EP0669451B1 - Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires - Google Patents
Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires Download PDFInfo
- Publication number
- EP0669451B1 EP0669451B1 EP95400353A EP95400353A EP0669451B1 EP 0669451 B1 EP0669451 B1 EP 0669451B1 EP 95400353 A EP95400353 A EP 95400353A EP 95400353 A EP95400353 A EP 95400353A EP 0669451 B1 EP0669451 B1 EP 0669451B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- platforms
- envelope
- sealing means
- rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
Definitions
- the invention relates to a gasket. seal arranged in an assembly of blades on a blower disc and intermediate platforms thus forming a rotor.
- a common concept is to produce the platform segments of a block with the vanes. It is exposed in numerous patents and presents the advantage that the platform segments get join vanes halfway through junctions straight lines that are easy to fill with a trim sealing.
- the downside is that the platforms, whose extension is substantially perpendicular to that of the blades, complicate their realization.
- the invention thus applies to constructions where the platforms are made in as loose parts of the blades and extend each between a pair of blades forming a set with each of them, which unfortunately implies that games are important along the blades because of the complexity of the form of these and in particular of their curvature and the need to dismantle the platforms.
- the platforms are held in position between the blades by two ferrules, one located upstream of the rotor, the other downstream.
- the invention may also apply to a rotor whose platforms have a foot which is housed in machined cells in the disc.
- GB-A-1 331 209 which shows seals occupying in the games between blades and platforms work.
- the invention relates to a gasket seal that can be placed in any of these games and who fills them properly. More precisely, it relates to an assembly for rotor, composed blades embedded in the rotor and platforms located between pairs of consecutive blades, sets substantially longitudinal remaining between the vanes and platforms, seals occupying the games and this assembly is characterized in that the fittings are made up of a envelope composed of a face bearing against the sides platforms and a flexible face directed towards the blade surfaces.
- the envelope can equivalent, be composed of one side bearing against the surfaces of the blades and of a flexible directed face towards the sides of the platforms.
- the fittings are still formed of a slender piece massive in the envelope, which can be sectored or composed of a plurality of elements.
- Figure 1 shows essentially a turbomachine as usual provided with several stages of compressors, turbines, etc., and which opens, on the left in the figure, by a blower input S composed of a rotor disc 8 carrying a circular stage of radial blades 1 which separate platforms 2 delimiting a flow vein.
- a blower input S composed of a rotor disc 8 carrying a circular stage of radial blades 1 which separate platforms 2 delimiting a flow vein.
- FIG 3 We can see two blades 1 adjacent and an intermediate platform 2, composed a central spar 3 and cores 4 on the one hand and other side member 3.
- the cores 4 have external flanks 6 oriented towards the blades 1 and which flare outward in a radial direction.
- the game 7, determined by the mounting method, with the blades 1 is only a few millimeters.
- Platform parts 2 are in composite material, which significantly reduces the rotor. We see in Figure 2 that they extend over all the length of disc 8, and exceed two sides by an upstream appendage 10 and an appendage downstream 11. An upstream ferrule 12 and a downstream ferrule 13 attached to the side faces of the disc 8 and fixed to these faces according to known arrangements cover Appendices 10 and 11 respectively platform 2 and thus hold these parts against axial and radial movements. In this realization, the platform parts 2 are held by the ferrules 12 and 13 a few tenths of a millimeter from the surface of the disc 8.
- the seals that occupy games 7 have the general reference 15 on the figure 3.
- Each consists of an envelope 16 formed of an internal face 17, an external face 18 and a radially internal heel 19.
- the section of envelope 16 is therefore triangular as it is shown, when inserting the parts of platform 2.
- a slender piece in the shape of rod 20 is engaged in the envelope 16 and occupies part of the volume it encompasses.
- Baguette 20 is not necessarily flexible and can be made of metal or of composite material, but whose mass is sufficient for it to move in the envelope 16 under the action of centrifugal forces created at operation.
- the casing 16 is made of elastomer, its face outer 18 and heel 19 have the ability to deform, and the rod 20 has the freedom to slide in the envelope 16 outwards to get closer from the place of game 7 and fill it.
- Baguette 20 is advantageously cylindrical with all its sections for facilitate its sliding.
- the envelope 16 then takes the shape of a triangle with the point inwards in a radial direction instead of being outward.
- the internal face 17 remains for its part glued to the side 6 corresponding.
- FIG 4 illustrates this realization of the invention in centripetal view.
- Each platform piece 2 carries two seals 15 similar, even if the respective games 7a and 7b which separate the edge of the platform piece 2 from the blades 1 between which it is located can be different: the flexibility of the envelope 16 allows bridge wide as well as narrow 7 games.
- the sides 6 of the platform pieces 2 are substantially parallel to the sides of the vanes 1 in front of which they extend, and that the seals 15 are bent so similar. Games 7 are thus filled over their entire length by a substantially uniform movement of translation of the sticks 20.
- FIG. 6 illustrates an embodiment in which platform parts 2 have as the vanes 1 a foot 5 engaged in a cavity of the disc 8 produced by a pinout. Ferrules 12 and 13 can then be omitted.
- Figure 7 illustrates another embodiment of the invention, in which the internal face, here 17 ′, of the casing 16 ′ of the seals 15 is glued to the flank of the blade 1, and the external face 18 'and the talcn 19 'are directed towards the side 6 of the platform 2.
- the operation is the even because centrifugal forces move the wand 20 towards the narrow portion of the game and therefore fill it.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
- la figure 1 est une vue générale d'une machine où l'invention est utilisée,
- la figure 2 est une coupe transversale de l'assemblage représentant une plate-forme maintenue en place par des viroles amont et aval,
- la figure 3 est une coupe dans le sens circonférentiel de l'assemblage de la figure 2,
- la figure 4 est une vue de dessus partiellement éclatée,
- la figure 5 est un détail de la figure 3 et qui illustre le comportement de la garniture d'étanchéité lorsque le moteur tourne conformément à l'invention,
- la figure 6 est une coupe dans le sens circonférentiel d'une variante de l'invention,
- et la figure 7 est une vue analogue à la figure 5 qui illustre une autre réalisation de l'invention.
Claims (3)
- Assemblage pour rotor, composé d'aubes (1) encastrées dans le rotor, de plates-formes (2) situées et maintenues en place entre des paires d'aubes (1) consécutives, des jeux (7) substantiellement longitudinaux subsistant entre les aubes (1) et les plates-formes (2), des garnitures d'étanchéité (15) occupant en fonctionnement les jeux (7), caractérisé en ce que les garnitures d'étanchéité (15) sont formées d'une enveloppe (16) composée d'une face (17) portant contre des flancs (6) des plates-formes (2) et d'une face souple (18, 19) dirigée vers les surfaces des aubes, les garnitures (15) étant encore formées d'une pièce longiligne massive (20) dans l'enveloppe (16).
- Assemblage pour rotor, composé d'aubes (1) encastrées dans le rotor, de plates-formes (2) situées et maintenues en place entre des paires d'aubes (1) consécutives, des jeux (7) substantiellement longitudinaux subsistant entre les aubes (1) et les plates-formes (2), des garnitures d'étanchéité (15) occupant en fonctionnement les jeux (7), caractérisé en ce que les garnitures d'étanchéité (15) sont formées d'une enveloppe (16') composée d'une face (17') portant contre des flancs des aubes et d'une face souple (18', 19') dirigée vers les surfaces des plate-formes, les garnitures (15) étant encore formées d'une pièce longiligne massive (20) dans l'enveloppe (16).
- Assemblage pour rotor selon la revendication 1 ou 2, caractérisé en ce que l'enveloppe (16) a une section substantiellement triangulaire s'amincissant radialement vers l'extérieur.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9402025A FR2716502B1 (fr) | 1994-02-23 | 1994-02-23 | Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires. |
FR9402025 | 1994-02-23 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0669451A1 EP0669451A1 (fr) | 1995-08-30 |
EP0669451B1 true EP0669451B1 (fr) | 1998-04-08 |
Family
ID=9460331
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95400353A Expired - Lifetime EP0669451B1 (fr) | 1994-02-23 | 1995-02-21 | Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires |
Country Status (4)
Country | Link |
---|---|
US (1) | US5520514A (fr) |
EP (1) | EP0669451B1 (fr) |
DE (1) | DE69501973T2 (fr) |
FR (1) | FR2716502B1 (fr) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2739135B1 (fr) * | 1995-09-21 | 1997-10-31 | Snecma | Agencement amortisseur monte entre des aubes de rotor |
GB9602129D0 (en) * | 1996-02-02 | 1996-04-03 | Rolls Royce Plc | Rotors for gas turbine engines |
DE19654471B4 (de) * | 1996-12-27 | 2006-05-24 | Alstom | Rotor einer Strömungsmaschine |
EP1124038A1 (fr) * | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Aubage de turbine |
US6916154B2 (en) * | 2003-04-29 | 2005-07-12 | Pratt & Whitney Canada Corp. | Diametrically energized piston ring |
CN100430606C (zh) * | 2004-01-05 | 2008-11-05 | 财团法人工业技术研究院 | 高速悬臂离心式压缩机转子机构 |
EP1925781A1 (fr) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Agencement d'aubes |
US7762781B1 (en) | 2007-03-06 | 2010-07-27 | Florida Turbine Technologies, Inc. | Composite blade and platform assembly |
GB0806171D0 (en) * | 2008-04-07 | 2008-05-14 | Rolls Royce Plc | Aeroengine fan assembly |
EP2447476A3 (fr) | 2010-11-01 | 2017-11-15 | Rolls-Royce plc | Pièce de remplissage annulaire pour un disque de rotor de turbine à gaz |
FR3003294B1 (fr) * | 2013-03-15 | 2018-03-30 | Safran Aircraft Engines | Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante |
US9926798B2 (en) | 2014-08-13 | 2018-03-27 | Rolls-Royce Corporation | Method for manufacturing composite fan annulus filler having nano-coating |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1331209A (en) * | 1969-10-28 | 1973-09-26 | Secr Defence | Bladed rotors for fluid flow machines |
US4111603A (en) * | 1976-05-17 | 1978-09-05 | Westinghouse Electric Corp. | Ceramic rotor blade assembly for a gas turbine engine |
FR2517779B1 (fr) * | 1981-12-03 | 1986-06-13 | Snecma | Dispositif d'amortissement des aubes d'une soufflante de turbomachine |
US4872812A (en) * | 1987-08-05 | 1989-10-10 | General Electric Company | Turbine blade plateform sealing and vibration damping apparatus |
US4784573A (en) * | 1987-08-17 | 1988-11-15 | United Technologies Corporation | Turbine blade attachment |
FR2669686B1 (fr) * | 1990-11-28 | 1994-09-02 | Snecma | Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine. |
US5222865A (en) * | 1991-03-04 | 1993-06-29 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
GB9209895D0 (en) * | 1992-05-07 | 1992-06-24 | Rolls Royce Plc | Rotors for gas turbine engines |
FR2706528B1 (fr) * | 1993-06-10 | 1995-09-01 | Snecma | Plate-forme séparée inter-aube de disque ailette de rotor de turbomachine. |
US5415526A (en) * | 1993-11-19 | 1995-05-16 | Mercadante; Anthony J. | Coolable rotor assembly |
-
1994
- 1994-02-23 FR FR9402025A patent/FR2716502B1/fr not_active Expired - Fee Related
-
1995
- 1995-02-21 US US08/391,028 patent/US5520514A/en not_active Expired - Fee Related
- 1995-02-21 DE DE69501973T patent/DE69501973T2/de not_active Expired - Fee Related
- 1995-02-21 EP EP95400353A patent/EP0669451B1/fr not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE69501973T2 (de) | 1998-08-20 |
EP0669451A1 (fr) | 1995-08-30 |
FR2716502B1 (fr) | 1996-04-05 |
FR2716502A1 (fr) | 1995-08-25 |
DE69501973D1 (de) | 1998-05-14 |
US5520514A (en) | 1996-05-28 |
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