EP0780544B1 - Root bearing for a pivoting blade - Google Patents

Root bearing for a pivoting blade Download PDF

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Publication number
EP0780544B1
EP0780544B1 EP96402807A EP96402807A EP0780544B1 EP 0780544 B1 EP0780544 B1 EP 0780544B1 EP 96402807 A EP96402807 A EP 96402807A EP 96402807 A EP96402807 A EP 96402807A EP 0780544 B1 EP0780544 B1 EP 0780544B1
Authority
EP
European Patent Office
Prior art keywords
ring
socket
bearing
axis
journal
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 - Lifetime
Application number
EP96402807A
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German (de)
French (fr)
Other versions
EP0780544A1 (en
Inventor
Jean-Louis Charbonnel
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
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0780544A1 publication Critical patent/EP0780544A1/en
Application granted granted Critical
Publication of EP0780544B1 publication Critical patent/EP0780544B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • the subject of the invention is a level inner end of pivoting vane.
  • Modern turbomachines include often stator blades with variable setting, that is to say the orientation of which can be changed by a pivoting movement to modify the recovery of the gases they cause and optimize machine performance at different speeds of it.
  • the blades 1 with variable setting are arranged in stages circulars which also alternate with floors circular vanes 2 fixed to the rotor 3; the vanes 1 have an outer end pivot 4, engaged in a bearing 5 of the stator and protruding at the outside to finish in a head 7 grabbed by a control lever 8, and control levers 8 of blades 1 of the same stage are articulated to their other end to a control ring 9 which surrounds the stator: the rotation of the control ring 9 around of its axis therefore produces the tilting of the levers 8 and the pivoting of the blades 1.
  • the internal end of the blades 1 comprises a internal pivot 10 engaged in an internal bearing 11, in cylindrical socket shape in this design classic and housed in a common link ring 12 to all the vanes 1 on the same stage and whose role is to strengthen the mounting of the blades 1 while helping to define the gas flow stream 13 with platforms 14 movable vanes 2 and wear a labyrinth seal 15 with the rotor 3.
  • the internal bearings 11 are the most often a substantially cylinder-shaped socket hollow and antifriction material, which therefore allows internal pivots 10 to turn easily.
  • the internal bearings 11 must be replaced frequently, as a result of efforts aerodynamics exerted on the blades 1, which drive their deformation and the displacement of the ring of link 12: the internal pivots 10 are then oriented obliquely in the internal bearings 11 and wear them out by expanding them.
  • the internal bearings 11 are mounted with a clamp in the connecting ring 12 and with a just sliding fit around the pivot internal 10. Wear therefore almost immediately a significant change in the adjustment.
  • the invention is based on the idea that wear and tear of the bearing part can be prevented without it should give him the freedom of movement of a patella.
  • the rectifier composed of vanes 1 and link ring 12 had low overall inertia rotating around the axis X of the machine and of the connecting ring 12, while its inertia in translation along this axis was much stronger, which explains why the movements of the internal pivots 10 and the wear they cause on the bearing parts are much more important in transverse direction than in direction longitudinal.
  • the level of the invention therefore has as characteristic that it can rotate in the ring of link only when the pivot he wears inflate a transverse rotation, around an axis parallel to the X axis of the machine.
  • the invention relates to an end bearing internal pivoting blade, engaged in a ring of connection of pivoting vanes on the same stage and comprising a socket surrounding the pivot, characterized in that it includes a revolving pin in a drilling of the axis ring parallel to the axis of the ring, and in that the sleeve, integral with the pin, is free to play in the ring.
  • the bearing part 18, that is to say that which connects each of the internal pivots 10 to the ring of link 12, is composed of a socket 19, cylindrical like known socket 11, and two portions of pin 20 in extension and located on each side of the socket 19, which forms a single piece with them.
  • the journal portions 20 therefore have an axis of common rotation X 'parallel to the machine axis X and of the connecting ring 12. As in Figures 2 and 3 the show, the journal portions 20 are engaged in bore portions 21 of the connecting ring 12 so that it can rotate freely around this axis X '.

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

Description

Le sujet de l'invention est un palier d'extrémité interne d'aube pivotante.The subject of the invention is a level inner end of pivoting vane.

Les turbomachines modernes comprennent souvent des aubes de stator à calage variable, c'est-à-dire dont il est possible de modifier l'orientation par un mouvement de pivotement pour modifier le redressement des gaz qu'elles provoquent et optimiser les performances de la machine aux différents régimes de celle-ci. Comme on le voit à la figure 1, les aubes 1 à calage variable sont disposées en étages circulaires qui alternent avec des étages également circulaires d'aubes mobiles 2 fixées au rotor 3 ; les aubes 1 possèdent un pivot d'extrémité externe 4, engagé dans un palier 5 du stator et dépassant à l'extérieur pour finir en une tête 7 saisie par un levier de commande 8, et les leviers de commande 8 des aubes 1 d'un même étage sont articulés à leur autre extrémité à un anneau de commande 9 qui entoure le stator : la rotation de l'anneau de commande 9 autour de son axe produit donc le basculement des leviers 8 et le pivotement des aubes 1.Modern turbomachines include often stator blades with variable setting, that is to say the orientation of which can be changed by a pivoting movement to modify the recovery of the gases they cause and optimize machine performance at different speeds of it. As seen in Figure 1, the blades 1 with variable setting are arranged in stages circulars which also alternate with floors circular vanes 2 fixed to the rotor 3; the vanes 1 have an outer end pivot 4, engaged in a bearing 5 of the stator and protruding at the outside to finish in a head 7 grabbed by a control lever 8, and control levers 8 of blades 1 of the same stage are articulated to their other end to a control ring 9 which surrounds the stator: the rotation of the control ring 9 around of its axis therefore produces the tilting of the levers 8 and the pivoting of the blades 1.

L'extrémité interne des aubes 1 comprend un pivot interne 10 engagé dans un palier interne 11, en forme de douille cylindrique dans cette conception classique et logé dans un anneau de liaison 12, commun à toutes les aubes 1 d'un même étage et dont le rôle est de renforcer le montage des aubes 1 tout en contribuant à délimiter la veine d'écoulement des gaz 13 avec des plates-formes 14 des aubes mobiles 2 et à porter un joint d'étanchéité à labyrinthe 15 avec le rotor 3.The internal end of the blades 1 comprises a internal pivot 10 engaged in an internal bearing 11, in cylindrical socket shape in this design classic and housed in a common link ring 12 to all the vanes 1 on the same stage and whose role is to strengthen the mounting of the blades 1 while helping to define the gas flow stream 13 with platforms 14 movable vanes 2 and wear a labyrinth seal 15 with the rotor 3.

Les paliers internes 11 sont le plus souvent une douille sensiblement en forme de cylindre creux et en matière à antifriction, qui permet donc aux pivots internes 10 de tourner facilement. On observe cependant que les paliers internes 11 doivent être remplacés fréquemment, en conséquence des efforts aérodynamiques exercés sur les aubes 1, qui entraínent leur déformation et le déplacement de l'anneau de liaison 12 : les pivots internes 10 s'orientent alors obliquement dans les paliers internes 11 et les usent en les élargissant. En effet, les paliers internes 11 sont montés avec un serrage dans l'anneau de liaison 12 et avec un ajustement juste glissant autour du pivot interne 10. L'usure entraíne donc presque tout de suite une modification importante de l'ajustement.The internal bearings 11 are the most often a substantially cylinder-shaped socket hollow and antifriction material, which therefore allows internal pivots 10 to turn easily. We observe however the internal bearings 11 must be replaced frequently, as a result of efforts aerodynamics exerted on the blades 1, which drive their deformation and the displacement of the ring of link 12: the internal pivots 10 are then oriented obliquely in the internal bearings 11 and wear them out by expanding them. In fact, the internal bearings 11 are mounted with a clamp in the connecting ring 12 and with a just sliding fit around the pivot internal 10. Wear therefore almost immediately a significant change in the adjustment.

On a donc déjà proposé de remplacer les paliers de forme cylindrique par des paliers à rotule comme dans les brevets français 2 599 785, avec l'avantage que les paliers basculent alors dans leur logement de l'anneau de liaison 12 en même temps que les pivots ; mais on peut regretter l'emploi d'un tel dispositif, car des logements sphériques pour les paliers sont plus difficiles à exécuter.We have therefore already proposed to replace the cylindrical bearings by spherical bearings as in French patents 2,599,785, with the advantage that the bearings then tilt in their housing of the connecting ring 12 at the same time as the pivots; but we can regret the use of such device, because spherical housings for bearings are more difficult to execute.

L'invention repose sur l'idée que l'usure de la pièce de palier peut être prévenue sans qu'il faille lui conférer la liberté de mouvement d'une rotule. En effet, on s'est aperçu que le redresseur composé des aubes 1 et de l'anneau de liaison 12 avait une faible inertie d'ensemble en rotation autour de l'axe X de la machine et de l'anneau de liaison 12, alors que son inertie en translation suivant cet axe était beaucoup plus forte, ce qui explique que les mouvements des pivots internes 10 et l'usure qu'ils provoquent sur les pièces de palier sont beaucoup plus importants en direction transversale qu'en direction longitudinale.The invention is based on the idea that wear and tear of the bearing part can be prevented without it should give him the freedom of movement of a patella. In fact, we realized that the rectifier composed of vanes 1 and link ring 12 had low overall inertia rotating around the axis X of the machine and of the connecting ring 12, while its inertia in translation along this axis was much stronger, which explains why the movements of the internal pivots 10 and the wear they cause on the bearing parts are much more important in transverse direction than in direction longitudinal.

Le palier de l'invention a donc comme caractéristique qu'il peut tourner dans l'anneau de liaison seulement quand le pivot qu'il porte lui inflige une rotation transversale, autour d'un axe parallèle à l'axe X de la machine. Pour résumer, l'invention est relative à un palier d'extrémité interne d'aube pivotante, engagé dans un anneau de liaison d'aubes pivotantes d'un même étage et comprenant une douille entourant le pivot, caractérisé en ce qu'il comprend un tourillon tournant dans un perçage de l'anneau d'axe parallèle à l'axe de l'anneau, et en ce que la douille, solidaire du tourillon, est libre de jouer dans l'anneau.The level of the invention therefore has as characteristic that it can rotate in the ring of link only when the pivot he wears inflate a transverse rotation, around an axis parallel to the X axis of the machine. To summarize, the invention relates to an end bearing internal pivoting blade, engaged in a ring of connection of pivoting vanes on the same stage and comprising a socket surrounding the pivot, characterized in that it includes a revolving pin in a drilling of the axis ring parallel to the axis of the ring, and in that the sleeve, integral with the pin, is free to play in the ring.

On va maintenant décrire l'invention plus en détail à l'aide du commentaire des figures suivantes, qui sont relatives à une réalisation préférée de l'invention :

  • la figure déjà décrite illustre le lieu d'utilisation de l'invention dans une turbomachine et une conception de l'art antérieur ;
  • la figure 2 illustre un palier complet selon l'invention,
  • la figure 3 représente les paliers vus en direction longitudinale,
  • et la figure 4 représente la pièce de palier en perspective.
The invention will now be described in more detail with the aid of the commentary to the following figures, which relate to a preferred embodiment of the invention:
  • the figure already described illustrates the place of use of the invention in a turbomachine and a design of the prior art;
  • FIG. 2 illustrates a complete bearing according to the invention,
  • FIG. 3 represents the bearings seen in the longitudinal direction,
  • and Figure 4 shows the bearing part in perspective.

On passe tout de suite à la figure 2, où on retrouve l'aube 1, son pivot interne 10 et l'anneau de liaison 12. La pièce de palier 18, c'est-à-dire celle qui relie chacun des pivots internes 10 à l'anneau de liaison 12, est composée d'une douille 19, cylindrique comme la douille 11 connue, et de deux portions de tourillon 20 en prolongement et situés de chaque côté de la douille 19, qui forme une seule pièce avec eux. Les portions de tourillon 20 ont donc un axe de rotation commun X' parallèle à l'axe X de la machine et de l'anneau de liaison 12. Comme les figures 2 et 3 le montrent, les portions de tourillon 20 sont engagées dans des portions d'alésage 21 de l'anneau de liaison 12 de manière à pouvoir tourner librement autour de cet axe X'. Ces portions 21 sont ménagées en creux sur deux faces planes 22 de l'anneau de liaison 12, et un puits 23 radial s'étend entre elles, dont la largeur est un peu supérieure à celle de la douille 19. Il en résulte que celle-ci peut jouer dans le puits 23 jusqu'à ce que ses faces latérales 24 touchent les faces planes 22 : une rotation limitée de la pièce de palier 18 est donc possible par rapport à l'anneau de liaison 12, selon les mouvements que lui infligent les pivots internes 10, sans que ces mouvements aient cependant la possibilité d'user l'intérieur de la douille 19.We go immediately to Figure 2, where we finds the blade 1, its internal pivot 10 and the ring of connection 12. The bearing part 18, that is to say that which connects each of the internal pivots 10 to the ring of link 12, is composed of a socket 19, cylindrical like known socket 11, and two portions of pin 20 in extension and located on each side of the socket 19, which forms a single piece with them. The journal portions 20 therefore have an axis of common rotation X 'parallel to the machine axis X and of the connecting ring 12. As in Figures 2 and 3 the show, the journal portions 20 are engaged in bore portions 21 of the connecting ring 12 so that it can rotate freely around this axis X '. These portions 21 are hollowed out of two flat faces 22 of the connecting ring 12, and a well 23 radial extends between them, the width of which is a little higher than that of the socket 19. This results that it can play in well 23 until its lateral faces 24 touch the flat faces 22: limited rotation of the bearing part 18 is therefore possible with respect to the connecting ring 12, according to the movements inflicted by the internal pivots 10, without these movements having the possibility of using the inside of the socket 19.

Claims (3)

  1. A bearing (18) for the inner end (10) of a pivoting vane (1), the bearing being engaged in a ring (12) which interconnects pivoting vanes (1) of a single stage and comprising a socket (19) extending around the pivot pin (10), characterised in that the bearing comprises a journal (20) rotating in a bore (21) in the ring (12), the journal axis (X') extending parallel to the ring axis (X), and in that the socket (19), which is rigidly secured to the journal (20), has free play in the ring (12).
  2. A bearing according to claim 1, characterised in that the journal (20) consists of two parts between which the socket (19) is disposed.
  3. A bearing according to claim 1 or claim 2, characterised in that the socket (19) is engaged between surfaces (22) of the ring (21), the surfaces (22) serving as play-limiting stops.
EP96402807A 1995-12-20 1996-12-19 Root bearing for a pivoting blade Expired - Lifetime EP0780544B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9515120A FR2742799B1 (en) 1995-12-20 1995-12-20 INTERNAL END END OF PIVOTING VANE
FR9515120 1995-12-20

Publications (2)

Publication Number Publication Date
EP0780544A1 EP0780544A1 (en) 1997-06-25
EP0780544B1 true EP0780544B1 (en) 1999-03-10

Family

ID=9485705

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96402807A Expired - Lifetime EP0780544B1 (en) 1995-12-20 1996-12-19 Root bearing for a pivoting blade

Country Status (4)

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US (1) US5796199A (en)
EP (1) EP0780544B1 (en)
DE (1) DE69601695T2 (en)
FR (1) FR2742799B1 (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2775731B1 (en) * 1998-03-05 2000-04-07 Snecma CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING
FR2874977A1 (en) * 2004-09-07 2006-03-10 Snecma Moteurs Sa Pivoting carrier bushing for variable vane`s pivot, has polygonal transversal section and shoulder, and is composed of single piece, where shoulder cooperates with complementary notch formed in inner ring sector of inner ring
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines
US7278819B2 (en) * 2005-07-05 2007-10-09 General Electric Company Variable stator vane lever arm assembly and method of assembling same
FR2889242B1 (en) * 2005-07-27 2007-11-02 Snecma SOCKET FOR VANE PIVOT WITH VARIABLE SETTING ANGLE FOR TURBOMACHINE
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
US7854586B2 (en) * 2007-05-31 2010-12-21 United Technologies Corporation Inlet guide vane inner air seal surge retaining mechanism
FR2920469A1 (en) 2007-08-30 2009-03-06 Snecma Sa TURBOMACHINE VARIABLE CALIBRATION
DE102008021683A1 (en) * 2008-04-30 2009-11-05 Rolls-Royce Deutschland Ltd & Co Kg Rotating unit for an axial compressor
EP2295732A1 (en) * 2009-09-14 2011-03-16 Alstom Technology Ltd Axial turbine and method for discharging a flow from an axial turbine
DE102011077626A1 (en) * 2011-06-16 2012-12-20 Bosch Mahle Turbo Systems Gmbh & Co. Kg Wastegate valve device
US10125789B2 (en) * 2013-02-15 2018-11-13 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the body
EP2952693B1 (en) 2014-06-06 2021-04-28 Raytheon Technologies Corporation Case with vane retention feature
EP3009604B1 (en) * 2014-09-19 2018-08-08 United Technologies Corporation Radially fastened fixed-variable vane system
RU2612666C1 (en) * 2015-12-09 2017-03-13 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Regulated guide vanes of axial compressor of turbine machine
DE102016207212A1 (en) * 2016-04-28 2017-11-02 MTU Aero Engines AG Guide vane ring for a turbomachine
DE102016215807A1 (en) * 2016-08-23 2018-03-01 MTU Aero Engines AG Inner ring for a vane ring of a turbomachine
DE102017109952A1 (en) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotor device of a turbomachine
DE102018210601A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE
US10808568B2 (en) 2018-09-12 2020-10-20 Raytheon Technologies Corporation Airfoil assembly for a gas turbine engine
US11816936B2 (en) 2018-12-03 2023-11-14 Bendix Commercial Vehicle Systems, Llc System and method for detecting driver tampering of vehicle information systems
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 (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4363600A (en) * 1981-04-06 1982-12-14 General Motors Corporation Variable vane mounting
FR2524934B1 (en) * 1982-04-08 1986-12-26 Snecma SAFETY STOP DEVICE FOR VARIABLE SETTING STATOR BLADE PIVOT
FR2556410B1 (en) * 1983-12-07 1986-09-12 Snecma DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR
FR2599785B1 (en) * 1986-06-04 1990-10-12 Snecma VARIABLE SETTING AIR INTAKE DIRECTOR FOR TURBOJET
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
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
FR2691507B1 (en) * 1992-05-20 1994-07-08 Snecma WATERPROOFING STRUCTURE FOR A PIVOTING VANE OF A TURBOMACHINE.
FR2696208B1 (en) * 1992-09-30 1994-11-10 Snecma Dawn with variable setting.
DE4237031C1 (en) * 1992-11-03 1994-02-10 Mtu Muenchen Gmbh Adjustable guide vane
FR2699595B1 (en) * 1992-12-23 1995-01-20 Snecma Device for guiding in rotation a control ring for pivoting vanes.
US5517817A (en) * 1993-10-28 1996-05-21 General Electric Company Variable area turbine nozzle for turbine engines
US5593275A (en) * 1995-08-01 1997-01-14 General Electric Company Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine

Also Published As

Publication number Publication date
FR2742799B1 (en) 1998-01-16
FR2742799A1 (en) 1997-06-27
US5796199A (en) 1998-08-18
DE69601695T2 (en) 2000-06-29
EP0780544A1 (en) 1997-06-25
DE69601695D1 (en) 1999-04-15

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