FR3001258A1 - Air/oil sealing assembly for high pressure environment of gas turbine of e.g. turbojet engine, of aircraft, has support bush formed to block sealing ring in rotation and partly in translation when sealing ring is positioned on support bush - Google Patents
Air/oil sealing assembly for high pressure environment of gas turbine of e.g. turbojet engine, of aircraft, has support bush formed to block sealing ring in rotation and partly in translation when sealing ring is positioned on support bush Download PDFInfo
- Publication number
- FR3001258A1 FR3001258A1 FR1350595A FR1350595A FR3001258A1 FR 3001258 A1 FR3001258 A1 FR 3001258A1 FR 1350595 A FR1350595 A FR 1350595A FR 1350595 A FR1350595 A FR 1350595A FR 3001258 A1 FR3001258 A1 FR 3001258A1
- Authority
- FR
- France
- Prior art keywords
- ring
- sealing
- sealing ring
- wipers
- support bush
- 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
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 55
- 238000012360 testing method Methods 0.000 claims abstract description 11
- 230000000295 complement effect Effects 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims abstract 2
- 230000000903 blocking effect Effects 0.000 abstract 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
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- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
Abstract
Description
STRUCTURE D'ANNEAU D'ÉTANCHÉITÉ AIR/HUILE POUR ENVIRONNEMENT HAUTE PRESSION D'UNE TURBINE À GAZ DOMAINE TECHNIQUE GÉNÉRAL ET ART ANTÉRIEUR La présente invention est relative à un anneau d'étanchéité 5 air/huile pour environnement haute pression d'une turbine à gaz. L'anneau d'étanchéité proposé par l'invention trouve en particulier avantageusement application dans le cas d'une turbine à gaz de turbomachine d'aéronef. Classiquement, une étanchéité air/huile dans un tel environnement 10 est obtenue au moyen d'un mouvement d'air généré par passages successifs dans des cavités appelées « léchettes » qui, selon leur configuration (nombre, inclinaisons), influent sur la pression d'air générée et donc sur l'étanchéité. Des pièces d'anneau d'étanchéité à léchettes inclinées du type de 15 celle illustrée sur la figure 1 sont déjà connues. Classiquement, une telle pièce est monobloc. Elle comporte une bague 1, d'un bloc avec une pluralité de léchettes 2, qui sont des crêtes annulaires, s'étendant selon des cercles parallèles entre eux. En l'occurrence sur la figure 1, ces léchettes 2 sont au nombre de trois et 20 sont toutes inclinées avec une certaine inclinaison par rapport à l'axe de la bague 1. À une extrémité axiale, la bague 1 présente un fond annulaire 3, qui s'étend à partir du bord de ladite bague 1 et qui comporte une pluralité de pattes radiales 4 munies d'orifices 5, qui permettent la 25 fixation de cet anneau d'étanchéité en position. De telles pièces d'étanchéité sont toutefois onéreuses. Le coût de réalisation qui en résulte lors d'essais de différentes configurations d'étanchéité sur un turbomoteur est de ce fait particulièrement important, puisqu'il est alors nécessaire de disposer de 30 tout un jeu de pièces spécifiques pour chaque essai.FIELD OF THE INVENTION The present invention relates to an air / oil seal ring for a high pressure environment of a turbine. gas. The sealing ring proposed by the invention is particularly advantageously used in the case of an aircraft turbomachine gas turbine engine. Conventionally, an air / oil seal in such an environment 10 is obtained by means of a movement of air generated by successive passages in cavities called "wipers" which, according to their configuration (number, inclinations), affect the pressure of air generated and therefore on the seal. Inclined wiping ring pieces of the type illustrated in FIG. 1 are already known. Classically, such a piece is monobloc. It comprises a ring 1, a block with a plurality of wipers 2, which are annular ridges, extending in circles parallel to each other. In this case in FIG. 1, these wipers 2 are three in number and all of them are inclined with a certain inclination with respect to the axis of the ring 1. At one axial end, the ring 1 has an annular bottom 3 , which extends from the edge of said ring 1 and which has a plurality of radial tabs 4 provided with orifices 5, which allow the fixing of this sealing ring in position. Such sealing pieces are however expensive. The resulting cost of implementation when testing different sealing configurations on a turbine engine is therefore particularly important, since it is then necessary to have a whole set of specific parts for each test.
PRÉSENTATION GÉNÉRALE DE L'INVENTION Un but de l'invention est résoudre les problématiques des pièces d'étanchéité de l'art antérieur. Notamment, un but de l'invention est de résoudre les 5 problématiques de coûts d'essai précitées. Un autre but encore de l'invention est de proposer une structure d'étanchéité permettant une grande flexibilité d'adaptation tout en étant d'un montage et d'un démontage aisés. Il est en particulier proposé un ensemble d'étanchéité air/huile à 10 léchettes pour environnement haute pression d'une turbine à gaz, qui comporte une bague support et au moins un anneau d'étanchéité à léchettes qui constitue une pièce distincte de ladite bague et qui est apte à être rapporté sur celle-ci, ladite bague étant conformée pour bloquer en rotation et, au moins en partie en translation, ledit anneau lorsque celui- 15 ci est mis en place sur ladite bague. De cette façon, il est possible, notamment dans le cadre d'essais d'étanchéité sur une turbine, d'utiliser plusieurs anneaux d'étanchéité de configurations de léchettes différentes. Il est ainsi également proposé un procédé d'essai d'étanchéité au 20 niveau d'un interface air/huile d'un environnement haute pression d'une turbine à gaz, dans lequel on met en place la bague de l'ensemble d'étanchéité au niveau de la zone de la turbine correspondant à cette interface et on met en oeuvre des essais d'étanchéité en rapportant sur ladite bague plusieurs anneaux d'étanchéité de la structure 25 correspondant à différentes configurations de léchettes. PRÉSENTATION DES FIGURES D'autres caractéristiques et avantages de l'invention ressortiront encore de la description qui suit, laquelle est purement illustrative et non 30 limitative, et doit être lue en regard des figures annexées sur lesquelles : - la figure 1 illustre un anneau d'étanchéité conforme à un état de la technique connu ; - la figure 2 illustre en perspective une structure d'ensemble d'étanchéité conforme à un mode de réalisation de l'invention ; - la figure 3 illustre le montage de l'anneau d'étanchéité de la figure 2 sur la bague ; - la figure 4 illustre une vue arrière de l'anneau d'étanchéité et de la bague après montage ; - les figure 5a et 5b illustrent deux exemples de configurations de léchettes d'étanchéité possibles avec un ensemble d'étanchéité conforme à un mode de réalisation de l'invention ; - les figures 6a et 6b illustrent en vue en coupe radiale les anneaux d'étanchéité correspondant aux configurations de léchettes illustrées sur les figures 5a et 5b. EXEMPLES DE RÉALISATION La structure illustrée sur les figures 2 et 4 comporte une bague 15 support 10 et un anneau d'étanchéité 11 qui est une pièce distincte de la bague support 10. La bague support 10 comporte sur sa périphérie annulaire externe une succession d'encoches 12a et de zones en saillie externe 12b destinées à coopérer avec des encoches 13a et des zones en saillie 13b 20 complémentaires de la périphérie annulaire intérieure de l'anneau d'étanchéité 11 pour bloquer en rotation ledit anneau 11 sur ladite bague 10. Ladite bague 10 comporte en outre à son extrémité axiale destinée à se trouver du côté huile (côté H sur la figure 3) un épaulement 14 en 25 saillie annulaire à la périphérie externe de ladite bague 10. Ledit épaulement 14 forme butée annulaire sur lequel l'anneau d'étanchéité 11 vient se bloquer. À son extrémité axiale opposée (côté air sous pression - A sur la figure 3), la bague 10 est pourvue d'au moins une gorge 15 d'accueil 30 d'un anneau d'arrêt 16 que l'on positionne dans ladite gorge 15 pour, avec la butée que constitue l'épaulement 14, bloquer axialement l'anneau d'étanchéité 11 sur la bague 10.GENERAL PRESENTATION OF THE INVENTION An object of the invention is to solve the problems of sealing parts of the prior art. In particular, it is an object of the invention to solve the above-mentioned test cost issues. Yet another object of the invention is to provide a sealing structure allowing great flexibility of adaptation while being easy assembly and disassembly. In particular, there is provided an air / oil seal assembly 10 for wiping high pressure environment of a gas turbine, which comprises a support ring and at least one wiper ring which constitutes a separate piece of said ring. and which is adapted to be attached thereto, said ring being shaped to lock in rotation and, at least partly in translation, said ring when it is placed on said ring. In this way, it is possible, particularly in the context of tightness tests on a turbine, to use several sealing rings of different wiper configurations. It is thus also proposed a leak test method at an air / oil interface of a high pressure environment of a gas turbine, in which is set up the ring of the assembly of sealing at the area of the turbine corresponding to this interface and is carried out sealing tests by reporting on said ring several sealing rings of the structure 25 corresponding to different wiper configurations. PRESENTATION OF THE FIGURES Other features and advantages of the invention will become apparent from the description which follows, which is purely illustrative and nonlimiting, and should be read with reference to the appended figures in which: FIG. sealing according to a known state of the art; - Figure 2 illustrates in perspective a sealing assembly structure according to an embodiment of the invention; - Figure 3 illustrates the mounting of the sealing ring of Figure 2 on the ring; - Figure 4 illustrates a rear view of the sealing ring and the ring after assembly; FIGS. 5a and 5b illustrate two examples of possible sealing lip configurations with a sealing assembly according to one embodiment of the invention; - Figures 6a and 6b illustrate in radial sectional view the sealing rings corresponding to wiper configurations shown in Figures 5a and 5b. EXAMPLES OF EMBODIMENT The structure illustrated in FIGS. 2 and 4 comprises a support ring 10 and a sealing ring 11 which is a separate piece from the support ring 10. The support ring 10 comprises on its outer annular periphery a succession of notches 12a and outer projecting regions 12b for cooperating with notches 13a and complementary projecting zones 13b of the inner annular periphery of the sealing ring 11 to rotate said ring 11 on said ring 10. Said ring 10 further comprises at its axial end intended to be on the oil side (H side in Figure 3) a shoulder 14 annular projecting at the outer periphery of said ring 10. Said shoulder 14 annular stop shape on which the sealing ring 11 comes hang. At its opposite axial end (pressurized air side - A in FIG. 3), the ring 10 is provided with at least one receiving groove 30 of a stop ring 16 which is positioned in said groove 15, with the stop constituted by the shoulder 14, axially locking the sealing ring 11 on the ring 10.
L'anneau d'arrêt 16 est par exemple un anneau ouvert ayant un diamètre intérieur qui correspond au diamètre intérieur de la gorge 15. Des pattes d'extrémité 16a permettent de l'ouvrir élastiquement pour le refermer sur la gorge 15.The stop ring 16 is for example an open ring having an inside diameter which corresponds to the inside diameter of the groove 15. End tabs 16a make it possible to open it elastically so as to close it on the groove 15.
L'assemblage de l'anneau d'étanchéité 11 sur la bague 10 se fait de la façon suivante. La bague 10 est préalablement montée au niveau de l'interface air/huile au niveau de laquelle on souhaite assurer une étanchéité et au niveau de laquelle on souhaite par exemple tester différentes 10 configurations de léchettes. Par exemple, ladite bague 10 est montée par serrage et freitage sur une pièce réceptrice P du côté du palier de la turbine, en étant bloquée sur celle-ci entre d'une part un épaulement E côté air sous pression (coté A) et d'autre part une pièce de fixation F elle-même 15 rapportée sur ladite pièce P du côté de l'enceinte d'huile (côté H). L'anneau d'étanchéité 11 est rapporté sur ladite bague 10 en faisant glisser ces zones en saillie 13b sur les encoches 12a de ladite bague 10, ainsi que ses encoches 13a sur les zones en saillie 12b. L'anneau d'arrêt 16 est ensuite rapporté sur la gorge 15. 20 Le sens de montage des différentes pièces est celui illustré sur la figure 2. Le démontage se fait également aisément en sens inverse en désengageant l'anneau d'arrêt 16 par rapport à la gorge 15 et en faisant coulisser l'anneau d'étanchéité 11 par rapport à la bague 10. 25 Comme on l'aura compris, la structure d'étanchéité proposée permet, à partir d'une même bague support 10, d'utiliser différentes configurations de léchettes et ainsi par exemple de tester, sur une zone d'étanchéité air/huile dans un environnement haute pression différentes configurations de léchettes possibles. 30 C'est ce qu'illustrent les figures 5a-5b et 6a-6b. Dans le cas illustré sur la figure 5a, l'anneau d'étanchéité 11 comporte trois léchettes annulaires 11a inclinées. En coupe radiale (figure 6a) ces léchettes 11a se présentent sous forme de trois dents parallèles, inclinées par rapport à l'axe Ax de l'anneau 11.The assembly of the sealing ring 11 on the ring 10 is as follows. The ring 10 is previously mounted at the air / oil interface at which it is desired to provide a seal and at which it is desired, for example, to test different configurations of wipers. For example, said ring 10 is mounted by clamping and bending on a receiving member P on the bearing side of the turbine, being locked thereon between a shoulder E on the air side under pressure (A side) and d on the other hand a fixing piece F itself attached to said piece P on the side of the oil chamber (H side). The sealing ring 11 is attached to said ring 10 by sliding these projecting areas 13b on the notches 12a of said ring 10, and its notches 13a on the projecting areas 12b. The stop ring 16 is then attached to the groove 15. The assembly direction of the different parts is that illustrated in FIG. 2. Disassembly is also easily done in the opposite direction by disengaging the stop ring 16. the groove 15 and sliding the sealing ring 11 relative to the ring 10. As will be understood, the proposed sealing structure allows, from the same support ring 10, to use different configurations wipers and thus for example to test, on an air / oil sealing zone in a high pressure environment different configurations of wipers possible. This is illustrated in Figures 5a-5b and 6a-6b. In the case illustrated in Figure 5a, the sealing ring 11 comprises three annular wipers 11a inclined. In radial section (FIG. 6a) these wipers 11a are in the form of three parallel teeth, inclined with respect to the axis Ax of the ring 11.
Dans le cas illustré sur la figure 5b, l'anneau d'étanchéité 11 comporte quatre léchettes annulaires 11b droites. En coupe radiale (figure 6b) ces léchettes 11b se présentent sous forme de quatre dents parallèles, s'étendant perpendiculairement à l'axe Ax de l'anneau 11.In the case illustrated in Figure 5b, the sealing ring 11 comprises four annular wipers 11b straight. In radial section (FIG. 6b) these wipers 11b are in the form of four parallel teeth, extending perpendicularly to the axis Ax of the ring 11.
Ainsi, il est possible de tester à moindre coût différentes configurations d'étanchéité possibles.Thus, it is possible to test cheaply different possible sealing configurations.
Claims (10)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1350595A FR3001258B1 (en) | 2013-01-24 | 2013-01-24 | AIR / OIL SEAL RING STRUCTURE FOR A HIGH-PRESSURE ENVIRONMENT OF A GAS TURBINE |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1350595A FR3001258B1 (en) | 2013-01-24 | 2013-01-24 | AIR / OIL SEAL RING STRUCTURE FOR A HIGH-PRESSURE ENVIRONMENT OF A GAS TURBINE |
Publications (2)
Publication Number | Publication Date |
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FR3001258A1 true FR3001258A1 (en) | 2014-07-25 |
FR3001258B1 FR3001258B1 (en) | 2016-09-02 |
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FR1350595A Active FR3001258B1 (en) | 2013-01-24 | 2013-01-24 | AIR / OIL SEAL RING STRUCTURE FOR A HIGH-PRESSURE ENVIRONMENT OF A GAS TURBINE |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2092242A (en) * | 1981-01-31 | 1982-08-11 | Rolls Royce | Non-contacting gas seal |
US5199172A (en) * | 1992-04-02 | 1993-04-06 | John Crane Inc. | Method of manufacturing a pinless retainer for a primary ring |
EP1130294A2 (en) * | 2000-02-29 | 2001-09-05 | General Electric Company | Surface following brush seal |
WO2006005950A2 (en) * | 2004-07-12 | 2006-01-19 | Aes Engineering Limited | Seal |
-
2013
- 2013-01-24 FR FR1350595A patent/FR3001258B1/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2092242A (en) * | 1981-01-31 | 1982-08-11 | Rolls Royce | Non-contacting gas seal |
US5199172A (en) * | 1992-04-02 | 1993-04-06 | John Crane Inc. | Method of manufacturing a pinless retainer for a primary ring |
EP1130294A2 (en) * | 2000-02-29 | 2001-09-05 | General Electric Company | Surface following brush seal |
WO2006005950A2 (en) * | 2004-07-12 | 2006-01-19 | Aes Engineering Limited | Seal |
Also Published As
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FR3001258B1 (en) | 2016-09-02 |
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