EP0192512A1 - Abradable turbine rings and turbines so obtained - Google Patents

Abradable turbine rings and turbines so obtained Download PDF

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Publication number
EP0192512A1
EP0192512A1 EP86400106A EP86400106A EP0192512A1 EP 0192512 A1 EP0192512 A1 EP 0192512A1 EP 86400106 A EP86400106 A EP 86400106A EP 86400106 A EP86400106 A EP 86400106A EP 0192512 A1 EP0192512 A1 EP 0192512A1
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EP
European Patent Office
Prior art keywords
abradable
ring
rings
carbon
refractory material
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Granted
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EP86400106A
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German (de)
French (fr)
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EP0192512B1 (en
Inventor
Georges Habarou
Jacques Etienne
Jean-Claude Clebant
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Societe Europeenne de Propulsion SEP SA
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Europeenne De Propulsion (sep) SA Ste
Societe Europeenne de Propulsion SEP SA
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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material

Definitions

  • the present invention relates to abradable turbine rings, their preparation process and the turbines obtained.
  • the object of the present invention is to propose an acceptable solution to this problem; this solution involves the use of a specific material and a particular structure of the ring.
  • the particular structure of the abradable ring according to the invention, said ring being mounted inside the metal structure of the turbine, is characterized in that it consists of at least one "open ring" clamped against said metallic structure by at least one spring.
  • open ring is meant either a ring forming almost the entire inner periphery of the metal structure but comprising a cut between the faces of which a spring is inserted or portions of rings between the faces of which a spring is inserted.
  • the facing faces obtained by the cut or cuts of the open ring can have the form of baffles so as to improve the seal at these cut.
  • the mentioned spring can be any means (spring operating in tension, spring operating in compression, jack), allowing by the application of a suitable force at the level of the cut (s) to apply 1 "open ring" against the metallic structure of the turbine or against a metallic or insulating structure itself (ceramic) which can be adapted to said metallic structure of the turbine.
  • the specific material used is an abradable material, obtained by gaseous deposition of a refractory material such as silicon carbide and alumina, within a carbon fibrous structure and then elimination of said carbon fibrous structure.
  • the preferred material consists of silicon carbide, has a porosity of 15 to 20% and is formed of small hollow tubes all having the same direction substantially that of the radius of one "open ring”.
  • the fibrous carbon structure in which the refractory material is deposited may be a disordered structure (felt) or a more or less ordered structure in which a greater or lesser proportion of the fibers will be oriented in at least one preferred direction. This orientation could for example be unidirectional and be obtained by combing or equivalent means.
  • the fibrous structure may be more or less densified by deposition, as known, on or between the carbon fibers. Thanks to this possibility of orientation of the carbon fibers, and thanks to the possibility of densification of the carbon fiber structure, the method according to the invention makes it possible to obtain a whole series of new materials whose properties can be controlled in order to adapt them to the intended uses.
  • the deposition, in the gas phase, of the refractory material in the structure based on carbon fibers can be advantageously carried out while said structure has been shaped so as to directly obtain a product in its final form, it that is, ready to be assembled or used.
  • the carbon contained in the complex material obtained (carbon in the form of fibers and possibly densification carbon) is eliminated by any known means, in particular by oxidation. This implies that the deposited refractory material resists well the means used to remove the carbon.
  • Products are thus obtained, the essential characteristic of which is that they are in the form of an assembly of small tubes of refractory material.
  • Such a material has been produced using, according to a nonlimiting example, a structure formed from oriented carbon fibers; this structure will for example have a weight of approximately 330 g / m 2 , a fiber content of approximately 9%, and a fiber diameter of 7 to 10 micrometers.
  • Silicon carbide will be deposited in this material, according to the vapor deposition technique, and the carbon fibers contained in the material obtained will be eliminated by any known means, for example by dissolution.
  • said material is particularly designated for making turbine rings using the particular structure of the ring as defined above, the small hollow tubes of silicon carbon being oriented in a substantially perpendicular to the abradable surface.
  • Figure 1 is a schematic representation in section perpendicular to its axis of a turbine ring of abradable material mounted, according to the invention, in a metal ring.
  • FIG. 2 shows, in axial section, an assembly of the abradable ring on the metal ring with partial interposition (Figure 2a) or total ( Figure 2b) of a metal insulator.
  • FIG. 1 there is shown in 1 the closed metal ring which constitutes the structure of the turbine and in 2 the ring of abradable material according to the invention.
  • This ring of abradable material is open 3; the two faces of this opening are compressed by a spring 4 working in compression, said spring being chosen so as to exert on said faces a sufficient force to permanently apply the ring of abradable material on the metal ring.
  • the spring 4 may consist of an air cylinder or a hydraulic cylinder or, preferably, of a leaf spring, either metallic, ceramic, or mixed.

Abstract

La présente invention concerne des anneaux abradables pour turbines caractérisés en ce qu'ils sont constitués d'un matériau réfractaire abradable et sont formés par au moins un anneau ouvert (2) maintenu serré contre une structure f?e métallique (1) à l'aide d'au moins un ressort (4). Les matériaux réfractaires utilisables pour la réalisation desdits anneaux sont obtenus par destruction du carbone dans un composé formé par le dépôt en phase gazeuse d'un matériau réfractaire au sein d'une structure fibreuse de carbone.The present invention relates to abradable rings for turbines, characterized in that they consist of an abradable refractory material and are formed by at least one open ring (2) held tight against a metallic structure (1) at the using at least one spring (4). The refractory materials which can be used for the production of said rings are obtained by destruction of the carbon in a compound formed by the deposition in the gas phase of a refractory material within a fibrous carbon structure.

Description

La présente invention concerne des anneaux de turbine abradables, leur procédé de préparation et les turbines obtenues.The present invention relates to abradable turbine rings, their preparation process and the turbines obtained.

Le rôle d'un anneau de turbine est d'assurer, au droit de la turbine, la frontière de la veine gazeuse en limitant au mieux le passage direct des gaz. Le rendement de la turbine est donc lié aux caractéristiques de cet anneau dont dépend le jeu en bout d'aubes. Pour pouvoir minimiser ce jeu autant que possible, l'anneau doit avoir deux propriétés :

  • - être constitué d'un matériau abradable,
  • - être réglable de façon à pouvoir prévoir une correction active du diamètre de l'anneau en fonction de la configuration instantanée du moteur.
The role of a turbine ring is to ensure, at the right of the turbine, the border of the gas stream by best limiting the direct passage of gases. The efficiency of the turbine is therefore linked to the characteristics of this ring on which the clearance at the tip of the blades depends. To be able to minimize this play as much as possible, the ring must have two properties:
  • - be made of an abradable material,
  • - be adjustable so as to be able to provide for an active correction of the diameter of the ring as a function of the instantaneous configuration of the motor.

Le but de la présente invention est de proposer une solution acceptable à ce problème ; cette solution implique l'emploi d'un matériau spécifique et une structure particulière de l'anneau.The object of the present invention is to propose an acceptable solution to this problem; this solution involves the use of a specific material and a particular structure of the ring.

La structure particulière de l'anneau abradable selon l'invention, ledit anneau étant monté à l'intérieur de la structure métallique de la turbine, est caractérisée en ce qu'elle est constituée d'au moins un "anneau ouvert" serré contre ladite structure métallique par au moins un ressort.The particular structure of the abradable ring according to the invention, said ring being mounted inside the metal structure of the turbine, is characterized in that it consists of at least one "open ring" clamped against said metallic structure by at least one spring.

Par "anneau ouvert", on entend soit un anneau faisant la quasi totalité du pourtour intérieur de la structure métallique mais comportant une coupure entre les faces de laquelle on insère un ressort soit des portions d'anneaux entre les faces desquelles on insère un ressort.By "open ring" is meant either a ring forming almost the entire inner periphery of the metal structure but comprising a cut between the faces of which a spring is inserted or portions of rings between the faces of which a spring is inserted.

Il est clair que les faces en regard obtenues par le ou les coupures de l'anneau ouvert peuvent avoir la forme de chicanes de façon à améliorer l'étanchéité au niveau de ces coupures.It is clear that the facing faces obtained by the cut or cuts of the open ring can have the form of baffles so as to improve the seal at these cut.

Le ressort mentionné peut être tout moyen (ressort opérant en traction, ressort opérant en compression, vérin), permettant par l'application d'une force convenable au niveau de la (ou des) coupure d'appliquer 1"'anneau ouvert" contre la structure métallique de la turbine ou contre une structure elle-même métallique ou isolante (céramique) que l'on pourra adapter a ladite structure métallique de la turbine.The mentioned spring can be any means (spring operating in tension, spring operating in compression, jack), allowing by the application of a suitable force at the level of the cut (s) to apply 1 "open ring" against the metallic structure of the turbine or against a metallic or insulating structure itself (ceramic) which can be adapted to said metallic structure of the turbine.

Le matériau spécifique utilisé est un matériau abradable, obtenu par dépôt en phase gazeuse d'un matériau réfractaire tel que le carbure de silicium et l'alumine, au sein d'une structure fibreuse de carbone puis élimination de ladite structure fibreuse de carbone.The specific material used is an abradable material, obtained by gaseous deposition of a refractory material such as silicon carbide and alumina, within a carbon fibrous structure and then elimination of said carbon fibrous structure.

Le matériau préféré est constitué de carbure de silicium, présente une porosité de 15 à 20 % et est formé de petits tubes creux ayant tous une même direction sensiblement celle du rayon de 1 '"anneau ouvert".The preferred material consists of silicon carbide, has a porosity of 15 to 20% and is formed of small hollow tubes all having the same direction substantially that of the radius of one "open ring".

La structure fibreuse de carbone dans laquelle s'effectuera le dépôt du matériau réfractaire pourra être une structure désordonnée (feutre) ou une structure plus ou moins ordonnée dans laquelle une plus ou moins grande proportion des fibres sera orientée dans au moins une direction préférentielle. Cette orientation pourra être par exemple unidirectionnelle et être obtenue par peignage ou moyens équivalents. La structure fibreuse pourra être plus ou moins densifiée par dépôt, comme connu, sur ou entre les fibres de carbone. Grâce à cette possibilité d'orientation des fibres de carbone, et grâce à la possibilité de densification de la structure en fibres de carbone, le procédé selon l'invention permet d'obtenir toute une série de matériaux nouveaux dont on peut contrôler les propriétés afin de les adapter aux utilisations prévues.The fibrous carbon structure in which the refractory material is deposited may be a disordered structure (felt) or a more or less ordered structure in which a greater or lesser proportion of the fibers will be oriented in at least one preferred direction. This orientation could for example be unidirectional and be obtained by combing or equivalent means. The fibrous structure may be more or less densified by deposition, as known, on or between the carbon fibers. Thanks to this possibility of orientation of the carbon fibers, and thanks to the possibility of densification of the carbon fiber structure, the method according to the invention makes it possible to obtain a whole series of new materials whose properties can be controlled in order to adapt them to the intended uses.

Il faut signaler que le dépôt, en phase gazeuse, du matériau réfractaire dans la structure à base de fibres de carbone peut être avantageusement réalisé alors que ladite structure a été mise en forme de façon à obtenir directement un produit dans sa forme définitive, c'est-à-dire prêt à être assemblé ou utilisé.It should be noted that the deposition, in the gas phase, of the refractory material in the structure based on carbon fibers can be advantageously carried out while said structure has been shaped so as to directly obtain a product in its final form, it that is, ready to be assembled or used.

L'élimination du carbone contenu dans le matériau complexe obtenu (carbone se trouvant sous forme de fibres et éventuellement de carbone de densification) s'effectue par tout moyen connu notam- me-t par oxydation. Ceci implique que le matériau réfractaire déposé résiste bien au moyen utilisé pour éliminer le carbone.The carbon contained in the complex material obtained (carbon in the form of fibers and possibly densification carbon) is eliminated by any known means, in particular by oxidation. This implies that the deposited refractory material resists well the means used to remove the carbon.

On obtient ainsi des produits dont la caractéristique essentielle est qu'ils se présentent sous la forme d'un assemblage de petits tubes en matière réfractaire.Products are thus obtained, the essential characteristic of which is that they are in the form of an assembly of small tubes of refractory material.

Lorsque ces petits tubes sont orientés, il est possible que les surfaces des pièces présentent, par rapport auxdits petits tubes, des orientations spécifiques par exemple les surfaces de frottement seront perpendiculaires à l'axe des tubes, dans ce dernier cas l'usure du matériau s'effectuera par la rupture, en flexion, des parois minces des tubes en matériau réfractaire.When these small tubes are oriented, it is possible that the surfaces of the parts have, relative to said small tubes, specific orientations, for example the friction surfaces will be perpendicular to the axis of the tubes, in the latter case the wear of the material. will be effected by the rupture, in bending, of the thin walls of the refractory material tubes.

On a réalisé un tel matériau en utilisant, selon un exemple non limitatif, une structure formée de fibres de carbone orientées ; cette structure aura par exemple un poids d'environ 330 g/m2, un taux de fibres d'environ 9 %, et un diamètre de fibres de 7 à 10 micromètres.Such a material has been produced using, according to a nonlimiting example, a structure formed from oriented carbon fibers; this structure will for example have a weight of approximately 330 g / m 2 , a fiber content of approximately 9%, and a fiber diameter of 7 to 10 micrometers.

On déposera dans ce matériau, selon la technique de dépôt en phase vapeur, du carbure de silicium et on éliminera par tout moyen connu, par exemple par dissolution, les fibres de carbone contenues dans le matériau obtenu.Silicon carbide will be deposited in this material, according to the vapor deposition technique, and the carbon fibers contained in the material obtained will be eliminated by any known means, for example by dissolution.

Un tel matériau possède les qualités suivantes :

  • - résistance à la corrosion par les produits de combustion à haute température (1 300°C) afin de limiter le débit d'air de refroidissement,
  • - résistance aux cyclages thermiques,
  • - résistance aux chocs thermiques,
  • - résistance à l'érosion (mais abradable quand même) due à l'impact de fines particules,
  • - fabrication reproductible,
  • - usinage et rectifiable en place,
  • - encombrement et poids minimum.
Such a material has the following qualities:
  • - resistance to corrosion by combustion products at high temperature (1300 ° C) in order to limit the flow of cooling air,
  • - resistance to thermal cycling,
  • - resistance to thermal shock,
  • - resistance to erosion (but nonetheless abradable) due to the impact of fine particles,
  • - reproducible manufacturing,
  • - machining and grinding in place,
  • - space and minimum weight.

Et il a été trouvé selon l'invention que ledit matériau était particulièrement désigné pour réaliser des anneaux de turbine en utilisant la structure particulière de l'anneau telle que définie ci-dessus, les petits tubes creux en carbone de silicium étant orientés de façon sensiblement perpendiculaire à la surface abradable.And it has been found according to the invention that said material is particularly designated for making turbine rings using the particular structure of the ring as defined above, the small hollow tubes of silicon carbon being oriented in a substantially perpendicular to the abradable surface.

Les exemples non limitatifs ci-après illustrent des modes de réalisation de la structure particulière de l'anneau selon l'invention ; ces exemples se réfèrent aux figures 1 et 2.The nonlimiting examples below illustrate embodiments of the particular structure of the ring according to the invention; these examples refer to Figures 1 and 2.

La figure 1 est une représentation schématique en coupe perpendiculaire à son axe d'un anneau de turbine en matériau abradable monté, selon l'invention, dans un anneau métallique.Figure 1 is a schematic representation in section perpendicular to its axis of a turbine ring of abradable material mounted, according to the invention, in a metal ring.

La figure 2 représente, en coupe axiale, un montage de l'anneau abradable sur l'anneau métallique avec interposition partielle (figure 2a) ou totale (figure 2b) d'un isolant métallique.2 shows, in axial section, an assembly of the abradable ring on the metal ring with partial interposition (Figure 2a) or total (Figure 2b) of a metal insulator.

Sur la figure 1, on a représenté en 1 l'anneau métallique fermé qui constitue la structure de la turbine et en 2 l'anneau en matériau abradable selon l'invention. Cet anneau en matériau abradable est ouvert 3 ; les deux faces de cette ouverture sont comprimées par un ressort 4 travaillant en compression, ledit ressort étant choisi de façon à exercer sur lesdites faces un effort suffisant pour appliquer en permanence l'anneau en matériau abradable sur l'anneau métallique.In Figure 1, there is shown in 1 the closed metal ring which constitutes the structure of the turbine and in 2 the ring of abradable material according to the invention. This ring of abradable material is open 3; the two faces of this opening are compressed by a spring 4 working in compression, said spring being chosen so as to exert on said faces a sufficient force to permanently apply the ring of abradable material on the metal ring.

Le ressort 4 peut être constitué d'un vérin à air ou d'un vérin hydraulique ou, de préférence, d'un ressort à lames, soit métalliques, soit céramiques, soit mixtes.The spring 4 may consist of an air cylinder or a hydraulic cylinder or, preferably, of a leaf spring, either metallic, ceramic, or mixed.

L'étanchéité au niveau de la coupure 3 de l'anneau abradable sera réalisée sans difficultés majeures par mise en oeuvre de moyens connus.The seal at the cutoff 3 of the abradable ring will be achieved without major difficulties by the use of known means.

Sur les figures 2a et 2b , on a représenté :

  • - en 1 l'anneau métallique fermé qui constitue la structure de la turbine,
  • - en 2, l'anneau abradable ; cet anneau est, comme représenté sur la figure 1, ouvert et comprimé par au moins un ressort,
  • - en 5, un isolant céramique qui peut être soit situé uniquement au droit des extrémités de l'anneau métallique 1 comme dans la figure 2a, soit s'étendre sur la totalité de la surface ouverte de cet anneau métallique comme dans la figure 2b ; dans ce dernier cas cette couche isolante peut contribuer à l'étanchéité radiale du système.
In FIGS. 2a and 2b, there is shown:
  • - in 1 the closed metal ring which constitutes the structure of the turbine,
  • - in 2, the abradable ring; this ring is, as shown in FIG. 1, open and compressed by at least one spring,
  • - In 5, a ceramic insulator which can either be located only in line with the ends of the metal ring 1 as in FIG. 2a, or extend over the entire open surface of this metal ring as in FIG. 2b; in the latter case this insulating layer can contribute to the radial sealing of the system.

Claims (4)

1. Anneaux abradables pour turbines caractérisés en ce qu'ils sont constitués d'un matériau réfractaire abradable et sont formés par au moins un anneau ouvert maintenu serré contre une structure fixe métallique à l'aide d'au moins un ressort.1. Abradable rings for turbines, characterized in that they consist of an abradable refractory material and are formed by at least one open ring held tight against a fixed metallic structure using at least one spring. 2. Anneaux selon la revendication 1, caractérisés en ce que entre ladite structure fixe métallique et l'anneau on intercale un isolant céramique.2. Rings according to claim 1, characterized in that between said fixed metallic structure and the ring is inserted a ceramic insulator. 3. Anneaux selon l'une des revendications 1 et 2, caractérisés en ce que le matériau réfractaire abradable utilisé est le matériau obtenu par destruction du carbone dans un composé formé par le dépôt en phase gazeuse d'un matériau réfractaire au sein d'une structure fibreuse de carbone.3. Rings according to one of claims 1 and 2, characterized in that the abradable refractory material used is the material obtained by destruction of the carbon in a compound formed by the deposition in the gas phase of a refractory material within a carbon fibrous structure. 4. Anneaux selon la revendication 3, caractérisés en ce que ladite structure fibreuse a été orientée de façon unidirectionnelle, la direction desdites fibres étant perpendiculaire à la surface abradable de l'anneau.4. Rings according to claim 3, characterized in that said fibrous structure has been oriented unidirectionally, the direction of said fibers being perpendicular to the abradable surface of the ring.
EP86400106A 1985-01-24 1986-01-21 Abradable turbine rings and turbines so obtained Expired EP0192512B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8500993A FR2576301B1 (en) 1985-01-24 1985-01-24 PROCESS FOR THE PREPARATION OF POROUS REFRACTORY MATERIALS, NOVEL PRODUCTS THUS OBTAINED AND THEIR APPLICATIONS IN THE PREPARATION OF ABRADABLE TURBINE RINGS
FR8500993 1985-01-24

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EP0192512A1 true EP0192512A1 (en) 1986-08-27
EP0192512B1 EP0192512B1 (en) 1989-05-10

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EP86400106A Expired EP0192512B1 (en) 1985-01-24 1986-01-21 Abradable turbine rings and turbines so obtained

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US (1) US4669954A (en)
EP (1) EP0192512B1 (en)
JP (1) JPS61171805A (en)
CA (1) CA1264299A (en)
DE (1) DE3663279D1 (en)
FR (1) FR2576301B1 (en)

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US4307993A (en) * 1980-02-25 1981-12-29 Avco Corporation Air-cooled cylinder with piston ring labyrinth
US4488920A (en) * 1982-05-18 1984-12-18 Williams International Corporation Process of making a ceramic heat exchanger element
GB2139293A (en) * 1983-05-06 1984-11-07 Mtu Muenchen Gmbh Abradable coating for a turbo compressor stutor/rotor assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
GB2225388B (en) * 1988-10-01 1992-08-19 Rolls Royce Plc Improvements in tip clearance setting in gas turbine engines
WO2014207054A1 (en) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine

Also Published As

Publication number Publication date
FR2576301A1 (en) 1986-07-25
FR2576301B1 (en) 1992-03-13
DE3663279D1 (en) 1989-06-15
US4669954A (en) 1987-06-02
CA1264299A (en) 1990-01-09
JPS61171805A (en) 1986-08-02
EP0192512B1 (en) 1989-05-10

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