EP0669451A1 - 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
EP0669451A1
EP0669451A1 EP95400353A EP95400353A EP0669451A1 EP 0669451 A1 EP0669451 A1 EP 0669451A1 EP 95400353 A EP95400353 A EP 95400353A EP 95400353 A EP95400353 A EP 95400353A EP 0669451 A1 EP0669451 A1 EP 0669451A1
Authority
EP
European Patent Office
Prior art keywords
blades
platforms
envelope
vanes
face
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
EP95400353A
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English (en)
French (fr)
Other versions
EP0669451B1 (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
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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 seal arranged in an assembly of blades on a fan disk and intermediate platforms, thus forming a rotor.
  • a common design is to produce the platform segments of a block with the vanes. It has been exposed in numerous patents and has the advantage that the platform segments join halfway between the blades by straight junctions which it is easy to fill with a gasket. The disadvantage is that the platforms, whose extension is substantially perpendicular to that of the blades, complicate their production.
  • the invention thus applies to constructions where the platforms are produced as separate parts of the blades and each extend between a pair of blades, forming a clearance with each of them, which unfortunately implies that the games are important along the blades because of the complexity of the shape thereof 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 can also be applied to a rotor, the platforms of which have a foot which is housed in cells machined in the disc.
  • the invention relates to a seal which can be placed in each of these sets and which fills them correctly. More specifically, it relates to an assembly for a rotor, composed of vanes embedded in the rotor and of platforms located between pairs of consecutive vanes, substantially longitudinal clearances remaining between the vanes and the platforms, and this assembly is characterized in that it comprises seals occupying the games and formed of an envelope composed of a face bearing against the sides of the platforms and a flexible face directed towards the surfaces of the blades.
  • the envelope may, in an equivalent manner, be composed of a face bearing against the surfaces of the blades and of a flexible face directed towards the sides of the platforms.
  • the linings are also formed of a solid elongated piece in the envelope, which can be sectored or composed of a plurality of elements.
  • FIG. 1 essentially represents a turbomachine provided as usual with several stages of compressors, turbines, etc., and which opens, on the left in the figure, by an inlet fan S composed of a rotor disk 8 carrying a circular stage of radial vanes 1 which separate platforms 2 delimiting a flow stream.
  • FIG. 3 We now deal with FIG. 3.
  • the cores 4 have external flanks 6 oriented towards the blades 1 and which widen in the radial direction towards the outside.
  • the clearance 7, determined by the mounting method, with the blades 1 is only a few millimeters.
  • the platform parts 2 are made of composite material, which significantly lightens the rotor. We see in Figure 2 that they extend over all the length of the disc 8, and protrude from both sides by an upstream appendage 10 and a downstream appendage 11. An upstream ferrule 12 and a downstream ferrule 13 attached to the lateral faces of the disc 8 and fixed to these faces according to known arrangements respectively cover the appendages 10 and 11 of the platform parts 2 and thus retain these parts against the axial and radial movements. In this embodiment, the platform pieces 2 are held by the ferrules 12 and 13 a few tenths of a millimeter from the surface of the disc 8.
  • the seals which occupy the sets 7 have the general reference 15 in FIG. 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 the envelope 16 is therefore triangular as shown, at the time of the insertion of the platform parts 2.
  • a long, baguette-shaped part 20 is engaged in the envelope 16 and occupies part of the volume it encompasses.
  • the rod 20 is not necessarily flexible and can be formed from metal or composite material, but whose mass is sufficient for it to move in the envelope 16 under the action of centrifugal forces created during operation.
  • the casing 16 is made of elastomer, its outer face 18 and the heel 19 have the ability to deform, and the rod 20 has the freedom to slide in the casing 16 towards outside to get closer to the place of game 7 and fill it.
  • the rod 20 is advantageously cylindrical with all its sections to facilitate its sliding.
  • the envelope 16 then takes the form of a triangle, the point of which is inwards in the radial direction instead of being outwards.
  • the internal face 17 remains for its part glued to the corresponding flank 6.
  • FIG. 4 illustrates this embodiment of the invention in centripetal view.
  • Each platform piece 2 carries two similar seals 15, even if the respective clearances 7a and 7b which separate the edge of the platform piece 2 from the blades 1 between which it is located may be different: the flexibility of the casing 16 makes it possible to fill wide as well as narrow clearances 7.
  • the sides 6 of the platform parts 2 are substantially parallel to the sides of the blades 1 in front of which they extend, and that the seals 15 are similarly curved.
  • the games 7 are thus filled over their entire length by a substantially uniform movement of translation of the rods 20.
  • FIG. 6 illustrates an embodiment in which the platform parts 2 have, like the blades 1, a foot 5 engaged in a cell of the disc 8 produced by a broaching.
  • the ferrules 12 and 13 can then be omitted.
  • FIG. 7 illustrates another embodiment of the invention, in which the internal face, here 17 ′, of the envelope 16 ′ of the seals 15 is glued to the flank of the blade 1, and the external face 18 ′ and the heel 19 ′ are directed towards the flank 6 of the platform 2. It can be seen that the operation is the same because the centrifugal forces move the rod 20 towards the narrow portion of the game and therefore fill it.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP0669451A1 (de) 1995-08-30
EP0669451B1 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0787890A3 (de) * 1996-02-02 1999-04-28 ROLLS-ROYCE plc Gasturbinenrotor

Families Citing this family (11)

* 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
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

Citations (6)

* 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
EP0081416A1 (de) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dämpfungsvorrichtung für die Schaufeln eines Turbomaschinengebläses
FR2619158A1 (fr) * 1987-08-05 1989-02-10 Gen Electric Dispositif d'etancheification et d'amortissement des vibrations de la plate-forme d'une aube de turbine
EP0488874A1 (de) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4111603A (en) * 1976-05-17 1978-09-05 Westinghouse Electric Corp. Ceramic rotor blade assembly for a gas turbine engine
US4784573A (en) * 1987-08-17 1988-11-15 United Technologies Corporation Turbine blade attachment
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
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

Patent Citations (6)

* 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
EP0081416A1 (de) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dämpfungsvorrichtung für die Schaufeln eines Turbomaschinengebläses
FR2619158A1 (fr) * 1987-08-05 1989-02-10 Gen Electric Dispositif d'etancheification et d'amortissement des vibrations de la plate-forme d'une aube de turbine
EP0488874A1 (de) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0787890A3 (de) * 1996-02-02 1999-04-28 ROLLS-ROYCE plc Gasturbinenrotor

Also Published As

Publication number Publication date
FR2716502A1 (fr) 1995-08-25
US5520514A (en) 1996-05-28
EP0669451B1 (de) 1998-04-08
DE69501973D1 (de) 1998-05-14
DE69501973T2 (de) 1998-08-20
FR2716502B1 (fr) 1996-04-05

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