EP0017534B1 - Garniture d'étanchéité amovible pour segment de distributeur de turbomachine - Google Patents

Garniture d'étanchéité amovible pour segment de distributeur de turbomachine Download PDF

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Publication number
EP0017534B1
EP0017534B1 EP80400349A EP80400349A EP0017534B1 EP 0017534 B1 EP0017534 B1 EP 0017534B1 EP 80400349 A EP80400349 A EP 80400349A EP 80400349 A EP80400349 A EP 80400349A EP 0017534 B1 EP0017534 B1 EP 0017534B1
Authority
EP
European Patent Office
Prior art keywords
radial
stator
slots
segments
seatings
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
EP80400349A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0017534A1 (fr
Inventor
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 EP0017534A1 publication Critical patent/EP0017534A1/fr
Application granted granted Critical
Publication of EP0017534B1 publication Critical patent/EP0017534B1/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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Definitions

  • the present invention relates to a removable seal for a turbomachine distributor segment.
  • Distributors of turbines which are made up of sectors comprising several blades, connected to each other by an external ferrule fixed on the turbine casing and by an internal ferrule between which and the rotor is mounted the seal comprising an element of sealing fixed to the bottom of a support member consisting of a folded sheet gutter with U-shaped section, of length equal to several segments of the distributor, on which is engaged the internal ring of the distributor segments which has a shape corresponding to section U-shaped, oriented in the same direction.
  • a lining is known for example from US-A-3,028,141.
  • the fittings are fixed to the internal flange by means of bolts, but due to the high thermal stresses which the fasteners undergo, it is necessary to use screws of a large diameter and the corresponding nuts are subjected to a considerable heating in turbulence caused by the proximity of the rotor wipers.
  • the present invention relates to a removable seal which avoids fixing by bolts.
  • a sealing element is fixed to the bottom of a support member in the form of a U-shaped gutter on which the internal ring of the distributor segments is engaged, which has a corresponding shape in U-section, said ferrule comprising on its radial faces L-shaped housings extending radially and circumferentially in which are engaged tongues formed in the radial faces of the support member for the seal.
  • GB-A-1 534124 describes vanes fixed to the circumference of a stator disc by studs, each stud being engaged in an L-shaped housing established at the foot of the blade.
  • the L-shaped housings formed on the radial faces of the ferrule can be either slots cut in the wall of these faces, or machined cells, by electro-erosion for example, in the thickness of bosses coming from foundry.
  • the seal is integral with the distributor, the latter being integral with the turbine housing, the expansion of which is controlled by an alternating cooling and heating system, so that the clearance between the stator is perfectly controlled. and the rotor.
  • FIG 1 there is shown a distributor segment 1 which consists of a casting part comprising vanes 2 which are connected together by an external ferrule 3 having fixing members 4, 4a on the turbine casing and by an internal ferrule 5.
  • the internal ferrule 5 has the shape of a gutter with a U-section, the radial faces 6, 6a of which, in the example shown, have slots 7 in the shape of an L, having a radial part 7a, opening onto the edge of said faces. and extending by a circumferentially extending part 7b.
  • a support member 8 for the seal Inside the shell 5 is engaged (FIG. 3) a support member 8 for the seal.
  • the support member 8 ( Figures 2 and 3) consists of a folded sheet metal gutter with a U-section, the length of which is likely to correspond to that of several sectors 1, 1a a on which the support member is engaged. 8.
  • the support member 8 has on its radial faces 9, 9a (FIG. 2) series of slots 10, 10a, 10b regularly spaced whose pitch corresponds to that of the L-shaped slots 7 provided on the internal ferrule of the distributor, such so that each series of slots 10, 10a, 10b delimits tongues 11 and 12, one of which 12 is raised at right angles to the radial faces 9, 9a is engaged (FIG. 3) in the circumferential part 7b of the slot 7 of the shell 5 of the distributor segments and of which the other 11 after folding is engaged in the radial part 7a of the slot 7.
  • shutter members 13 of U-section which are located in line with the slots 10, 10a, 10b, so that when the tongues 12 are raised for their engagement in the slots 7, the upstream-downstream gas tightness is always ensured.
  • the sealing element 14 which is constituted in particular by a honeycomb coating, is fixed to the bottom of the support member 8 ( Figures 2 and 3) in particular by brazing.
  • the seal between two segments 1, 1a of the distributor at the level of the vein can be supplemented by plates 15 (FIGS. 3, 4, 5) which are engaged in circumferential slots 16 formed in the internal ferrule 5 of the distributor segments and laterally having an opening 17 for engaging the plate 15.
  • the plate 15 After its engagement through the opening 17 in the slot 16, the plate 15 is pushed to the end and it takes its place in said groove.
  • a force F and then a push P are exerted with a rule introduced between two distributor segments.
  • a support member 8 for sealing element 14 is introduced into the internal ferrule 5 of the distributor so that the folded tabs 12 engage in the radial part 7a of the slots. 7 in L provided on the radial faces 6, 6a of the ferrule.
  • the tongues 12 are made to penetrate into the circumferential part 7b of the slots 7 of the dispenser, which has the effect of radially locking the support member of the packing.
  • the slots 7 in L are oriented so that the rotation of the mobile forces the tongues 12 to engage in the direction of the bottom of the part 7b of the slot in the locking direction; the rupture of a tongue 11 cannot therefore cause the loss of a sealing support member 8.
  • the seal is integral with the distributor, the latter being integral with the turbine casing, the expansion of which is controlled, by an alternating cooling and heating system; the clearance between the stator and the rotor is perfectly controlled.
  • the seal between two segments 1, the at the level of the vein can be completed by the plates 15 which are introduced into your housings 16 provided on the internal ferrule 5.
  • This arrangement does not improve the upstream-downstream sealing produced by the sealing element 14, but it in fact restores the vein; this is particularly important at the trailing edge.
  • Such a device makes it possible to link the seal to the movements of the turbine casing and thus to optimize the play between the rotor and the stator of the labyrinth; moreover, it keeps the sectors in their plan.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
EP80400349A 1979-03-27 1980-03-17 Garniture d'étanchéité amovible pour segment de distributeur de turbomachine Expired EP0017534B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7907590 1979-03-27
FR7907590A FR2452590A1 (fr) 1979-03-27 1979-03-27 Garniture d'etancheite amovible pour segment de distributeur de turbomachine

Publications (2)

Publication Number Publication Date
EP0017534A1 EP0017534A1 (fr) 1980-10-15
EP0017534B1 true EP0017534B1 (fr) 1984-03-14

Family

ID=9223584

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80400349A Expired EP0017534B1 (fr) 1979-03-27 1980-03-17 Garniture d'étanchéité amovible pour segment de distributeur de turbomachine

Country Status (4)

Country Link
US (1) US4295785A (OSRAM)
EP (1) EP0017534B1 (OSRAM)
DE (1) DE3066906D1 (OSRAM)
FR (1) FR2452590A1 (OSRAM)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3797213B1 (fr) * 2018-05-23 2024-07-10 Safran Aircraft Engines Assemblage de deux secteurs angulaires adjacents de couronne d'aubages fixes de turbomachine et couronne d'aubages fixes correspondante
EP3797212B1 (fr) * 2018-05-23 2025-01-08 Safran Aircraft Engines Secteur angulaire d'aubage de turbomachine avec etancheite entre secteurs

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4346904A (en) * 1980-11-26 1982-08-31 Watkins Jr Shelton Honeycomb structure for use in abradable seals
GB2112878B (en) * 1981-12-28 1985-12-04 United Technologies Corp Air seal for compressor stator
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
US4710097A (en) * 1986-05-27 1987-12-01 Avco Corporation Stator assembly for gas turbine engine
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
FR2619330B1 (fr) * 1987-08-12 1994-03-11 Snecma Procede de realisation d'etages de stator de compresseur ou de turbine, aubes et grilles d'aubes ainsi obtenues
US5197856A (en) * 1991-06-24 1993-03-30 General Electric Company Compressor stator
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
FR2758856B1 (fr) 1997-01-30 1999-02-26 Snecma Joint d'etancheite a plaquettes empilees glissant dans des fentes de reception
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
US6042334A (en) * 1998-08-17 2000-03-28 General Electric Company Compressor interstage seal
US6280000B1 (en) 1998-11-20 2001-08-28 Joseph A. Zupanick Method for production of gas from a coal seam using intersecting well bores
US6139264A (en) * 1998-12-07 2000-10-31 General Electric Company Compressor interstage seal
US6135715A (en) * 1999-07-29 2000-10-24 General Electric Company Tip insulated airfoil
US6409472B1 (en) 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
DE10305899B4 (de) * 2003-02-13 2012-06-14 Alstom Technology Ltd. Dichtungsanordnung zur Dichtspaltreduzierung bei einer Strömungsrotationsmaschine
US20040239040A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Nozzle interstage seal for steam turbines
GB2422641B (en) * 2005-01-28 2007-11-14 Rolls Royce Plc Vane for a gas turbine engine
US7635251B2 (en) * 2006-06-10 2009-12-22 United Technologies Corporation Stator assembly for a rotary machine
FR2928961B1 (fr) * 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
FR2930592B1 (fr) 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine
EP2196629B1 (fr) * 2008-12-11 2018-05-16 Safran Aero Boosters SA Virole interne composite segmentée de redresseur de compresseur axial
US20130315708A1 (en) * 2012-05-25 2013-11-28 Jacob Romeo Rendon Nozzle with Extended Tab
EP2735707B1 (fr) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Redresseur de turbomachine axiale avec virole interne segmentée et compresseur associé
EP2871325B1 (de) 2013-11-12 2016-04-06 MTU Aero Engines GmbH Innenring einer Strömungsmaschine und Leitrad
BE1022513B1 (fr) * 2014-11-18 2016-05-19 Techspace Aero S.A. Virole interne de compresseur de turbomachine axiale
US10443417B2 (en) * 2015-09-18 2019-10-15 General Electric Company Ceramic matrix composite ring shroud retention methods-finger seals with stepped shroud interface
US10094244B2 (en) 2015-09-18 2018-10-09 General Electric Company Ceramic matrix composite ring shroud retention methods-wiggle strip spring seal
US9945257B2 (en) 2015-09-18 2018-04-17 General Electric Company Ceramic matrix composite ring shroud retention methods-CMC pin-head
EP3228827B1 (de) * 2016-04-05 2021-03-03 MTU Aero Engines GmbH Dichtungsträger für eine turbomaschine, zugehörige gasturbine und herstellungsverfahren
US10557364B2 (en) * 2016-11-22 2020-02-11 United Technologies Corporation Two pieces stator inner shroud
US20190078469A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Fan exit stator assembly retention system
US11149853B2 (en) * 2018-05-15 2021-10-19 Dell Products L.P. Airflow sealing by flexible rubber with I-beam and honeycomb structure
FR3091311B1 (fr) * 2018-12-31 2021-04-09 Safran Aircraft Engines Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine.
FR3091725B1 (fr) * 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine

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US2640679A (en) * 1950-03-21 1953-06-02 Gen Motors Corp Turbine or compressor stator ring
US2925998A (en) * 1952-12-22 1960-02-23 Gen Motors Corp Turbine nozzles
US2962809A (en) * 1953-02-26 1960-12-06 Gen Motors Corp Method of making a compressor seal
US2968467A (en) * 1956-11-14 1961-01-17 Orenda Engines Ltd Connecting means, especially for securing annular stator elements between supports whose positions are fixed
US3028141A (en) * 1957-03-25 1962-04-03 United Aircraft Corp Stator construction
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
US3601414A (en) * 1969-10-29 1971-08-24 Ford Motor Co Ceramic crossarm seal for gas turbine regenerators
US3727660A (en) * 1971-02-16 1973-04-17 Gen Electric Bolt retainer and compressor employing same
US3752599A (en) * 1971-03-29 1973-08-14 Gen Electric Bucket vibration damping device
US3846899A (en) * 1972-07-28 1974-11-12 Gen Electric A method of constructing a labyrinth seal
US3941500A (en) * 1974-06-10 1976-03-02 Westinghouse Electric Corporation Turbomachine interstage seal assembly
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4119389A (en) * 1977-01-17 1978-10-10 General Motors Corporation Radially removable turbine vanes

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3797213B1 (fr) * 2018-05-23 2024-07-10 Safran Aircraft Engines Assemblage de deux secteurs angulaires adjacents de couronne d'aubages fixes de turbomachine et couronne d'aubages fixes correspondante
EP3797212B1 (fr) * 2018-05-23 2025-01-08 Safran Aircraft Engines Secteur angulaire d'aubage de turbomachine avec etancheite entre secteurs

Also Published As

Publication number Publication date
DE3066906D1 (en) 1984-04-19
FR2452590A1 (fr) 1980-10-24
FR2452590B1 (OSRAM) 1982-05-21
EP0017534A1 (fr) 1980-10-15
US4295785A (en) 1981-10-20

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