EP0571244A1 - Sealing structure for a pivoting blade of a turbomachine - Google Patents

Sealing structure for a pivoting blade of a turbomachine Download PDF

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Publication number
EP0571244A1
EP0571244A1 EP93401205A EP93401205A EP0571244A1 EP 0571244 A1 EP0571244 A1 EP 0571244A1 EP 93401205 A EP93401205 A EP 93401205A EP 93401205 A EP93401205 A EP 93401205A EP 0571244 A1 EP0571244 A1 EP 0571244A1
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EP
European Patent Office
Prior art keywords
ring
pivot
sleeve
groove
turbomachine
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
EP93401205A
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German (de)
French (fr)
Other versions
EP0571244B1 (en
Inventor
Jean-Louis Charbonnel
Jacky Serge Naudet
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 EP0571244A1 publication Critical patent/EP0571244A1/en
Application granted granted Critical
Publication of EP0571244B1 publication Critical patent/EP0571244B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially 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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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

Definitions

  • the invention relates to a sealing structure for a pivoting blade of a turbomachine.
  • variable pitch vanes that is to say which rotate so as to more or less straighten the gas streams which pass through them. It is thus possible to maintain a satisfactory yield whatever the speed of the machine.
  • Such blades are often encountered in particular in the first stages of a high pressure compressor located downstream of a lower pressure compressor.
  • French Patent No. 2,452,591 describes a device with several seals including a split elastic seal disposed in a groove in the pivot. The insertion of such a split ring in the bearing can however be difficult, and this is why the invention proposes with the invention a structure which allows this insertion very simply and even automatically.
  • the invention therefore relates to a structure comprising a turbomachine blade pivoting around a pivot engaged in a bearing, a split elastic ring being disposed in a groove of the pivot and designed so as to rub against the bearing by at least one first portion of the outer face, characterized by a socket engaged around the pivot on one side of the groove, the socket being movable along the pivot between a position where it covers at least a second portion of the outer face and a position where it is remote from the ring, the groove and the ring being designed so that the ring can be pushed into the groove at the location of the second portion.
  • the simplicity of assembly is further accentuated if the two portions are distinct, adjacent and separated by a shoulder from the outer face or if the sleeve has a flare at an end opposite to the ring, the flare being designed to abut against a surface where the landing opens. If these two characteristics are combined, the first position mentioned corresponds to the stop of the end of the sleeve on the shoulder and the second corresponds to the stop of the flare on the surface where the bearing emerges.
  • the slit is advantageously sinuous or in the form of a labyrinth to limit leaks through it.
  • another sleeve can be threaded between the pivot and the bearing, opposite the first sleeve relative to the split ring. The best support for the pivot is then achieved.
  • FIG. 1 therefore represents the turbomachine, essentially composed of a stator 1 surrounding a rotor 2 to delimit a substantially annular vein 3 through which the gases pass.
  • a low-pressure compressor 4 and a high-pressure compressor 5 occupy two different parts of the annular stream 3 and are each composed of stages of rotor blades 6, integral with the latter, and stages of blades of stator 7 and 8, most of which are fixed vanes 7 but some of which, namely the vanes of the first four stages of the high pressure compressor 5, are variable pitch vanes 8 pivoting around a pivot 9 housed in a through bearing the stator wall 1.
  • the pivot 9 is notched with a groove 10 in which there is a split ring 11 and whose slot is designated by 12. It is a slot 12 labyrinth , that is to say that it is not straight but sinuous and here comprises a part in an arc 13 joining two straight parts 14 and 15 for connection to the two axial edges 16 and 17 of the ring 11.
  • a slot 12 labyrinth that is to say that it is not straight but sinuous and here comprises a part in an arc 13 joining two straight parts 14 and 15 for connection to the two axial edges 16 and 17 of the ring 11.
  • the groove 10 is designed so that the material of the ring 11 located in front of the peripheral portions 20 and 21 is entirely contained in the groove 10 when the slot 12 is closed as a result of the contraction of the ring 11.
  • a contraction can be achieved by a sleeve 22 sliding along the pivot 9 and located between the ring 11 and the blade 8: the bush 22 is placed just before the blade 8 is mounted on the stator 1 so that it occupies a position where it abuts against the crest of the ring 11 and covers one of the peripheral portions 21.
  • the cylindrical part 23 is introduced by sliding freely in the bearing 25 of the stator 1 until the flange 24 abuts against the internal surface 26 of the stator 1, where the bearing 25 opens. It is then retained while the depression of the blade 8 and of the pivot 9 continues, until the blade 8 abuts against the flange 24, but the ring 11 is then entirely escaped from the sleeve 22 , which allowed its expansion, so that the crest portion 19 now touches a part of the surface of the bearing 25 and establishes the desired seal.
  • a second sleeve 27 can be threaded into the bearing 25, on the other side of the previous one with respect to the ring 11: this sleeve 27 can also consist of a cylindrical part 28 and a flared part in a flange 29 intended to serve as a stop on the external surface 30 of the stator 1.
  • the pivot 9 is then well supported and can be screwed by conventional fixing systems outside the stator 1.
  • the bushings 22 and 27 are made of self-lubricating material and are used, as usual, to support bearings for the pivot 9.

Abstract

Sealing structure for a blade (8) of a turbomachine pivoting about a spindle (9). A split ring (11) is housed in a groove (10) into which it can be driven and held by a sleeve (22). When the blade is fitted, the sleeve (22) abuts against a wall of the stator (1), slides on the pivot (9) and releases the ring (11) which expands and provides sealing. The invention relates to some turbomachines in which the stator blades have what is known as variable pitch. <IMAGE>

Description

L'invention concerne une structure d'étanchéité pour une aube pivotante de turbomachine.The invention relates to a sealing structure for a pivoting blade of a turbomachine.

De nombreuses turbomachines de moteurs d'avions comprennent maintenant des aubes à calage variable, c'est-à-dire qui pivotent de façon à redresser plus ou moins les courants gazeux qui passent à travers elles. Il est ainsi possible de maintenir un rendement satisfaisant quel que soit le régime de la machine. De telles aubes se rencontrent en particulier souvent dans les premiers étages d'un compresseur à haute pression situé en aval d'un compresseur à plus basse pression.Many aircraft engine turbomachines now include variable pitch vanes, that is to say which rotate so as to more or less straighten the gas streams which pass through them. It is thus possible to maintain a satisfactory yield whatever the speed of the machine. Such blades are often encountered in particular in the first stages of a high pressure compressor located downstream of a lower pressure compressor.

La pression des gaz soumet les pivots de ces aubes à des forces de poussée importantes, qui les usent petit à petit selon une ovalisation de leur section. L'étanchéité de la veine annulaire où les gaz circulent est alors perdue à l'emplacement des pivots, ce qui impose de prévoir des joints d'étanchéité.The pressure of the gases subjects the pivots of these blades to significant thrust forces, which wear them out little by little according to an ovalization of their section. The tightness of the annular vein where the gases circulate is then lost at the location of the pivots, which makes it necessary to provide seals.

Le brevet français n° 2 452 591 décrit un dispositif de plusieurs joints d'étanchéité dont un joint élastique fendu disposé dans une gorge du pivot. L'insertion d'un tel anneau fendu dans le palier peut cependant être difficile, et c'est pourquoi on propose avec l'invention une structure qui permet très simplement et même automatiquement cette insertion.French Patent No. 2,452,591 describes a device with several seals including a split elastic seal disposed in a groove in the pivot. The insertion of such a split ring in the bearing can however be difficult, and this is why the invention proposes with the invention a structure which allows this insertion very simply and even automatically.

L'invention est donc relative à une structure comportant une aube de turbomachine pivotant autour d'un pivot engagé dans un palier, un anneau élastique fendu étant disposé dans une gorge du pivot et conçu de façon à frotter contre le palier par au moins une première portion de la face extérieure, caractérisée par une douille engagée autour du pivot d'un côté de la gorge, la douille étant mobile le long du pivot entre une position où elle recouvre au moins une seconde portion de la face extérieure et une position où elle est éloignée de l'anneau, la gorge et l'anneau étant conçus de façon que l'anneau puisse être enfoncé dans la gorge à l'endroit de la seconde portion.The invention therefore relates to a structure comprising a turbomachine blade pivoting around a pivot engaged in a bearing, a split elastic ring being disposed in a groove of the pivot and designed so as to rub against the bearing by at least one first portion of the outer face, characterized by a socket engaged around the pivot on one side of the groove, the socket being movable along the pivot between a position where it covers at least a second portion of the outer face and a position where it is remote from the ring, the groove and the ring being designed so that the ring can be pushed into the groove at the location of the second portion.

La simplicité du montage est encore accentuée si les deux portions sont distinctes, adjacentes et séparées par un épaulement de la face extérieure ou si la douille présente un évasement à une extrémité opposée à l'anneau, l'évasement étant conçu pour buter contre une surface où le palier débouche. Si ces deux caractéristiques sont réunies, la première position mentionnée correspond à la butée de l'extrémité de la douille sur l'épaulement et la seconde correspond à la butée de l'évasement sur la surface où le palier débouche.The simplicity of assembly is further accentuated if the two portions are distinct, adjacent and separated by a shoulder from the outer face or if the sleeve has a flare at an end opposite to the ring, the flare being designed to abut against a surface where the landing opens. If these two characteristics are combined, the first position mentioned corresponds to the stop of the end of the sleeve on the shoulder and the second corresponds to the stop of the flare on the surface where the bearing emerges.

La fente est avantageusement sinueuse ou en forme de labyrinthe pour limiter les fuites au travers d'elle. Enfin, une autre douille peut être enfilée entre le pivot et le palier, à l'opposé de la première douille par rapport à l'anneau fendu. Le meilleur soutien du pivot est alors réalisé.The slit is advantageously sinuous or in the form of a labyrinth to limit leaks through it. Finally, another sleeve can be threaded between the pivot and the bearing, opposite the first sleeve relative to the split ring. The best support for the pivot is then achieved.

On va maintenant décrire une réalisation de l'invention plus en détail avec les figures suivantes annexées à titre illustratif et non limitatif :

  • la figure 1 représente un fragment de turbomachine,
  • les figures 2 et 3 représentent la structure conforme à l'invention, respectivement avant et après le montage,
  • et la figure 4 représente l'anneau fendu en perspective.
An embodiment of the invention will now be described in more detail with the following figures annexed by way of illustration and not limitation:
  • FIG. 1 represents a fragment of a turbomachine,
  • FIGS. 2 and 3 show the structure according to the invention, respectively before and after assembly,
  • and Figure 4 shows the split ring in perspective.

La figure 1 représente donc la turbomachine, composée essentiellement d'un stator 1 entourant un rotor 2 pour délimiter une veine sensiblement annulaire 3 à travers laquelle passent les gaz. Un compresseur à basse pression 4 et un compresseur à haute pression 5 occupent deux parties différentes de la veine annulaire 3 et sont composés chacun d'étages d'aubes de rotor 6, solidaires de celui-ci, et d'étages d'aubes de stator 7 et 8 dont la plupart sont des aubes fixes 7 mais dont certaines, à savoir les aubes des quatre premiers étages du compresseur à haute pression 5, sont des aubes à calage variable 8 pivotant autour d'un pivot 9 logé dans un palier traversant la paroi du stator 1.FIG. 1 therefore represents the turbomachine, essentially composed of a stator 1 surrounding a rotor 2 to delimit a substantially annular vein 3 through which the gases pass. A low-pressure compressor 4 and a high-pressure compressor 5 occupy two different parts of the annular stream 3 and are each composed of stages of rotor blades 6, integral with the latter, and stages of blades of stator 7 and 8, most of which are fixed vanes 7 but some of which, namely the vanes of the first four stages of the high pressure compressor 5, are variable pitch vanes 8 pivoting around a pivot 9 housed in a through bearing the stator wall 1.

On se reporte maintenant aux figures 2, 3 et 4. Le pivot 9 est entaillé d'une gorge 10 dans laquelle se trouve un anneau 11 fendu et dont la fente est désignée par 12. Il s'agit d'une fente 12 à labyrinthe, c'est-à-dire qu'elle n'est pas droite mais sinueuse et comporte ici une partie en arc de cercle 13 joignant deux parties droites 14 et 15 de raccordement aux deux bords axiaux 16 et 17 de l'anneau 11. On peut distinguer trois portions sur la face extérieure 18 de l'anneau 11 : une portion en crête 19 au centre de l'anneau 11 et deux portions periphériques 20 et 21 qui correspondent à des diamètres plus petits de l'anneau 11. La gorge 10 est conçue pour que la matière de l'anneau 11 située devant les portions périphériques 20 et 21 soit entièrement contenue dans la gorge 10 quand la fente 12 est refermée par suite de la contraction de l'anneau 11. Une telle contraction peut être réalisée par une douille 22 coulissant le long du pivot 9 et située entre l'anneau 11 et l'aube 8 : on dispose la douille 22 juste avant le montage de l'aube 8 sur le stator 1 de façon qu'elle occupe une position où elle bute contre la crête de l'anneau 11 et recouvre une des portions périphériques 21. Quand le montage est effectué, on voit sur la figure 3 que la douille 22 est déplacée, car elle se compose d'une partie cylindrique 23 et d'une collerette 24 constituant un évasement à l'extrémité de la douille 22 opposée à l'anneau 11 : la partie cylindrique 23 est introduite en coulissant librement dans le palier 25 du stator 1 jusqu'à ce que la collerette 24 bute contre la surface interne 26 du stator 1, où le palier 25 débouche. Elle est alors retenue pendant que l'enfoncement de l'aube 8 et du pivot 9 continue, jusqu'à ce que l'aube 8 bute contre la collerette 24, mais l'anneau 11 s'est alors entièrement échappé de la douille 22, ce qui a permis sa dilatation, de sorte que la portion de crête 19 touche maintenant une partie de la surface du palier 25 et établit l'étanchéité souhaitée.Referring now to Figures 2, 3 and 4. The pivot 9 is notched with a groove 10 in which there is a split ring 11 and whose slot is designated by 12. It is a slot 12 labyrinth , that is to say that it is not straight but sinuous and here comprises a part in an arc 13 joining two straight parts 14 and 15 for connection to the two axial edges 16 and 17 of the ring 11. We can distinguish three portions on the outer face 18 of the ring 11: a crest portion 19 in the center of the ring 11 and two peripheral portions 20 and 21 which correspond to smaller diameters of the ring 11. The groove 10 is designed so that the material of the ring 11 located in front of the peripheral portions 20 and 21 is entirely contained in the groove 10 when the slot 12 is closed as a result of the contraction of the ring 11. Such a contraction can be achieved by a sleeve 22 sliding along the pivot 9 and located between the ring 11 and the blade 8: the bush 22 is placed just before the blade 8 is mounted on the stator 1 so that it occupies a position where it abuts against the crest of the ring 11 and covers one of the peripheral portions 21. When the assembly is carried out, it can be seen in FIG. 3 that the sleeve 22 is displaced, because it consists of a cylindrical part 23 and a flange 24 constituting a flare at the end of the sleeve 22 opposite the ring 11: the cylindrical part 23 is introduced by sliding freely in the bearing 25 of the stator 1 until the flange 24 abuts against the internal surface 26 of the stator 1, where the bearing 25 opens. It is then retained while the depression of the blade 8 and of the pivot 9 continues, until the blade 8 abuts against the flange 24, but the ring 11 is then entirely escaped from the sleeve 22 , which allowed its expansion, so that the crest portion 19 now touches a part of the surface of the bearing 25 and establishes the desired seal.

Une seconde douille 27 peut être enfilée dans le palier 25, de l'autre côté de la précédente par rapport à l'anneau 11 : cette douille 27 peut être également constituée d'une partie cylindrique 28 et d'une partie évasée en collerette 29 destinées à servir de butée sur la surface extérieure 30 du stator 1. Le pivot 9 est alors bien soutenu et peut être vissé par des systèmes de fixation classiques à l'extérieur du stator 1.A second sleeve 27 can be threaded into the bearing 25, on the other side of the previous one with respect to the ring 11: this sleeve 27 can also consist of a cylindrical part 28 and a flared part in a flange 29 intended to serve as a stop on the external surface 30 of the stator 1. The pivot 9 is then well supported and can be screwed by conventional fixing systems outside the stator 1.

Les douilles 22 et 27 sont en matière autolubrifiante et servent comme à l'accoutumée de coussinets de support du pivot 9.The bushings 22 and 27 are made of self-lubricating material and are used, as usual, to support bearings for the pivot 9.

Claims (3)

Structure comportant une aube (8) de turbomachine pivotant autour d'un pivot (9) engagé dans un palier (25), un anneau (11) élastique fendu étant disposé dans une gorge (10) du pivot (9) et conçu de façon à frotter contre le palier (25) par au moins une première portion (19) de sa face extérieure, caractérisée par une douille (22) engagée autour du pivot (9) d'un côté de la gorge (10), la douille (22) étant mobile le long du pivot (9) entre une position où elle recouvre au moins une seconde portion (21) de la face extérieure de l'anneau (11) et une position où elle est éloignee de l'anneau (11), la gorge (10) et l'anneau (11) étant conçus de façon que l'anneau (11) puisse être enfoncé dans la gorge (10) à l'endroit de la seconde portion (21).Structure comprising a blade (8) of a turbomachine pivoting around a pivot (9) engaged in a bearing (25), a split elastic ring (11) being disposed in a groove (10) of the pivot (9) and designed so to rub against the bearing (25) by at least a first portion (19) of its outer face, characterized by a sleeve (22) engaged around the pivot (9) on one side of the groove (10), the sleeve ( 22) being movable along the pivot (9) between a position where it covers at least a second portion (21) of the outer face of the ring (11) and a position where it is moved away from the ring (11) , the groove (10) and the ring (11) being designed so that the ring (11) can be pressed into the groove (10) at the location of the second portion (21). Structure selon la revendication 1, caractérisee en ce que les deux portions (19, 21) de la face extérieure (18) de l'anneau (11) sont distinctes, adjacentes et séparées par un épaulement.Structure according to claim 1, characterized in that the two portions (19, 21) of the outer face (18) of the ring (11) are distinct, adjacent and separated by a shoulder. Structure selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que la douille (22) présente un évasement (24) à une extrémité opposée à l'anneau (11), l'évasement (24) étant conçu pour buter contre une surface (26) où le palier (25) débouche.Structure according to any one of claims 1 or 2, characterized in that the sleeve (22) has a flare (24) at an end opposite to the ring (11), the flare (24) being designed to abut against a surface (26) where the bearing (25) opens.
EP93401205A 1992-05-20 1993-05-12 Sealing structure for a pivoting blade of a turbomachine Expired - Lifetime EP0571244B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9206101 1992-05-20
FR9206101A FR2691507B1 (en) 1992-05-20 1992-05-20 WATERPROOFING STRUCTURE FOR A PIVOTING VANE OF A TURBOMACHINE.

Publications (2)

Publication Number Publication Date
EP0571244A1 true EP0571244A1 (en) 1993-11-24
EP0571244B1 EP0571244B1 (en) 1995-07-26

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EP93401205A Expired - Lifetime EP0571244B1 (en) 1992-05-20 1993-05-12 Sealing structure for a pivoting blade of a turbomachine

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US (1) US5324165A (en)
EP (1) EP0571244B1 (en)
JP (1) JP2618181B2 (en)
DE (1) DE69300297T2 (en)
FR (1) FR2691507B1 (en)

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DE69300297T2 (en) 1996-02-01
DE69300297D1 (en) 1995-08-31
JP2618181B2 (en) 1997-06-11
EP0571244B1 (en) 1995-07-26
US5324165A (en) 1994-06-28
FR2691507A1 (en) 1993-11-26
JPH0650103A (en) 1994-02-22
FR2691507B1 (en) 1994-07-08

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