EP0110757A1 - Leitschaufelbefestigung eines Axialverdichters für die aktive Kontrolle des Spiels zwischen Rotor und Stator - Google Patents

Leitschaufelbefestigung eines Axialverdichters für die aktive Kontrolle des Spiels zwischen Rotor und Stator Download PDF

Info

Publication number
EP0110757A1
EP0110757A1 EP83402151A EP83402151A EP0110757A1 EP 0110757 A1 EP0110757 A1 EP 0110757A1 EP 83402151 A EP83402151 A EP 83402151A EP 83402151 A EP83402151 A EP 83402151A EP 0110757 A1 EP0110757 A1 EP 0110757A1
Authority
EP
European Patent Office
Prior art keywords
sectors
upstream
downstream
grooves
envelope
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
EP83402151A
Other languages
English (en)
French (fr)
Other versions
EP0110757B1 (de
Inventor
Jean-Pierre "Domaine du Château des Dames" Ruis
Marcel Robert Soligny
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 EP0110757A1 publication Critical patent/EP0110757A1/de
Application granted granted Critical
Publication of EP0110757B1 publication Critical patent/EP0110757B1/de
Expired legal-status Critical Current

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Definitions

  • the invention relates to a device for suspending stator vanes of an axial compressor, more particularly adapted to the active control of the clearances between rotor and stator, the stator vanes being fixed to an inner casing formed of at least one cylindrical shell maintained by means of attachment to the inner wall of an outer casing, the space between the two casings being traversed by air taken from one stage of the compressor.
  • stator vanes are mounted on an inner envelope, made of a material preferably having a low coefficient of expansion, which is suspended from the 'outer casing by fixing means.
  • the control of the heat exchange of the interior envelope with the exterior envelope is obtained by ventilation of the exterior envelope and the space between the two envelopes.
  • British patent 2,019,954 describes a compressor casing comprising an outer casing and an inner casing, annular, coaxial.
  • the inner casing bears, radially inward, the stator vanes, and outwardly of the pins.
  • the pins cooperate with housings provided in the outer casing.
  • the inner envelope is formed by annular ferrules placed one behind the other along the longitudinal axis of the outer envelope. The nipples and the thickening of the area surrounding their housings form thermal bridges making it possible to control the thermal expansion or contraction of the internal envelope in the radial direction.
  • stator vanes as well as the friction bands ensuring the sealing of the ends of the blades of the rotor vanes are fixed to the inner casing of which they form a non-negligible portion. It is therefore relatively difficult to intervene on the stator to replace damaged blades or friction bands.
  • the purpose of the device according to the invention is to allow effective control of the compressor clearances by protecting the external envelope from the thermal radiation of the compressed air stream, but also to allow an easy change of the blades and the friction bands.
  • the device according to the invention is remarkable in that the inner envelope is formed of at least one set of hollow cylindrical sectors carrying alternately on their internal faces radial grooves for the stator vanes and the friction bands and on their external faces and in two radial planes fixing lugs capable of cooperating with horn lugs of the outer envelope.
  • FIG. 1 represents an axial half-section of a compression section or of an axial compressor, more particularly intended to equip a turbomachine.
  • the first three compression stages are arranged in an annular frustoconical channel, the widest part of which receives the air flow to be compressed.
  • the following compression stages are in a substantially cylindrical annular channel.
  • the compressor housing has two envelopes: an inner envelope 1 and an outer envelope 2.
  • the inner envelope fixed on the outer envelope carries the stator vanes and between the crowns of blades, friction bands made of abradable material and on which the ends of the blades of the rotor blades are likely to rub.
  • the stator vanes carry means at the free end of their blades ensuring sealing with the rotor. These means conventionally consist of a friction band 3 on which the liplets 4 carried by the rotor casing rub and are located between two rotor disks 5.
  • the rotor discs 5 have in their rims a groove 6 in which the blades are retained? rotor.
  • the upstream section 8 of the compressor is separated from the downstream section 9 by a sampling zone 10 which is in communication with the space 11 formed between the internal and external casings and with air intakes 12 intended to supply the compressed air. necessary for services and cooling systems for hot parts of the engine, such as the turbine. Furthermore, ventilation ramps 13, four in number according to the example shown, are arranged on sections of the outer casing and have the function of ventilating, by rows of orifices, the surface of the casing.
  • Means for controlling the admission of air into the ramps make it possible to control the temperature of the envelope and consequently its dimensional variations. This maintains the constancy of the clearances despite the different thermal inertias between the rotor discs and the compressor casing on which the stator vanes are fixed.
  • the outer envelope 2 consists of three cylindrical sections: an upstream section 14 and a downstream section 15, substantially symmetrical with respect to an intermediate section 16.
  • the sections 14 and 15 consist of a cylindrical shell 17 comprising at one end an external radial flange 18 and an internal radial flange 19.
  • the internal radial flange 19 is notched at regular intervals so as to leave tabs 20 comprising a bore cylindrical 21. These tabs will serve to maintain corresponding tabs 22 provided on the inner casing.
  • the intermediate section 16 is formed of a cylindrical shell whose upstream and downstream edges are welded to the edges of the sections 14 and 15, for example, by electron bombardment. Connections are provided on the outer surface of the shell to constitute the air intakes 12.
  • the ferrule also includes near each end a radial flange 23 directed inward and indented to form tabs 24 carrying in their center a bore.
  • a radial flange 23 directed inward and indented to form tabs 24 carrying in their center a bore.
  • the external flanges 18 are used for fixing the flanges 25 and 26 ensuring the seal between the external and internal envelopes, as well as possibly for blocking the fixing means 27, pins or tie rods passing through the lugs 20 and 24.
  • the inner envelope is formed of two sets of sectors, an upstream assembly 28 and a downstream assembly 29.
  • Figures 3 and 5 show a hollow cylindrical sector 30 whose projection on a horizontal plane (plane of Figure 2) is a parallelogram .
  • the sectors are arranged so that two of their parallel sides are in the radial planes.
  • the sectors of the downstream assembly 29 comprise on the internal face seven radial grooves (FIGS. 1 and 2), four grooves 31 intended to receive the friction bands 32 and three grooves 33 receiving the stator vanes 34, the friction bands and the blades successively alternating.
  • the sectors bear on their outer face the fixing lugs 22 intended to cooperate with the corresponding fixing lugs provided inside the outer casing.
  • the pins of the outer casing are fixed with those of the inner casing by the pins 27. Because the lateral edges of the sectors are not parallel to the axis of the compressor, it is expected that a spindle fixing 27 on two is fixed to two consecutive sectors.
  • the lateral edges 35 (FIG. 3) of the sectors carry inside and outside a groove intended to receive a bar 36 which ensures the radia tightness the between two consecutive sectors,
  • the holes 21 provided in the legs 2Q of the outer casing, receiving the pins are cylindrical, the holes provided in the legs 22 of the sector edge are oblong and the others are cylindrical.
  • the grooves 31 receiving the friction bands have a T-shaped section whose leg is directed towards the axis of the compressor .
  • the grooves 33 receiving the blades have a U-shaped section, the edges of the groove having a recess.
  • the recesses of the groove 33 are machined in the edges of the groove 31.
  • the friction bands 32 are fixed on supports 37 made up of two U-shaped rings 38 brazed symmetrically on a segment 39 of a cylindrical shell.
  • the frictmon bands, metallic or organic, are glued or brazed to the internal surface of the shell segment 39.
  • the stator vanes 34 are assembled into sectors 40 formed by two sections of annular ferrules 41, 42 carrying cutouts corresponding to the profile of the vanes and in which they are brazed or glued at their ends.
  • the portion of the ferrule section 42 directed towards the axis carries the friction band 3 cooperating with the wipers 4 of the rotor housing.
  • the ferrule section 41 is produced in the form of a box having on its peripheral edges two longitudinal tabs 43, 44, shaped so as to be able to be placed in the recesses of the groove 33
  • the edges of the ferrules 39 forming the support of the friction bands cover the recesses of the grooves 33 by providing grooves in which the blade sectors can be slid and held statorics.
  • the section of the ferrule 42 ⁇ shown in perspective in FIG. 4, has a width greater than that of the ferrule 44 in order to achieve the continuity of the annular channel in which the compressed air stream circulates directly above the sampling zone 10 of air.
  • this one is doubled internally with a thermal insulator 45.
  • This insulator contributes to reduce the transmissions by radiation of the interior envelope towards the external envelope 14-15-16 .
  • the compressor stator is assembled as follows: the friction band supports are slid into the grooves of each sector, then when all the sectors of an assembly are thus equipped, the sectors of the stator vanes are placed.
  • the compressor rotor is covered with the sectors previously prepared and the crown thus reconstituted is positioned by a tool assembly.
  • the ferrules constituting the outer envelope are then presented so that the tabs that they carry are angularly offset with respect to those of the sectors.
  • the upstream and downstream sections of the outer casing are engaged axially and the tab holes are brought back in front of the tab holes of the sectors forming the inner casing, the pins 27 are slid and locked in place by fixing the flanges d 'end 25.26.
  • the outer casing 14-15-16 is insulated by thermal insulation 45 on the one hand, and, on the other hand, ventilated by the circulation of air in the space between the two envelopes , and its temperature, so its variations dimen - sional can thereby be controlled by more or less hot air inlet in the ramps 13.
  • the distance between the stator segments to the outer casing can be controlled and thereby consequently, the clearance between the ends of the rotor blades and the friction strips 32 can be reduced to a minimum and remain almost constant during the transient operations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Rotary Pumps (AREA)
EP83402151A 1982-11-08 1983-11-07 Leitschaufelbefestigung eines Axialverdichters für die aktive Kontrolle des Spiels zwischen Rotor und Stator Expired EP0110757B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8218651 1982-11-08
FR8218651A FR2535795B1 (fr) 1982-11-08 1982-11-08 Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator

Publications (2)

Publication Number Publication Date
EP0110757A1 true EP0110757A1 (de) 1984-06-13
EP0110757B1 EP0110757B1 (de) 1986-09-03

Family

ID=9278972

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83402151A Expired EP0110757B1 (de) 1982-11-08 1983-11-07 Leitschaufelbefestigung eines Axialverdichters für die aktive Kontrolle des Spiels zwischen Rotor und Stator

Country Status (5)

Country Link
US (1) US4543039A (de)
EP (1) EP0110757B1 (de)
JP (1) JPS59113299A (de)
DE (1) DE3365894D1 (de)
FR (1) FR2535795B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2577282A1 (fr) * 1985-02-13 1986-08-14 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre rotor et stator
EP0475771A1 (de) * 1990-09-12 1992-03-18 United Technologies Corporation Kompressorgehäuse-Konstruktion
FR2692627A1 (fr) * 1992-05-29 1993-12-24 Gen Electric Ensemble de carters de compresseur, installation de prélèvement d'air pour ceux-ci et procédé de régulation de la distorsion de cet ensemble de carters.

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2591674B1 (fr) * 1985-12-18 1988-02-19 Snecma Dispositif de reglage des jeux radiaux entre rotor et stator d'un compresseur
FR2607198B1 (fr) * 1986-11-26 1990-05-04 Snecma Carter de compresseur adapte pour le pilotage actif de ses dilatations et son procede de fabrication
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
FR2640687B1 (fr) * 1988-12-21 1991-02-08 Snecma Carter de compresseur de turbomachine a pilotage de son diametre interne
GB2236809B (en) * 1989-09-22 1994-03-16 Rolls Royce Plc Improvements in or relating to gas turbine engines
FR2653171B1 (fr) * 1989-10-18 1991-12-27 Snecma Carter de compresseur de turbomachine muni d'un dispositif de pilotage de son diametre interne.
US5197281A (en) * 1990-04-03 1993-03-30 General Electric Company Interstage seal arrangement for airfoil stages of turbine engine counterrotating rotors
US5127794A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case with controlled thermal environment
US5299910A (en) * 1992-01-23 1994-04-05 General Electric Company Full-round compressor casing assembly in a gas turbine engine
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US5562408A (en) * 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud
US6553665B2 (en) * 2000-03-08 2003-04-29 General Electric Company Stator vane assembly for a turbine and method for forming the assembly
US6926496B2 (en) * 2002-12-31 2005-08-09 General Electric Company High temperature turbine nozzle for temperature reduction by optical reflection and process for manufacturing
US20070237629A1 (en) * 2006-04-05 2007-10-11 General Electric Company Gas turbine compressor casing flowpath rings
EP2075416B1 (de) * 2007-12-27 2011-05-18 Techspace Aero Verfahren zur Herstellung eines Teils einer Strömungsmaschine und so erhaltene Vorrichtung
RU2487251C2 (ru) * 2008-03-31 2013-07-10 Мицубиси Хеви Индастрис, Лтд. Теплоизолирующая конструкция для конструктивного элемента и спиральная конструкция
EP2236761A1 (de) * 2009-04-02 2010-10-06 Siemens Aktiengesellschaft Leitschaufelträger
JP4916560B2 (ja) * 2010-03-26 2012-04-11 川崎重工業株式会社 ガスタービンエンジンの圧縮機
US9366149B2 (en) 2012-09-21 2016-06-14 United Technologies Corporation Multi-stage high pressure compressor case
US20230399981A1 (en) * 2022-06-09 2023-12-14 Pratt & Whitney Canada Corp. Containment assembly for an aircraft engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2980396A (en) * 1959-06-29 1961-04-18 Gen Electric Stator construction for turbine engines
US3000552A (en) * 1957-05-28 1961-09-19 Gen Motors Corp Compressor vane mounting
FR2238838A1 (de) * 1973-07-27 1975-02-21 Westinghouse Electric Corp
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
FR2421279A1 (fr) * 1978-03-29 1979-10-26 Bbc Brown Boveri & Cie Machine a ecoulement avec refroidissement du dispositif support des ailettes directrices
FR2452600A1 (fr) * 1979-03-28 1980-10-24 United Technologies Corp Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter
FR2482661A1 (fr) * 1980-05-16 1981-11-20 United Technologies Corp Assemblage directeur d'ecoulement pour une turbine a gaz

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2917276A (en) * 1955-02-28 1959-12-15 Orenda Engines Ltd Segmented stator ring assembly
US2997275A (en) * 1959-03-23 1961-08-22 Westinghouse Electric Corp Stator structure for axial-flow fluid machine
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
JPS5035364U (de) * 1973-07-25 1975-04-15
US4083180A (en) * 1976-10-01 1978-04-11 Caterpillar Tractor Co. Gas turbine engine internal insulation
GB2019954B (en) * 1978-04-04 1982-08-04 Rolls Royce Turbomachine housing
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
US4431373A (en) * 1980-05-16 1984-02-14 United Technologies Corporation Flow directing assembly for a gas turbine engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000552A (en) * 1957-05-28 1961-09-19 Gen Motors Corp Compressor vane mounting
US2980396A (en) * 1959-06-29 1961-04-18 Gen Electric Stator construction for turbine engines
FR2238838A1 (de) * 1973-07-27 1975-02-21 Westinghouse Electric Corp
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
FR2421279A1 (fr) * 1978-03-29 1979-10-26 Bbc Brown Boveri & Cie Machine a ecoulement avec refroidissement du dispositif support des ailettes directrices
FR2452600A1 (fr) * 1979-03-28 1980-10-24 United Technologies Corp Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter
FR2482661A1 (fr) * 1980-05-16 1981-11-20 United Technologies Corp Assemblage directeur d'ecoulement pour une turbine a gaz

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2577282A1 (fr) * 1985-02-13 1986-08-14 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre rotor et stator
EP0192557A1 (de) * 1985-02-13 1986-08-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbinengehäuse mit einer Einrichtung, um den Abstand zwischen den Schaufelspitzen und dem Gehäuse einzustellen
EP0475771A1 (de) * 1990-09-12 1992-03-18 United Technologies Corporation Kompressorgehäuse-Konstruktion
TR27460A (tr) * 1990-09-12 1995-05-29 United Technologies Corp Gaz türbinli motora mahsus kompresör gövdesi yapimi.
FR2692627A1 (fr) * 1992-05-29 1993-12-24 Gen Electric Ensemble de carters de compresseur, installation de prélèvement d'air pour ceux-ci et procédé de régulation de la distorsion de cet ensemble de carters.
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly

Also Published As

Publication number Publication date
EP0110757B1 (de) 1986-09-03
JPH0158359B2 (de) 1989-12-11
FR2535795B1 (fr) 1987-04-10
FR2535795A1 (fr) 1984-05-11
JPS59113299A (ja) 1984-06-29
US4543039A (en) 1985-09-24
DE3365894D1 (en) 1986-10-09

Similar Documents

Publication Publication Date Title
EP0110757B1 (de) Leitschaufelbefestigung eines Axialverdichters für die aktive Kontrolle des Spiels zwischen Rotor und Stator
EP1975374B1 (de) Dichte Außenhülle eines Turbinenrads einer Strömungsmaschine
EP0397566B1 (de) Hitzebeständige Struktur für einen Nachbrenner oder für ein Gasturbinenzwischenstück
CA2739208C (fr) Etancheite entre une chambre de combustion et un distributeur de turbine dans une turbomachine
EP0387123B1 (de) Thermische Schutzauskleidung für das heisse Rohr eines Turboluftstrahltriebwerkes
EP3591178B1 (de) Abdichtungsmodul für turbomaschine
EP2634374B1 (de) Turbine und verfahren zur herstellung einer turbine
FR2558211A1 (fr) Turbine a gaz comprenant un joint d'etancheite statique a auto-alignement pour les aubes du stator de cette turbine
FR2641031A1 (de)
EP1059420B1 (de) Gehäuse für einen Hochdruckkompressor
FR2552159A1 (fr) Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
JP2003227353A (ja) ガスタービンにおける弦ヒンジシールのための補助シール
FR2656899A1 (fr) Assemblage a auto-refroidissement pour segments en aboutement dans un moteur a turbine a gaz, segment de turbine pour moteur a turbine a gaz, et procede de refroidissement de tels segments.
EP3597864A1 (de) Abdichtungseinheit für einen turbinenrotor eines triebwerks, und turbinerotor eines triebwerks, die eine solche einheit umfasst
FR2646466A1 (fr) Stator interne hp-mp unique de turbine a vapeur avec climatisation controlee
FR3004518A1 (fr) Chambre de combustion annulaire d'une turbomachine
JP2003227305A (ja) ガスタービンにおける弦ヒンジシールのための補助シール
FR3114841A1 (fr) Ensemble annulaire pour turbine de turbomachine
FR2690965A1 (fr) Dispositif pour assurer l'étanchéité de pièces, notamment dans des turbomachines.
WO2020148489A1 (fr) Ensemble pour une turbomachine
FR2955152A1 (fr) Turbomachine a circulation de flux d'air de purge amelioree
FR3061741A1 (fr) Turbine pour turbomachine
EP0716219A1 (de) Aus Segmenten aufgebauter Leitkranz für eine Turbomaschine
EP0651139B1 (de) Turbomaschine mit Einrichtungnen um das Schaufelspitzenspiel zwischen Rotor und Stator zu Regeln
FR3109402A1 (fr) Turbine pour une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19831117

AK Designated contracting states

Designated state(s): DE FR GB

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 3365894

Country of ref document: DE

Date of ref document: 19861009

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19921023

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19921027

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19930129

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19931107

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19931107

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19940729

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19940802

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST