, the guiding device comprises a low bearing between the lower part of the pivot and its housing in the housing. It further reduces the load on the bushings by distributing them.

D'autres caractéristiques et avantages, apparaîtront à la lecture de deux modes de réalisation non limitatifs de l'invention en référence aux dessins annexés sur lesquels :

  • La figure 1 représente une aube de stator à calage variable, de l'art antérieur, montée dans un carter de compresseur;
  • La figure 2 représente une aube de stator à calage variable avec un dispositif de guidage selon un premier mode de réalisation;
  • La figure 3 montre une aube de stator à calage variable avec un dispositif de guidage selon un deuxième mode de réalisation.
Other characteristics and advantages will appear on reading two non-limiting embodiments of the invention with reference to the accompanying drawings in which:
  • FIG. 1 represents a variable-pitch stator vane of the prior art, mounted in a compressor casing;
  • FIG. 2 represents a variable-pitch stator vane with a guiding device according to a first embodiment;
  • FIG. 3 shows a variable-pitch stator blade with a guiding device according to a second embodiment.

En se reportant à la figure 2, on voit une aube de stator à calage variable 20 à montage en porte à faux avec une pale 22, une plateforme 23 et un pivot 24. Le pivot 24 est logé dans un alésage radial du carter 3 qui est par exemple celui du compresseur d'un moteur à turbine à gaz. L'aube est retenue par un écrou 28 dans sa partie haute et relié à un levier 27 de commande de calage comme cela est connu. Les termes haut et bas désignent la position par rapport à l'axe du moteur, un élément haut étant éloigné de l'axe par rapport à un élément bas. Le dispositif de guidage de l'aube est constitué ici d'une douille cylindrique 25 entre le pivot 24 et le logement dans le carter 3. Cette douille assure également l'étanchéité. Une douille 26 dans la partie basse du pivot, comprend une partie cylindrique 26a entre la partie basse du pivot et le logement dans le carter. La douille se prolonge par une partie globalement en forme de disque 26b, entre la plateforme 23 et le fond du lamage du carter constituant le logement de celle-ci. Conformément à l'invention, un palier est formé au niveau de la plateforme. Selon ce mode de réalisation, le palier est formé par la coopération d'une nervure 26b1 et d'une rainure 23b1. La nervure circulaire est ménagée sur la face de la douille tournée vers la plateforme 23. Le terme circulaire comprend aussi le mode de réalisation où la nervure s'étend sur un ou plusieurs arcs de cercles. Cette nervure est selon cet exemple à section carré et est ajustée dans la rainure 23b1 de forme complémentaire, creusée dans la face de la plateforme tournée vers la douille 26. Les deux parties, nervure et rainure, forment un palier intégré 23b1-26b1 qui reprend les efforts aérodynamiques appliqués sur la pale et les transmet au carter 3.Referring to FIG. 2, a variably variable stator vane 20 is seen to be cantilevered with a blade 22, a platform 23 and a pivot 24. The pivot 24 is housed in a radial bore of the casing 3 which is for example that of the compressor of a gas turbine engine. The blade is retained by a nut 28 in its upper part and connected to a lever 27 for stall control as is known. The terms high and low designate the position relative to the axis of the motor, a high element being away from the axis relative to a low element. The guide device of the blade is constituted by a cylindrical sleeve 25 between the pivot 24 and the housing in the housing 3. This sleeve also provides sealing. A socket 26 in the lower part of the pivot, comprises a part cylindrical 26a between the lower part of the pivot and the housing in the housing. The sleeve is extended by a generally disk-shaped portion 26b, between the platform 23 and the bottom of the housing counterbore constituting the housing thereof. According to the invention, a bearing is formed at the platform. According to this embodiment, the bearing is formed by the cooperation of a rib 26b1 and a groove 23b1. The circular rib is formed on the face of the sleeve facing the platform 23. The circular term also includes the embodiment wherein the rib extends over one or more arcs of circles. This rib is according to this example square section and is adjusted in the groove 23b1 of complementary shape, hollowed in the face of the platform facing the sleeve 26. The two parts, rib and groove form an integrated bearing 23b1-26b1 which takes again the aerodynamic forces applied on the blade and transmits them to the casing 3.

On note que dans cette réalisation, il n'y a pas de contact glissant entre la partie basse du pivot 24 et la douille 26a. La partie haute du pivot forme un palier haut 29Note that in this embodiment, there is no sliding contact between the lower part of the pivot 24 and the sleeve 26a. The upper part of the pivot forms a high bearing 29

On note également que le rayon du palier intégré est choisi de manière à ce que les frottements entre la nervure 26bl de la douille 26 et la rainure 23bl de la plateforme induisent une résistance au pivotement axial de l'aube qui soit acceptable et ne perturbe pas le fonctionnement des moyens de commande du calage. Pendant la rotation de l'aube autour de son axe, la douille 26 reste immobile par rapport au carter.It is also noted that the radius of the integrated bearing is chosen so that the friction between the rib 26bl of the sleeve 26 and the groove 23bl of the platform induce a resistance to the axial pivoting of the blade which is acceptable and does not disturb the operation of the control means of the setting. During the rotation of the blade around its axis, the sleeve 26 remains stationary relative to the housing.

A titre d'exemple on a chiffré l'avantage de cette disposition : les forces en présence sont la force F aérodynamique, la force F1 de réaction du carter sur la partie basse du dispositif de guidage et la force F2 de réaction du carter sur la partie haute du dispositif de guidage.By way of example, the advantage of this arrangement has been quantified: the forces in the presence are the aerodynamic force F, the reaction force F1 of the casing on the lower part of the guiding device and the force F2 of the reaction of the casing on the upper part of the guiding device.

L, 50mm, est la distance entre le point d'application de F et le palier bas, L1, 40 mm, est la distance entre le palier bas et le palier haut. Pour une valeur F de 100 daN, les valeurs de F1 et F2 sont alors respectivement de 225 daN et 125 daN.L, 50mm, is the distance between the point of application of F and the low bearing, L1, 40 mm, is the distance between the low bearing and the high bearing. For a value F of 100 daN, the values of F1 and F2 are respectively 225 daN and 125 daN.

On voit sur le tableau ci dessous qu'en rapprochant le palier bas de 8 mm de la pale, le gain en réduction d'effort est de 17% et 30% respectivement. Art antérieur Invention Gain F (daN) 100 100 F1 (daN) 225 187,5 17% F2 (daN) 125 87,5 30% L (mm) 50 42 L1 (mm) 40 48 Moment 5000 4200 We see in the table below that bringing the low bearing 8 mm of the blade, the gain in effort reduction is 17% and 30% respectively. Prior art Invention Gain F (daN) 100 100 F1 (daN) 225 187.5 17% F2 (daN) 125 87.5 30% L (mm) 50 42 L1 (mm) 40 48 Moment 5000 4200

On a représenté sur la figure 3 une variante de l'invention selon laquelle on maintient le palier au bas du pivot par rapport à la solution précédente. Avec ce palier bas doublant le palier intégré à la plateforme, la charge est répartie entre F1 et F1'. Les références sont les mêmes que pour la solution précédente. On distingue le palier bas supplémentaire formé par la coopération de la frette 31 montée sur le pivot 24 avec la portion cylindrique 26a de la douille 26.FIG. 3 shows a variant of the invention according to which the bearing is maintained at the bottom of the pivot relative to the previous solution. With this low bearing doubling the bearing integrated in the platform, the load is distributed between F1 and F1 '. The references are the same as for the previous solution. We distinguish the additional low bearing formed by the cooperation of the hoop 31 mounted on the pivot 24 with the cylindrical portion 26a of the sleeve 26.

Claims (5)

Dispositif de guidage d'aube de stator à calage variable dans une turbomachine axiale, l'aube comprenant une pale (22), une plateforme (23) et un pivot (24) par lequel l'aube est montée dans le carter (3) de la turbomachine, caractérisé par le fait qu'il comprend une douille (26) avec une partie (26b) en forme de disque entre le carter et la plateforme (23), une nervure circulaire (26b1) étant ménagée sur ladite partie en forme de disque coopérant avec une rainure (23b1) complémentaire ménagée sur la plateforme, de manière à former un palier lisse entre elles.Variable-pitch stator vane guiding device in an axial turbomachine, the blade comprising a blade (22), a platform (23) and a pivot (24) through which the blade is mounted in the housing (3) of the turbomachine, characterized in that it comprises a bushing (26) with a disc-shaped portion (26b) between the housing and the platform (23), a circular rib (26b1) being provided on said shaped portion disk cooperating with a groove (23b1) complementary formed on the platform, so as to form a smooth bearing between them. Dispositif de guidage, selon la revendication 1, comprenant un palier haut entre la partie haute du pivot (24) et son logement dans le carter (3).Guiding device according to claim 1, comprising a high bearing between the upper part of the pivot (24) and its housing in the housing (3). Dispositif de guidage, selon la revendication 1 ou 2, comprenant un palier bas (31) supplémentaire entre la partie basse du pivot (24) et son logement dans le carter.Guiding device according to claim 1 or 2, comprising a further low bearing (31) between the lower part of the pivot (24) and its housing in the housing. Dispositif de guidage, selon la revendication 1, dont la douille (26) comprend une portion cylindrique (26a) entre le pivot (24) et le carter.Guiding device according to claim 1, the bush (26) comprises a cylindrical portion (26a) between the pivot (24) and the housing. Turbomachine avec des aubes de stator à calage variable, les aubes comprenant un pivot (24) par lequel elles sont montées en porte à faux dans le carter (3) de la turbomachine et une plateforme (23) caractérisée par le fait qu'une douille (26) avec une partie en forme de disque est interposée entre le carter (3) et la plateforme (23), la douille comprenant une nervure (26b1) ménagée sur ladite partie en forme de disque et la plateforme une rainure circulaire (23b1), la nervure et la rainure formant un palier lisse.Turbomachine with variable-pitch stator vanes, the vanes comprising a pivot (24) by which they are cantilevered in the casing (3) of the turbomachine and a platform (23) characterized by the fact that a bushing (26) with a disk-shaped portion is interposed between the housing (3) and the platform (23), the socket comprising a rib (26b1) formed on said disk-shaped portion and the platform a circular groove (23b1) , the rib and the groove forming a plain bearing.
EP06076731.6A 2005-10-18 2006-09-18 Bearing device of a variable guide vane in an axial turbomachine Active EP1777375B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0553159A FR2892147B1 (en) 2005-10-18 2005-10-18 VARIABLE-TIMING STATOR VANE GUIDING DEVICE IN AXIAL TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP1777375A1 true EP1777375A1 (en) 2007-04-25
EP1777375B1 EP1777375B1 (en) 2014-07-16

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US (1) US7661925B2 (en)
EP (1) EP1777375B1 (en)
FR (1) FR2892147B1 (en)

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EP2622178A4 (en) * 2010-09-30 2017-12-27 Rolls-Royce North American Technologies, Inc. Seal arrangement for variable vane
DE102017222209A1 (en) * 2017-12-07 2019-06-13 MTU Aero Engines AG Guide vane connection and turbomachine

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FR2913052B1 (en) * 2007-02-22 2011-04-01 Snecma CONTROL OF AUBES WITH VARIABLE SETTING ANGLE
US10570762B2 (en) * 2015-05-15 2020-02-25 United Technologies Corporation Vane strut positioning and securing systems including locking washers
FR3039226B1 (en) 2015-07-20 2017-07-14 Snecma VARIABLE SHAFT OF AUBES FOR A TURBOMACHINE
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

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US3558237A (en) * 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
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EP1717450A2 (en) * 2005-04-28 2006-11-02 Snecma Variable stator blade, method for repair of a blade

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2622178A4 (en) * 2010-09-30 2017-12-27 Rolls-Royce North American Technologies, Inc. Seal arrangement for variable vane
DE102017222209A1 (en) * 2017-12-07 2019-06-13 MTU Aero Engines AG Guide vane connection and turbomachine
US10982558B2 (en) 2017-12-07 2021-04-20 MTU Aero Engines AG Guide vane connection

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Publication number Publication date
US7661925B2 (en) 2010-02-16
US20080025837A1 (en) 2008-01-31
EP1777375B1 (en) 2014-07-16
FR2892147B1 (en) 2010-09-17
FR2892147A1 (en) 2007-04-20

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