EP0140736B1 - Dispositif de liaison et d'étanchéité de secteurs d'aubes de stator de turbine - Google Patents

Dispositif de liaison et d'étanchéité de secteurs d'aubes de stator de turbine Download PDF

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Publication number
EP0140736B1
EP0140736B1 EP84401766A EP84401766A EP0140736B1 EP 0140736 B1 EP0140736 B1 EP 0140736B1 EP 84401766 A EP84401766 A EP 84401766A EP 84401766 A EP84401766 A EP 84401766A EP 0140736 B1 EP0140736 B1 EP 0140736B1
Authority
EP
European Patent Office
Prior art keywords
segments
sectors
arrangement according
lining
sealing
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
Application number
EP84401766A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0140736A3 (en
EP0140736A2 (fr
Inventor
Claude Christian Hallinger
Alain Marie Joseph Lardellier
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0140736A2 publication Critical patent/EP0140736A2/fr
Publication of EP0140736A3 publication Critical patent/EP0140736A3/fr
Application granted granted Critical
Publication of EP0140736B1 publication Critical patent/EP0140736B1/fr
Expired legal-status Critical Current

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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
    • F01D11/08—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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the invention relates to a device for connecting and sealing a turbine distributor stage, said stage consisting of sectors formed of fins arranged between an external casing and an internal cylindrical shell, the conjugate edges of the sectors being cut according to a sinuous shape line, the inner part of the inner ferrule carrying a honeycomb lining with hexagonal cells cooperating with the wipers of a rotor disc to ensure sealing between the upstream rotor stage and the downstream rotor stage .
  • French patent 1331030 discloses a fixed compressor blade in which the fins are fixed to an inner ring and to an outer ring.
  • the outer ring is formed by segments with sinuous edges which overlap and which are joined by welding to form an outer strip in one piece, the overlapping zones between segments constituting reinforcing ribs.
  • French patent 1,519,898 also describes a rotor blade in which the outer ring is formed by lateral segments provided at one end of the blades. The axial edges of the neighboring segments form a Z-shaped cutout, between the end branches of which there is a clearance. The phenomenon of deflection of the fins is used to ensure a continuous connection in operation between all the fins of the same blade.
  • French patent 2514409 shows a rotor blade made from sectors comprising six blades connected at one of their ends by a single heel cooperating with a groove in the rotor disc and at the other ends by a peripheral heel.
  • the circumferential ends of the heels have a configuration in Z which allows the assembly by interlocking of several sectors in succession.
  • grooves in which are engaged metal plates which ensure the radial seal between the neighboring sectors.
  • the invention proposes to give to the ends of the stator vane segments a particular Z configuration allowing the expansion of the various elements while avoiding vibrations and providing an improvement in the seal between the stator distributor stage and the upstream rotor stages. and downstream by a particular arrangement of sealing plates between the edges of the blade segments and by a determined orientation of the honeycomb material forming the lining of the labyrinth seals, relative to the plane of rotation of the wipers of said seals.
  • the device according to the invention is remarkable in that the conjugate edges of the neighboring sectors are formed of three rectilinear segments, at least two of the extreme segments of the edge of a sector delimiting with the two extreme segments of the conjugate edge of a neighboring sector a space to compensate for thermal expansion, the middle segments of the two sectors being in contact; and in that the conjugate faces of at least one end segment of two neighboring sectors carry sealing means, and in that a gasket with honeycomb structure is fixed on the inner shell so that the sides welded hexagonal cells make with the plane of rotation of the rotor discs carrying the wipers an angle of 60 °.
  • FIG. 1 represents a partial view of a turbine comprising a fixed distributor stage 1, or stator, disposed between two stages of movable or rotor blades 2 and 3.
  • the rotor stages 2 and 3 consist of rotor disks 4 and 5 bearing vanes 6.
  • the foot of the blades is shaped to cooperate with axial grooves provided in the rim of the rotor.
  • the rotor disks are joined together by bolts 7 which also hold the disc & carrying an inter-stage seal 9 of the labyrinth type.
  • This joint known per se consists of two or more radial annular extensions or wipers 10 cooperating with an annular cylindrical lining 11 of honeycomb structure, this structure is fixed on the inner ferrule 15 of the stator blading of the stage distributor 1.
  • the distributor stage consists of sectors 12, 13 ... ( Figure 2) comprising at least one fin 14 fixed by its external foot to the periphery of the turbine casing and carrying at its internal end circumferential segments forming with the neighboring segments of the other fins the inner ring 15.
  • the sectors comprise several fins 14. These fins are fixed at one of their ends to a cylindrical segment carrying a foot for fixing to the turbine casing, and at the other end, to a segment of revolution generally cylindrical or conical forming with the adjacent segments of the neighboring sectors the inner ferrule 15 continues on the internal face of which is fixed the lining 11 in honeycomb of the labyrinth seal.
  • the circumferential ends of the sectors are cut along a line of sinuous or broken shape comprising three rectilinear segments defining approximately a Z. The combined edges of two neighboring sectors cooperate to limit the relative axial displacements due to vibrations.
  • the spaces 16 and 17 separating the extreme rectilinear segments 161, 162 and 171, 172 from the conjugate edges of two neighboring sectors 12, 13 make it possible to compensate for thermal expansion.
  • the middle segments 181 and 182 delimit a reduced space at a contact line 18 parallel to the radial plane of the distributor stage. This arrangement prevents axial displacements of the sectors relative to each other but does not hinder the circumferential displacements due to thermal expansion.
  • the segments 181, 182 of the conjugate edges of two neighboring sectors are filled with a material resistant to wear and to matting for example a cobalt-based alloy.
  • the material is preferably used in the form of welded plates 183, 184.
  • the sealing of the inner ring 15 is the result of the sealing obtained between the conjugate edges of the neighboring sectors.
  • the seal between the segments 181 and 182 is obtained by the contact of the corresponding faces or by the contact of the faces of the plates 183, 184 lining the segments 181, 182.
  • an extreme segment 161, 162 is provided which is very long compared to the others and in particular compared to the segment 171, 172 which it is approximately parallel to it.
  • the segment 161, 162 extends approximately from the upstream radial edge of the lining 11 to the downstream radial edge of the sectors 12, 13.
  • the faces of the segments 161, 162 of two neighboring sectors 12, 13 carry sealing means consisting of two corresponding grooves in which is housed a sealing plate 19 which extends approximately to the radial edge downstream of the sectors, and in any case downstream of the aerodynamic neck of the blading "C".
  • the non-sealed part of the internal shroud is thus limited to segment 171, 172 of very short length upstream of the inlet of the distributor vane and does not cause appreciable disturbances in the flow of the air flow.
  • the sealing of the distributor stage 1 with the rotor is, as known, produced by a labyrinth seal 9.
  • a gasket with a honeycomb structure 11 is fixed by known means (welding, soldering, bolting, gluing, etc. .) on the surface of the inner shell.
  • the wipers 10, carried by a disc 8 secured to the rotor, make circumferential grooves in the honeycomb leading to a very small clearance between the rotor and the stator.
  • the hexagonal cellular structure of the honeycomb is obtained in a known manner by embossing sheets of stainless steel or of alloy resistant to high temperature which are then welded to each other by the top of their corrugations.
  • a honeycomb cell therefore has two opposite sides 20 of the hexagon stiffened by welding.
  • the lining 11 was made up of cylindrical sectors fixed to the internal ring of the distributor vane and machined so that a row of rigid sides 20 (FIG. 3) form the circumferential edge of the lining and are aligned parallel to the plane of rotation of the wiper disk whose direction is indicated by the arrow 22 in FIG. 3.
  • the lining according to the invention (FIG. 4) is oriented so that the planes passing through the sides 20 carrying the weld make an angle of 60 ° relative to the planes of rotation of the wipers whose direction is indicated by arrow 22 in FIG. 4.
  • the number of walls of steel sheets, seen by the wipers is therefore reduced, and the penetration results in a reduced effort. and by the absence of parasitic component on the distributors.
  • This honeycomb arrangement is particularly desirable for equipping the outer seals 23 and 24 at the end of the moving vane 2 and 3.
  • the prior art (FIG. 5) is such that during penetration of the wipers 25 and 26 in the abradable honeycomb, the axial component produced in the direction of least resistance 21 results in a tendency for the abrupt engagement of the moving blades 3 in this direction which can lead to the destruction of the seal and to deterioration of the outer part of the movable blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP84401766A 1983-09-21 1984-09-06 Dispositif de liaison et d'étanchéité de secteurs d'aubes de stator de turbine Expired EP0140736B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8314974A FR2552159B1 (fr) 1983-09-21 1983-09-21 Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
FR8314974 1983-09-21

Publications (3)

Publication Number Publication Date
EP0140736A2 EP0140736A2 (fr) 1985-05-08
EP0140736A3 EP0140736A3 (en) 1985-06-05
EP0140736B1 true EP0140736B1 (fr) 1987-01-07

Family

ID=9292384

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84401766A Expired EP0140736B1 (fr) 1983-09-21 1984-09-06 Dispositif de liaison et d'étanchéité de secteurs d'aubes de stator de turbine

Country Status (5)

Country Link
US (1) US4623298A (sh)
EP (1) EP0140736B1 (sh)
JP (1) JPS60145403A (sh)
DE (1) DE3461945D1 (sh)
FR (1) FR2552159B1 (sh)

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FR2930592B1 (fr) * 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine
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US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US8444371B2 (en) 2010-04-09 2013-05-21 General Electric Company Axially-oriented cellular seal structure for turbine shrouds and related method
US8961135B2 (en) 2011-06-29 2015-02-24 Siemens Energy, Inc. Mateface gap configuration for gas turbine engine
FR2979662B1 (fr) * 2011-09-07 2013-09-27 Snecma Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
US9840917B2 (en) * 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
ITCO20110068A1 (it) * 2011-12-20 2013-06-21 Nuovo Pignone Spa Metodo e tenuta a nido d'ape
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US10443736B2 (en) * 2015-10-01 2019-10-15 United Technologies Corporation Expansion seal
US10690251B2 (en) 2016-09-23 2020-06-23 General Electric Company Labyrinth seal system and an associated method thereof
FR3058756B1 (fr) 2016-11-15 2020-10-16 Safran Aircraft Engines Turbine pour turbomachine
FR3064669B1 (fr) * 2017-03-31 2020-11-13 Safran Aircraft Engines Dispositif d'etancheite d'une turbomachine a revetement abradable
FR3081500B1 (fr) * 2018-05-23 2020-05-22 Safran Aircraft Engines Secteur angulaire d'aubage de turbomachine a etancheite perfectionnee
FR3081499B1 (fr) 2018-05-23 2021-05-28 Safran Aircraft Engines Secteur angulaire d'aubage de turbomachine a etancheite perfectionnee
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IT201900014724A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
IT201900014736A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
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Also Published As

Publication number Publication date
JPH023008B2 (sh) 1990-01-22
EP0140736A3 (en) 1985-06-05
US4623298A (en) 1986-11-18
EP0140736A2 (fr) 1985-05-08
JPS60145403A (ja) 1985-07-31
DE3461945D1 (en) 1987-02-12
FR2552159A1 (fr) 1985-03-22
FR2552159B1 (fr) 1987-07-10

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