EP0356305A1 - An einem Turbinengehäuse befestigter Statorring - Google Patents

An einem Turbinengehäuse befestigter Statorring Download PDF

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Publication number
EP0356305A1
EP0356305A1 EP89402256A EP89402256A EP0356305A1 EP 0356305 A1 EP0356305 A1 EP 0356305A1 EP 89402256 A EP89402256 A EP 89402256A EP 89402256 A EP89402256 A EP 89402256A EP 0356305 A1 EP0356305 A1 EP 0356305A1
Authority
EP
European Patent Office
Prior art keywords
turbine
ring
segment
casing
stator ring
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
EP89402256A
Other languages
English (en)
French (fr)
Other versions
EP0356305B1 (de
Inventor
François Emile Georges Crozet
Jean Luc Soupizon
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 EP0356305A1 publication Critical patent/EP0356305A1/de
Application granted granted Critical
Publication of EP0356305B1 publication Critical patent/EP0356305B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a turbine stator ring, in particular for a low-pressure turbine of a turbofan engine, associated with a support for connection to the turbine casing.
  • FR-A-2 407 342 and FR-A-2 407 343 thus illustrate an example of such an assembly in which the support of a turbine ring is constituted, on its upstream edge, by a segmented ferrule fixed by fasteners on an external envelope and, on its downstream edge, by a radial flange of said envelope and a flange of the neighboring distributor stage.
  • FIG. 1 also represents a known example of embodiment of the front part, seen in longitudinal section of the low pressure turbine of a known turbofan engine.
  • a turbine ring 2 is mounted on an annular support 3 which is bolted to the upstream flange 4 of the turbine casing 5.
  • a layer 6 of insulating material can be interposed between the ring 2 and its support 3.
  • the invention aims to improve the thermal insulation of the casing and of the ring support itself while reducing the mass, which is a particularly important selection criterion for aeronautical applications.
  • One of the aims is also to make the ring support independent of the turbine casing.
  • a turbine stator ring associated with a ring support characterized in that said ring consists of a sheet metal ferrule formed of a plurality of sectors each comprising two segments, a first segment, generally oriented in a longitudinal direction relative to the turbine, carrying an abradable type seal and the downstream edge of which bears on a spoiler of the blades of the neighboring distributor stage and a second segment, generally oriented in a radial direction relative to the turbine, secured by its radially internal end with the upstream end of said first segment and cooperating by its radially external end with said ring support which has an S-shaped section and whose radially outer groove cooperates with an annular hook carried by the turbine housing.
  • a turbine stator ring 10 is constituted by a plurality of sectors, for example eighteen in number in the example shown.
  • Each sector comprises two sheet metal shell segments, a first segment 10a generally oriented in a longitudinal direction relative to the turbine and a second segment 10b, generally oriented in a radial direction and whose radially internal end 10c is secured, for example by welding, with the upstream end 10d of the first segment 10a.
  • the first segments 10a carry, on their internal face and in line with the ends of the moving blades 11 of the first stage of the turbine rotor, a seal 12 of abradable type.
  • the downstream edge 10e of the first segments 10a bears on the upstream spoilers 13a of the fixed vanes 13 of the turbine distributor.
  • the turbine casing 14 carries at its upstream end an annular hook 14a which cooperates with the radially outer groove 15a of a ring support 15 which has an S-shaped section.
  • This support 15 is of annular shape having a slot which gives said audit support 15 freedom of thermal expansion.
  • the end radially outer second segments 10b has a rim 10f which cooperates with the radially inner groove 15b of the support 15. The turbine ring 10 is thus suspended between the support 15 and the spoilers of blades 13.
  • Between the turbine casing 14 and the turbine ring 10 is provided with a space allowing to have on the external face of the first segments 10a a first layer 16 of thermally insulating material which is covered with a sheet in the shape of a ferrule 17, itself carrying a second layer 18 of thermally insulating material.
  • the front part of the turbine comprising the stator ring according to the invention can be mounted in the manner described below.
  • the ring support 15 is mounted on the turbine casing 14; the second layer 18 of thermal insulator is placed in the casing; the covering ring 17 is positioned then the first layer 16 of thermal insulation is put in place.
  • the downstream edge 10e of the turbine ring sectors 10 is then tilted towards the axis of the turbojet engine, then said sectors are engaged on the upstream side in the internal groove 15b of the support 15 and moved axially until they press at the bottom of the groove 15b of the support 15 and the downstream edge 10e is tilted outwards.
  • Said downstream edge 10e of the first segments 10a further carries an anti-rotation stud 19 which is then used to position them angularly, said studs 19 being held by a tool.
  • the first movable stage 11 of the rotor is then mounted, then the distributor 13 which comprises, on the upstream side of the external ring, a housing 20 cooperating with the pins 19 by which the turbine ring 10 is thus prevented from rotating.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP89402256A 1988-08-18 1989-08-10 An einem Turbinengehäuse befestigter Statorring Expired - Lifetime EP0356305B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8810977A FR2635562B1 (fr) 1988-08-18 1988-08-18 Anneau de stator de turbine associe a un support de liaison au carter de turbine
FR8810977 1988-08-18

Publications (2)

Publication Number Publication Date
EP0356305A1 true EP0356305A1 (de) 1990-02-28
EP0356305B1 EP0356305B1 (de) 1994-01-12

Family

ID=9369384

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89402256A Expired - Lifetime EP0356305B1 (de) 1988-08-18 1989-08-10 An einem Turbinengehäuse befestigter Statorring

Country Status (5)

Country Link
US (1) US4925365A (de)
EP (1) EP0356305B1 (de)
JP (1) JPH0694801B2 (de)
DE (1) DE68912241T2 (de)
FR (1) FR2635562B1 (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2660371A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Arrangement d'etancheite inter-etage pour des etages d'aubages de rotors tournant a contrarotation dans un moteur a turbine.
EP0478494A1 (de) * 1990-09-25 1992-04-01 United Technologies Corporation Verfahren und Vorrichtung für die Statoranordnung einer rotierenden Maschine
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
EP0844369A1 (de) * 1996-11-23 1998-05-27 ROLLS-ROYCE plc Zusammenbau eines Schaufelrotors und dessen Gehäuses
EP1045115A1 (de) * 1999-04-12 2000-10-18 Asea Brown Boveri AG Hitzeschild für eine Gasturbine
FR2899273A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
EP2236754A3 (de) * 2009-03-16 2014-01-08 Hitachi Ltd. Laufschaufel einer Dampfturbine und zugehörige Dampfturbine
EP2696037A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Abdichtung des Strömungskanals einer Strömungsmaschine
EP2725203A1 (de) * 2012-10-23 2014-04-30 MTU Aero Engines GmbH Kühlluftführung in einer Gehäusestruktur einer Strömungsmaschine
WO2016030632A1 (fr) * 2014-08-28 2016-03-03 Snecma Procede de fabrication de supports d'anneaux d'organe de turbomachine
FR3093541A1 (fr) * 2019-03-08 2020-09-11 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor

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GB2226365B (en) * 1988-12-22 1993-03-10 Rolls Royce Plc Turbomachine clearance control
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
DE4331060C1 (de) * 1993-09-13 1994-06-30 Gruenzweig & Hartmann Montage Wärmedämmanordnung
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
FR2786222B1 (fr) * 1998-11-19 2000-12-29 Snecma Dispositif d'etancheite a lamelle
JP2002129901A (ja) * 2000-10-30 2002-05-09 Ishikawajima Harima Heavy Ind Co Ltd チップシュラウド構造
DE10122464C1 (de) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring
FR2829176B1 (fr) * 2001-08-30 2005-06-24 Snecma Moteurs Carter de stator de turbomachine
US6814541B2 (en) * 2002-10-07 2004-11-09 General Electric Company Jet aircraft fan case containment design
WO2004113771A2 (en) * 2003-06-20 2004-12-29 Elliott Company Hybrid abradable labyrinth damper seal
GB2407343B (en) * 2003-10-22 2006-04-19 Rolls Royce Plc An acoustic liner for a gas turbine engine casing
FR2867224B1 (fr) * 2004-03-04 2006-05-19 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine
DE102005011742A1 (de) * 2005-03-11 2006-09-14 Johnson Controls Gmbh Schaumteil für ein Fahrzeug, insbesondere für einen Sitz und insbesondere mit Sensormittel
US7665960B2 (en) 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
US8429816B2 (en) * 2008-09-12 2013-04-30 General Electric Company Stator ring configuration
FR2952965B1 (fr) * 2009-11-25 2012-03-09 Snecma Isolation d'un rebord circonferentiel d'un carter externe de turbomachine vis-a-vis d'un secteur d'anneau correspondant
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
FR2960591B1 (fr) * 2010-06-01 2012-08-24 Snecma Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
EP2696036A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Klemmring für eine Strömungsmaschine
EP2719869A1 (de) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Axiale Abdichtung in einer Gehäusestruktur für eine Strömungsmaschine
US9803491B2 (en) * 2012-12-31 2017-10-31 United Technologies Corporation Blade outer air seal having shiplap structure
DE102013205883B4 (de) * 2013-04-03 2020-04-23 MTU Aero Engines AG Anordnung aus Leitschaufelsegmenten und Verfahren zur Herstellung einer derartigen Anordnung
US20160040547A1 (en) * 2013-04-12 2016-02-11 United Technologies Corporation Blade outer air seal with secondary air sealing
RU2534669C1 (ru) * 2013-11-25 2014-12-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор турбины низкого давления
WO2015084550A1 (en) * 2013-12-03 2015-06-11 United Technologies Corporation Heat shields for air seals
JP6233578B2 (ja) * 2013-12-05 2017-11-22 株式会社Ihi タービン
US10253645B2 (en) 2013-12-12 2019-04-09 United Technologies Corporation Blade outer air seal with secondary air sealing
US10145308B2 (en) 2014-02-10 2018-12-04 United Technologies Corporation Gas turbine engine ring seal
EP3153671A1 (de) 2015-10-08 2017-04-12 MTU Aero Engines GmbH Schutzvorrichtung für eine strömungsmaschine
EP3179053B1 (de) 2015-12-07 2019-04-03 MTU Aero Engines GmbH Gehäusestruktur einer strömungsmaschine mit hitzeschutzschild
FR3058755B1 (fr) * 2016-11-15 2020-09-25 Safran Aircraft Engines Turbine pour turbomachine
DE102016222720A1 (de) * 2016-11-18 2018-05-24 MTU Aero Engines AG Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine
FR3065483B1 (fr) * 2017-04-24 2020-08-07 Safran Aircraft Engines Dispositif d'etancheite entre rotor et stator de turbomachine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
EP3412871B1 (de) 2017-06-09 2021-04-28 Ge Avio S.r.l. Dichtung für gasturbinenleitschaufelanordnung
JP7061497B2 (ja) * 2018-03-30 2022-04-28 三菱重工航空エンジン株式会社 航空機用ガスタービン
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
DE102018210598A1 (de) 2018-06-28 2020-01-02 MTU Aero Engines AG Gehäusestruktur für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Kühlen eines Gehäuseabschnitts einer Gehäusestruktur einer Strömungsmaschine
FR3086323B1 (fr) * 2018-09-24 2020-12-11 Safran Aircraft Engines Carter interne de turmomachine a isolation thermique amelioree
JP2021110291A (ja) * 2020-01-10 2021-08-02 三菱重工業株式会社 動翼、及び軸流回転機械
CA3182646A1 (en) * 2021-12-24 2023-06-24 Itp Next Generation Turbines, S.L. A turbine arrangement including a turbine outlet stator vane arrangement
US11933226B2 (en) * 2022-05-13 2024-03-19 Rtx Corporation Heat shield and method of installing the same

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GB839915A (en) * 1958-01-20 1960-06-29 Rolls Royce Labyrinth seals
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
EP0017546A1 (de) * 1979-03-30 1980-10-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Auswechselbarer Träger für die Anstreif-Dichtungsschicht im Gehäuse eines Bläsertriebwerkes
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
GB2151709A (en) * 1983-12-19 1985-07-24 Gen Electric Sheet metal panel
US4648792A (en) * 1985-04-30 1987-03-10 United Technologies Corporation Stator vane support assembly

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GB839915A (en) * 1958-01-20 1960-06-29 Rolls Royce Labyrinth seals
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
EP0017546A1 (de) * 1979-03-30 1980-10-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Auswechselbarer Träger für die Anstreif-Dichtungsschicht im Gehäuse eines Bläsertriebwerkes
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
GB2151709A (en) * 1983-12-19 1985-07-24 Gen Electric Sheet metal panel
US4648792A (en) * 1985-04-30 1987-03-10 United Technologies Corporation Stator vane support assembly

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2660371A1 (fr) * 1990-04-03 1991-10-04 Gen Electric Arrangement d'etancheite inter-etage pour des etages d'aubages de rotors tournant a contrarotation dans un moteur a turbine.
EP0478494A1 (de) * 1990-09-25 1992-04-01 United Technologies Corporation Verfahren und Vorrichtung für die Statoranordnung einer rotierenden Maschine
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5281089A (en) * 1990-09-25 1994-01-25 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
EP0844369A1 (de) * 1996-11-23 1998-05-27 ROLLS-ROYCE plc Zusammenbau eines Schaufelrotors und dessen Gehäuses
US6062813A (en) * 1996-11-23 2000-05-16 Rolls-Royce Plc Bladed rotor and surround assembly
EP1045115A1 (de) * 1999-04-12 2000-10-18 Asea Brown Boveri AG Hitzeschild für eine Gasturbine
FR2899273A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
EP2236754A3 (de) * 2009-03-16 2014-01-08 Hitachi Ltd. Laufschaufel einer Dampfturbine und zugehörige Dampfturbine
US9512734B2 (en) 2012-08-09 2016-12-06 MTU Aero Engines AG Sealing of the flow channel of a turbomachine
EP2696037A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Abdichtung des Strömungskanals einer Strömungsmaschine
EP2725203A1 (de) * 2012-10-23 2014-04-30 MTU Aero Engines GmbH Kühlluftführung in einer Gehäusestruktur einer Strömungsmaschine
US9488069B2 (en) 2012-10-23 2016-11-08 MTU Aero Engines AG Cooling-air guidance in a housing structure of a turbomachine
FR3025124A1 (fr) * 2014-08-28 2016-03-04 Snecma Procede de fabrication de supports d'anneaux d'organe de turbomachine
WO2016030632A1 (fr) * 2014-08-28 2016-03-03 Snecma Procede de fabrication de supports d'anneaux d'organe de turbomachine
CN106794506A (zh) * 2014-08-28 2017-05-31 赛峰航空器发动机 制造涡轮机构件环支撑件的方法
CN106794506B (zh) * 2014-08-28 2019-01-08 赛峰航空器发动机 制造涡轮机构件环支撑件的方法
US10773296B2 (en) 2014-08-28 2020-09-15 Safran Aircraft Engines Method for manufacturing turbomachine member ring supports
FR3093541A1 (fr) * 2019-03-08 2020-09-11 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor
WO2020183074A3 (fr) * 2019-03-08 2020-11-05 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor
CN113544361A (zh) * 2019-03-08 2021-10-22 赛峰飞机发动机公司 用于双旋翼飞机的燃气涡轮

Also Published As

Publication number Publication date
FR2635562B1 (fr) 1993-12-24
EP0356305B1 (de) 1994-01-12
DE68912241D1 (de) 1994-02-24
US4925365A (en) 1990-05-15
JPH0694801B2 (ja) 1994-11-24
DE68912241T2 (de) 1994-05-11
JPH02104903A (ja) 1990-04-17
FR2635562A1 (fr) 1990-02-23

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