EP0669451B1 - Abdichtung zwischen den Schaufeln und den zwischenliegenden Plattformen - Google Patents

Abdichtung zwischen den Schaufeln und den zwischenliegenden Plattformen Download PDF

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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
Application number
EP95400353A
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English (en)
French (fr)
Other versions
EP0669451A1 (de
Inventor
Jean-Pierre Louis Mareix
Philippe Jean-Pierre Pabion
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 EP0669451A1 publication Critical patent/EP0669451A1/de
Application granted granted Critical
Publication of EP0669451B1 publication Critical patent/EP0669451B1/de
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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)

Claims (3)

  1. Montageanordnung für einen Rotor, bestehend aus
    in den Rotor eingelassenen Schaufeln (1),
    Plattformen (2), die zwischen Paaren von aufeinanderfolgenden Schaufeln (1) liegen und dort festgehalten sind,
    im wesentlichen longitudinalen Spielräumen (7) zwischen den Schaufeln (1) und den Plattformen (2),
    und Dichtungen (15), die die Spielräume (7) im Betrieb ausfüllen,
       dadurch gekennzeichnet,
    daß die Dichtungen (15) von einer Hülle (16) gebildet sind, die eine an den Flanken (6) der Plattformen (2) anliegende Seite (17) und eine den Oberflächen der Schaufeln zugewandte nachgiebige Seite (18, 19) besitzt,
    und daß die Dichtungen (15) außerdem von einem langgestreckten massiven Teil (20) in der Hülle (16) gebildet sind.
  2. Montageanordnung für einen Rotor, bestehend aus
    in den Rotor eingelassenen Schaufeln (1),
    Plattformen (2), die zwischen Paaren von aufeinanderfolgenden Schaufeln (1) liegen und dort festgehalten sind,
    und im wesentlichen longitudinalen Spielräumen (7) zwischen den Schaufeln (1) und den Plattformen (2), Dichtungen (15), die im Betrieb die Spielräume (7) ausfüllen,
       dadurch gekennzeichnet,
    daß die Dichtungen (15) von einer Hülle (16) mit einer an den Flanken (6) der Schaufeln anliegenden Seite (17') und einer den Oberflächen der Schaufeln zugewandten nachgiebigen Seite (18', 19') gebildet sind, und daß die Dichtungen (15) weiterhin von einem langgestreckten massiven Teil (20) in der Hülle (16) gebildet sind
  3. Montageanordnung für einen Rotor nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Hülle (16) einen im wesentlichen dreieckförmigen Querschnitt besitzt, der radial nach außen dünner wird.
EP95400353A 1994-02-23 1995-02-21 Abdichtung zwischen den Schaufeln und den zwischenliegenden Plattformen Expired - Lifetime EP0669451B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9402025 1994-02-23
FR9402025A FR2716502B1 (fr) 1994-02-23 1994-02-23 Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.

Publications (2)

Publication Number Publication Date
EP0669451A1 EP0669451A1 (de) 1995-08-30
EP0669451B1 true EP0669451B1 (de) 1998-04-08

Family

ID=9460331

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95400353A Expired - Lifetime EP0669451B1 (de) 1994-02-23 1995-02-21 Abdichtung zwischen den Schaufeln und den zwischenliegenden Plattformen

Country Status (4)

Country Link
US (1) US5520514A (de)
EP (1) EP0669451B1 (de)
DE (1) DE69501973T2 (de)
FR (1) FR2716502B1 (de)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
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 (de) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbinenschaufelanordnung
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 (de) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Schaufelanordnung
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
US8827651B2 (en) 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler
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)

* Cited by examiner, † Cited by third party
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

Also Published As

Publication number Publication date
DE69501973T2 (de) 1998-08-20
FR2716502A1 (fr) 1995-08-25
DE69501973D1 (de) 1998-05-14
EP0669451A1 (de) 1995-08-30
US5520514A (en) 1996-05-28
FR2716502B1 (fr) 1996-04-05

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