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EP0780545A1 - Arrangement of the root ends of a variable angle row of blades - Google Patents

Arrangement of the root ends of a variable angle row of blades Download PDF

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Publication number
EP0780545A1
EP0780545A1 EP96402808A EP96402808A EP0780545A1 EP 0780545 A1 EP0780545 A1 EP 0780545A1 EP 96402808 A EP96402808 A EP 96402808A EP 96402808 A EP96402808 A EP 96402808A EP 0780545 A1 EP0780545 A1 EP 0780545A1
Authority
EP
European Patent Office
Prior art keywords
blades
arrangement
ring
pivots
variable
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.)
Granted
Application number
EP96402808A
Other languages
German (de)
French (fr)
Other versions
EP0780545B1 (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
Priority date (The priority date 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 date listed.)
Filing date
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 EP0780545A1 publication Critical patent/EP0780545A1/en
Application granted granted Critical
Publication of EP0780545B1 publication Critical patent/EP0780545B1/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 invention relates to an arrangement of internal ends of a stage of variable-pitch blades.
  • So called blades related to a stator but whose inclination can be changed at will to deflect or straighten more or less the flow of gas passing through them to obtain the best performance characteristics at different speeds of the machine in which they are located.
  • the outer ends of these blades are then supported by a bearing formed in the wall of the stator, and the inner ends, close to the rotor, are retained in a common connecting ring.
  • the invention is therefore characterized, compared to this prior art, by the combination of a threaded sleeve engaged in the connecting ring and serving as a bearing for the pivot and of brake parts engaged both in the notches of the pivots and sockets to hold them in rotation.
  • FIG. 1 A circular stage of blades 1 with variable setting is therefore shown in FIG. 1; he is located between two stages of movable vanes 2, linked to a rotor 3, while the variable-pitch vanes 1 are linked to a stator wall 4 at their external ends 5, where they end in an external pivot 6 passing through a bearing 7 cleaning through the wall of the stator 4, and, beyond this wall, by a head 8 of square or other section which is gripped by a lever, not shown, articulated to a control ring surrounding the turbomachine.
  • the control ring When the control ring is rotated, it switches the control levers and therefore rotates the external pivots 6 and the blades 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

The assembly consists of a coupling ring (10) which is common to all the blades (1) of the turbine stage. A threaded bush (13) receives each blade pivot shank (15), screwed into a threaded hole in the ring. Each bush and blade shank has a groove (18) designed to receive a retaining pin (16) when aligned. Each blade shank groove is annular, while each bush groove is straight and lies at a tangent to the surface of the shank. The retaining pin is hollow and made from a carbon-based composition material. The assembly also has a thrust ring (19) which surrounds the shank and fits between parallel flat surfaces (20,21) lying perpendicular to the shank, the coupling ring and blade. The inner end of each threaded bush has a polygonal head (22) for adjustment which makes contact with the surface of a circular rail (24) which is attached to the inside of the coupling ring by tongues (25).

Description

L'invention a trait à un agencement d'extrémités internes d'un étage d'aubes à calage variable.The invention relates to an arrangement of internal ends of a stage of variable-pitch blades.

On appelle ainsi des aubes liés à un stator mais dont l'inclinaison peut être modifiée à volonté pour dévier ou redresser plus ou moins le flux de gaz qui les traverse afin d'obtenir les meilleures caractéristiques de rendement aux différents régimes de la machine dans laquelle elles sont situées. Les extrémités externes de ces aubes sont alors soutenues par un palier ménagé dans la paroi du stator, et les extrémités internes, proches du rotor, sont retenues dans un anneau de liaison commun.So called blades related to a stator but whose inclination can be changed at will to deflect or straighten more or less the flow of gas passing through them to obtain the best performance characteristics at different speeds of the machine in which they are located. The outer ends of these blades are then supported by a bearing formed in the wall of the stator, and the inner ends, close to the rotor, are retained in a common connecting ring.

Un agencement connu et décrit en particulier dans le brevet français 2 556 410 consiste à pourvoir les extrémités internes des aubes de pivots qui tournent dans des douilles solidaires de l'anneau ; ces douilles peuvent notamment présenter une surface externe filetée, ce qui permet de les visser dans des évidements de l'anneau. L'anneau est alors soutenu, mais des glissements des pivots dans les douilles et par rapport à l'anneau restent possibles si bien que l'anneau peut jouer dans la veine des gaz et nuire ainsi au bon fonctionnement de la machine.A known arrangement, described in particular in French patent 2,556,410, consists in providing the internal ends of the blades with pivots which rotate in sockets integral with the ring; these sockets can in particular have a threaded external surface, which allows them to be screwed into recesses in the ring. The ring is then supported, but sliding of the pivots in the sockets and relative to the ring remains possible so that the ring can play in the gas flow and thus affect the proper functioning of the machine.

Dans d'autres conceptions, telle que celle du brevet 2 644 525, des pivots d'aubes (à vrai dire, des pivots de l'extrémité externe) sont retenus dans des paliers par des pièces de frein, c'est-à-dire des pièces d'arrêt du mouvement de translation des pivots dans les paliers. Mais pas plus que dans le cas précédent, on ne peut régler une position convenable des aubes, qui sont alors retenues à une position fixe par rapport à la pièce qui les porte.In other designs, such as that of patent 2,644,525, blade pivots (actually, pivots of the outer end) are retained in bearings by brake parts, i.e. say parts for stopping the translational movement of the pivots in the bearings. But no more than in the previous case, we can not adjust a suitable position vanes, which are then retained in a fixed position relative to the part which carries them.

L'invention se caractérise donc, par rapport à cet art antérieur, par la combinaison d'une douille filetée engagée dans l'anneau de liaison et servant de palier au pivot et de pièces de frein engagées à la fois dans des encoches des pivots et des douilles pour les retenir en rotation.The invention is therefore characterized, compared to this prior art, by the combination of a threaded sleeve engaged in the connecting ring and serving as a bearing for the pivot and of brake parts engaged both in the notches of the pivots and sockets to hold them in rotation.

Il est ainsi possible de régler la position axiale des aubes dans l'anneau en vissant plus ou moins profondément les douilles, ce qui serait inopérant dans le brevet 2 556 410 où le filetage n'est qu'un moyen de retenue des douilles ; il est alors indiqué qu'une butée de réglage de position des aubes par rapport à l'anneau ne se produise plus entre une plate-forme des aubes et les douilles comme dans ce brevet mais par une butée de ces plates-formes contre l'anneau lui-même, ou de préférence contre une pièce de palier butant contre l'anneau.It is thus possible to adjust the axial position of the blades in the ring by screwing the bushings more or less deeply, which would be inoperative in patent 2,556,410 where the threading is only a means of retaining the bushings; it is then indicated that a stop for adjusting the position of the blades relative to the ring no longer occurs between a platform of the blades and the bushings as in this patent but by a stop of these platforms against the ring itself, or preferably against a bearing piece abutting against the ring.

De préférence, les encoches de pivots sont circulaires, les encoches de douilles sont rectilignes et tangentes aux encoches de pivot et les pièces de frein sont des barrettes glissées dans les encoches de douilles.Preferably, the pivot notches are circular, the socket notches are rectilinear and tangent to the pivot notches and the brake parts are bars slid into the socket notches.

L'invention va maintenant être décrite plus en détail à l'aide des figures suivantes, annexées à titre illustratif et non limitatif :

  • la figure 1 est une vue générale de l'étage d'aubes,
  • la figure 2 représente l'agencement conforme à l'invention,
  • et la figure 3 est une coupe suivant la ligne III-III sur la figure 2.
The invention will now be described in more detail with the aid of the following figures, which are given by way of illustration and not limitation:
  • FIG. 1 is a general view of the blade stage,
  • FIG. 2 represents the arrangement in accordance with the invention,
  • and Figure 3 is a section on the line III-III in Figure 2.

On a représenté donc un étage circulaire d'aubes 1 à calage variable sur la figure 1 ; il est situé entre deux étages d'aubes mobiles 2, liés à un rotor 3, alors que les aubes 1 à calage variable sont liées à une paroi de stator 4 à leurs extrémités externes 5, où elles se terminent par un pivot externe 6 traversant un palier 7 ménage à travers la paroi du stator 4, et, au-delà de cette paroi, par une tête 8 à section carrée ou autre qui est saisie par un levier, non représenté, articulé à un anneau de commande entourant la turbomachine. Quand l'anneau de commande est mis en rotation, il fait basculer les leviers de commande et fait donc tourner les pivots externes 6 et les aubes 1.A circular stage of blades 1 with variable setting is therefore shown in FIG. 1; he is located between two stages of movable vanes 2, linked to a rotor 3, while the variable-pitch vanes 1 are linked to a stator wall 4 at their external ends 5, where they end in an external pivot 6 passing through a bearing 7 cleaning through the wall of the stator 4, and, beyond this wall, by a head 8 of square or other section which is gripped by a lever, not shown, articulated to a control ring surrounding the turbomachine. When the control ring is rotated, it switches the control levers and therefore rotates the external pivots 6 and the blades 1.

Les extrémités opposées ou extrémités internes 9 des aubes 1 sont liées entre elles par un anneau de liaison 10 associé au rotor 3 par un joint à labyrinthe 11 qui établit l'étanchéité interdisant aux gaz en mouvement dans la veine de contourner les aubes à calage variable 1 ; l'anneau de liaison 10 porte des évidements taraudés 12 dans lesquels des douilles filetées 13 sont engagées par vissage ; il vient en prolongement de plates-formes annulaires 23 des aubes mobiles 2 pour délimiter la veine d'écoulement des gaz de façon aussi continue et lisse que possible. Si on commence à se reporter à la figure 2, on voit que les douilles 13 comprennent un perçage central 14 dans lequel un pivot 15, terminant une aube 1 respective de ce côté, est engagé en pouvant à la fois y coulisser et y tourner. Comme le mouvement de translation a la conséquence défavorable qu'il laisse l'anneau de liaison 10 flotter et perturbe donc le joint à labyrinthe 11 en approchant ou éloignant ses parties solidaires du rotor 3 et du stator, tout en détruisant l'alignement entre l'anneau de liaison 10 et les plates-formes 23 des aubes mobiles 2, on interdit ce mouvement par un dispositif visible également à la figure 3 et composé essentiellement d'une barrette 16 rectiligne, engagée dans une encoche rectiligne 17 qui traverse horizontalement (c'est-à-dire perpendiculairement au pivot 15) la douille 13 de part en part et affleure dans le perçage 14, où elle est tangente à une rainure circulaire 18 ménagée autour du pivot 15 : la barrette 16 occupe donc une partie de cette rainure circulaire 18 et freine la translation du pivot 15.The opposite ends or internal ends 9 of the vanes 1 are linked together by a connecting ring 10 associated with the rotor 3 by a labyrinth seal 11 which establishes the seal preventing the gases moving in the vein from bypassing the variable pitch vanes 1; the connecting ring 10 carries threaded recesses 12 in which threaded sleeves 13 are engaged by screwing; it comes in extension of annular platforms 23 of the movable vanes 2 to delimit the gas flow stream as continuously and smoothly as possible. If we start to refer to Figure 2, we see that the sockets 13 include a central bore 14 in which a pivot 15, ending a respective blade 1 on this side, is engaged being able to both slide and rotate there. As the translational movement has the unfavorable consequence that it leaves the connecting ring 10 floating and therefore disturbs the labyrinth seal 11 by approaching or distancing its parts integral with the rotor 3 and the stator, while destroying the alignment between the 'connecting ring 10 and the platforms 23 of the movable vanes 2, this movement is prohibited by a device also visible at the FIG. 3 and essentially composed of a rectilinear bar 16, engaged in a rectilinear notch 17 which crosses horizontally (that is to say perpendicular to the pivot 15) the sleeve 13 right through and is flush with the bore 14, where it is tangent to a circular groove 18 formed around the pivot 15: the bar 16 therefore occupies part of this circular groove 18 and slows down the translation of the pivot 15.

Une rondelle 19 servant de palier de butée est retenue entre une plate-forme 20 plane de l'aube 1, de laquelle le pivot interne 15 se dresse, et une plate-forme 21 également plane et perpendiculaire au pivot interne 15 de l'anneau de liaison 10.A washer 19 serving as a thrust bearing is retained between a flat platform 20 of the blade 1, from which the internal pivot 15 rises, and a platform 21 also flat and perpendicular to the internal pivot 15 of the ring. Liaison 10.

La position d'enfoncement correcte du pivot interne 15 dans l'anneau de liaison 10 est ainsi établie en tournant une tête polygonale 22 établie au fond de la douille 13, ce qui modifie le vissage de la douille 13 et donc la hauteur du pivot interne 15. Le joint à labyrinthe 11 est ensuite serti dans un rail circulaire 24 dans l'anneau de liaison 10 ; le rail 24 porte une languette 25 qui vient toucher un pan de la tête polygonale 22 et interdit alors à la douille 13 de se déplacer pendant le fonctionnement de la machine. L'épaisseur de la rondelle 19 est choisie en fonction du réglage souhaité.The correct insertion position of the internal pivot 15 in the connecting ring 10 is thus established by turning a polygonal head 22 established at the bottom of the sleeve 13, which modifies the screwing of the sleeve 13 and therefore the height of the internal pivot 15. The labyrinth seal 11 is then crimped into a circular rail 24 in the connecting ring 10; the rail 24 carries a tongue 25 which comes to touch a section of the polygonal head 22 and then prevents the sleeve 13 from moving during the operation of the machine. The thickness of the washer 19 is chosen according to the desired setting.

La barrette 16 peut être pleine ou évidée au centre, et métallique ou en matière composite à base de carbone ; ce sont ces dernières possibilités qui sont préférées, car elles permettent de réduire les efforts à l'assemblage.The bar 16 can be full or hollowed out in the center, and metallic or made of carbon-based composite material; it is these latter possibilities which are preferred, since they make it possible to reduce the efforts during assembly.

Claims (6)

Agencement d'extrémités internes d'un étage d'aubes à calage variable (1), comprenant un anneau de liaison (10) commun aux aubes, des douilles filetées (13) respectivement associées aux aubes (1), vissées dans des évidements (12) de l'anneau et dans lesquelles des pivots (15) d'extrémité des aubes pénètrent en coulissant, caractérisé en ce que les douilles (13) et les pivots (15) sont pourvus d'encoches (17, 18) en regard dans lesquelles sont introduites des pièces de frein (16) perpendiculaires aux pivots.Arrangement of internal ends of a stage of variable-pitch blades (1), comprising a connecting ring (10) common to the blades, threaded bushings (13) respectively associated with the blades (1), screwed into recesses ( 12) of the ring and into which pivots (15) of the end of the blades penetrate by sliding, characterized in that the bushings (13) and the pivots (15) are provided with notches (17, 18) facing each other into which brake parts (16) are introduced perpendicular to the pivots. Agencement d'extrémités internes d'un étage d'aubes à calage variable selon la revendication 1, caractérisé en ce que les encoches (18) de pivots sont circulaires, les encoches (17) de douilles sont rectilignes et tangentes aux encoches de pivot et les pièces de frein sont des barrettes glissées dans les encoches de douilles.Arrangement of internal ends of a stage of variable-pitch vanes according to claim 1, characterized in that the notches (18) of pivots are circular, the notches (17) of bushings are rectilinear and tangent to the pivot notches and the brake parts are bars slid into the socket notches. Agencement d'extrémités internes d'un étage d'aubes à calage variable selon l'une quelconque des revendications 1 ou 2, caractérisé en ce qu'il comprend des rondelles de butée (19) engagées autour des pivots (15) et retenues entre des surfaces planes (20, 21), parallèles entre elles et perpendiculaires aux pivots, de l'anneau et des aubes.Arrangement of internal ends of a stage of variable-pitch blades according to any one of claims 1 or 2, characterized in that it comprises thrust washers (19) engaged around the pivots (15) and retained between planar surfaces (20, 21), mutually parallel and perpendicular to the pivots, of the ring and the vanes. Agencement d'extrémités internes d'un étage d'aubes à calage variable selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les douilles (13) finissent par une tête polygonale de réglage (22).Arrangement of internal ends of a stage of variable-pitch vanes according to any one of Claims 1 to 3, characterized in that the sockets (13) end in a polygonal adjustment head (22). Agencement d'extrémités internes d'un étage d'aubes à calage variable selon la revendication 4, caractérisé en ce que des languettes (25) d'un rail circulaire (24) serti dans l'anneau de liaison (10) touchent les têtes polygonales (22).Arrangement of internal ends of a stage of variable-pitch vanes according to claim 4, characterized in that the tongues (25) of a rail circular (24) crimped in the connecting ring (10) touch the polygonal heads (22). Agencement d'extrémités internes d'un étage d'aubes à calage variable selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les pièces de frein sont évidées et en matière composite à base de carbone.Arrangement of internal ends of a stage of variable-pitch vanes according to any one of Claims 1 to 5, characterized in that the brake parts are hollowed out and made of carbon-based composite material.
EP19960402808 1995-12-20 1996-12-19 Arrangement of the root ends of a variable angle row of blades Expired - Lifetime EP0780545B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9515122 1995-12-20
FR9515122A FR2742800B1 (en) 1995-12-20 1995-12-20 ARRANGEMENT OF INTERNAL ENDS OF A VARIABLE SETTING BLADE STAGE

Publications (2)

Publication Number Publication Date
EP0780545A1 true EP0780545A1 (en) 1997-06-25
EP0780545B1 EP0780545B1 (en) 1999-05-06

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EP19960402808 Expired - Lifetime EP0780545B1 (en) 1995-12-20 1996-12-19 Arrangement of the root ends of a variable angle row of blades

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DE (1) DE69602342T2 (en)
FR (1) FR2742800B1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998017896A1 (en) * 1996-10-22 1998-04-30 Siemens Westinghouse Power Corporation Vane segment support and alignment device
EP1205638A2 (en) * 2000-11-09 2002-05-15 General Electric Company Inlet guide vane and shroud support contact
FR2846384A1 (en) * 2002-10-23 2004-04-30 Gen Electric IMPROVED DESIGN OF A TRIBOLOGICAL POINT OF VIEW FOR FIXED BLADES WITH VARIABLE SETTING
JP2005299667A (en) * 2004-04-14 2005-10-27 General Electric Co <Ge> Gas turbine engine assembling method and its device
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
FR2920492A1 (en) * 2007-08-30 2009-03-06 Snecma Sa VARIABLE SHAFT OF AUBES FOR A TURBOMACHINE
EP2149678A1 (en) 2008-07-28 2010-02-03 Ansaldo Energia S.P.A. Connection assembly for connecting a blade to a support ring
FR2966530A1 (en) * 2010-10-21 2012-04-27 Snecma Variable-pitch vane stage for high-pressure compressor of turbomachine e.g. turbojet, of aircraft, has inner ring including bearing with smooth outer cylindrical surface, and another bearing with external threading
US20150016984A1 (en) * 2013-06-20 2015-01-15 MTU Aero Engines AG Guide vane arragement and method for mounting a guide vane

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2556410A1 (en) 1983-12-07 1985-06-14 Snecma DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR
GB2159887A (en) * 1984-06-04 1985-12-11 Gen Electric A stator vane mounting arrangement
EP0298894A1 (en) * 1987-07-08 1989-01-11 United Technologies Corporation Split shroud compressor
FR2644525A1 (en) 1989-03-15 1990-09-21 Snecma STATOR VARIABLE STATOR AUBER RETENTION SYSTEM

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2556410A1 (en) 1983-12-07 1985-06-14 Snecma DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR
GB2159887A (en) * 1984-06-04 1985-12-11 Gen Electric A stator vane mounting arrangement
EP0298894A1 (en) * 1987-07-08 1989-01-11 United Technologies Corporation Split shroud compressor
FR2644525A1 (en) 1989-03-15 1990-09-21 Snecma STATOR VARIABLE STATOR AUBER RETENTION SYSTEM

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5921749A (en) * 1996-10-22 1999-07-13 Siemens Westinghouse Power Corporation Vane segment support and alignment device
GB2333808A (en) * 1996-10-22 1999-08-04 Westinghouse Electric Corp Vane segment support and alignment device
GB2333808B (en) * 1996-10-22 2000-10-11 Westinghouse Electric Corp Vane segment support and alignment device
WO1998017896A1 (en) * 1996-10-22 1998-04-30 Siemens Westinghouse Power Corporation Vane segment support and alignment device
EP1205638A2 (en) * 2000-11-09 2002-05-15 General Electric Company Inlet guide vane and shroud support contact
EP1205638A3 (en) * 2000-11-09 2004-01-07 General Electric Company Inlet guide vane and shroud support contact
FR2846384A1 (en) * 2002-10-23 2004-04-30 Gen Electric IMPROVED DESIGN OF A TRIBOLOGICAL POINT OF VIEW FOR FIXED BLADES WITH VARIABLE SETTING
EP1586744A3 (en) * 2004-04-14 2008-04-23 General Electric Company Variable vane assembly for a gas turbine engine
JP2005299667A (en) * 2004-04-14 2005-10-27 General Electric Co <Ge> Gas turbine engine assembling method and its device
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
FR2920492A1 (en) * 2007-08-30 2009-03-06 Snecma Sa VARIABLE SHAFT OF AUBES FOR A TURBOMACHINE
US8162597B2 (en) 2007-08-30 2012-04-24 Snecma Stage of variable-pitch vanes for a turbomachine
EP2149678A1 (en) 2008-07-28 2010-02-03 Ansaldo Energia S.P.A. Connection assembly for connecting a blade to a support ring
FR2966530A1 (en) * 2010-10-21 2012-04-27 Snecma Variable-pitch vane stage for high-pressure compressor of turbomachine e.g. turbojet, of aircraft, has inner ring including bearing with smooth outer cylindrical surface, and another bearing with external threading
US20150016984A1 (en) * 2013-06-20 2015-01-15 MTU Aero Engines AG Guide vane arragement and method for mounting a guide vane
US9617861B2 (en) * 2013-06-20 2017-04-11 MTU Aero Engines AG Guide vane arrangement and method for mounting a guide vane

Also Published As

Publication number Publication date
DE69602342T2 (en) 1999-11-04
FR2742800B1 (en) 1998-01-16
DE69602342D1 (en) 1999-06-10
FR2742800A1 (en) 1997-06-27
EP0780545B1 (en) 1999-05-06

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