EP1462616B1 - Ensemble de fixation axiale et radiale d'une aube statorique dans un boîtier d'un moteur à turbine - Google Patents

Ensemble de fixation axiale et radiale d'une aube statorique dans un boîtier d'un moteur à turbine Download PDF

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Publication number
EP1462616B1
EP1462616B1 EP20040002392 EP04002392A EP1462616B1 EP 1462616 B1 EP1462616 B1 EP 1462616B1 EP 20040002392 EP20040002392 EP 20040002392 EP 04002392 A EP04002392 A EP 04002392A EP 1462616 B1 EP1462616 B1 EP 1462616B1
Authority
EP
European Patent Office
Prior art keywords
housing
turbine engine
engages
shaped
assembly
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 - Fee Related
Application number
EP20040002392
Other languages
German (de)
English (en)
Other versions
EP1462616A2 (fr
EP1462616A3 (fr
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
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 MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1462616A2 publication Critical patent/EP1462616A2/fr
Publication of EP1462616A3 publication Critical patent/EP1462616A3/fr
Application granted granted Critical
Publication of EP1462616B1 publication Critical patent/EP1462616B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine with a locking ring which engages in a corresponding radial groove in the facing wall of the housing and is secured by a locking element against radial deflection.
  • Vane-Kluster designated Leitschaufelbau phenomenon insert as a unit from behind into the housing of a turbine engine and set in the retracted position by means of piston rings similar retaining rings which are inserted in this provided with these corresponding grooves in the retracted position.
  • the retaining rings themselves are locked by a subsequent component, usually by a designated as a liner turbine shroud segment, which prevents the radial sliding out of the retaining ring from the associated groove.
  • a liner turbine shroud segment for such a backup by the subsequent turbine shroud segment this must be designed such that it can overlap by means of a hook-shaped trailing edge of the guide vane assembly.
  • U.S. Patent 5,848,854 discloses an arrangement for axially and radially defining a stator vane assembly in the housing of a turbine engine having a piston annular circlip which engages a corresponding radial groove in the facing wall of the housing and by means of a locking member is secured against radial deflection, wherein the retaining ring is formed in cross-section L-shaped, engages the first leg in the radial groove of the wall of the housing and the second leg is held by means of a U-shaped bracket in its backup position.
  • This object is achieved by using an L-shaped retaining ring according to the invention that the second, short leg engages behind a hook-shaped projection on the respective blade head of the vanes of the vane group, and that the clip is attached to a subsequent turbine shroud segment.
  • the inventive solution requires neither axial webs to accommodate the usual safety pins nor a large length to accommodate the thermally induced axial tolerances and thus avoids relatively high axial space requirements.
  • a groove 18 for receiving the retaining ring 15 is provided in the housing 14, to which a flange-like extension 19 of the blade head 11 is applied.
  • the extension has an opening 20 into which engages a locking pin 23 secured in a corresponding flange-like extension 21 of the housing 14 for the purpose of preventing the radial sliding out of the guide blade assembly with bearing play.
  • the radial locking of the retaining ring takes place by means of a cam 25 which bears against the inner circumferential surface of the retaining ring and is fastened to the facing end face of the downstream assembly 26 of the turbine engine designated as "liner".
  • the upstream end of the blade head 11 engages with an extension 27 in a recess 28 associated therewith of the housing 14.
  • a locking pin there is provided a retaining ring 15 under cross U-shaped bracket 23 which is rigidly secured to the facing end 24 of the downstream downstream assembly 26 of the turbine engine, so the "liner" and with this in a recess 29 of the housing 14 engages.
  • the free leg 16 of the U-shaped bracket 23 engages under a hook-shaped extension 17 on the head part 11 of the guide vane 10th
  • a locking ring is provided, which is designated by the reference numeral 30 and in contrast to the known locking rings has an L-shaped cross-section.
  • the locking ring 30 engages with its long leg 32 in the groove 14 provided in the housing 14.
  • the short leg 33 engages around a correspondingly shaped short hook-shaped extension 34 on the blade head 11 of the respective associated guide blade 10 of the stator blade assembly to be held and forms with its end face 35, the contact surface for the retaining ring 30th
  • a U-shaped bracket 36 is provided, which is attached to the front end 24 of the subsequent assembly 26 of the turbine engine and engages with its free leg 38 on the short leg 33 of the locking ring 30 adjacent this engages.
  • the U-shaped bracket 36 is, as in connection with Fig. 2 described, with the facing end 24 of the subsequent downstream referred to as a liner Buffle 26 firmly connected and engages in the recess 29 in the housing 14 a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (3)

  1. Dispositif pour la fixation axiale et radiale d'un agrégat d'aubes directrices dans le carter (14) d'un mécanisme d'entraînement de turbine, comportant une bague de fixation (30) en forme de segment de piston, qui s'engage dans une rainure radiale (18) correspondante dans la paroi opposée du carter (14) et dont un jeu radial est empêché par un élément de verrouillage (attache 36), dans lequel la bague de fixation (30) est prévue avec une section sensiblement en forme de L, sa première branche (32) s'engageant dans la rainure radiale (18) de la paroi du carter (14) et sa deuxième branche (33) étant maintenue dans sa position de fixation au moyen d'une attache en forme de U (36), caractérisé en ce que la deuxième branche (33) plus courte, retient par le dessous une saillie en forme de crochet (34) sur le bout d'aube (11) de chaque aube directrice (10) de l'agrégat d'aubes directrices, et en ce que l'attache (36) est fixée sur un segment suivant du bandage de roue de turbine (26).
  2. Dispositif selon la revendication 1, caractérisé en ce que la face frontale de la saillie en forme de crochet (34) forme la surface de butée (35) pour la bague de fixation (30), laquelle définit la position axiale de l'agrégat d'aubes directrices.
  3. Dispositif selon la revendication 1, caractérisé en ce que la branche (39) de l'attache en forme de U (36) qui est reliée à l'extrémité frontale de l'agrégat suivant (liner 26) s'engage dans un évidement (29) du carter (14) du mécanisme d'entraînement de turbine.
EP20040002392 2003-03-22 2004-02-04 Ensemble de fixation axiale et radiale d'une aube statorique dans un boîtier d'un moteur à turbine Expired - Fee Related EP1462616B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10312956 2003-03-22
DE2003112956 DE10312956B4 (de) 2003-03-22 2003-03-22 Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes

Publications (3)

Publication Number Publication Date
EP1462616A2 EP1462616A2 (fr) 2004-09-29
EP1462616A3 EP1462616A3 (fr) 2009-09-30
EP1462616B1 true EP1462616B1 (fr) 2011-06-15

Family

ID=32798061

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20040002392 Expired - Fee Related EP1462616B1 (fr) 2003-03-22 2004-02-04 Ensemble de fixation axiale et radiale d'une aube statorique dans un boîtier d'un moteur à turbine

Country Status (2)

Country Link
EP (1) EP1462616B1 (fr)
DE (1) DE10312956B4 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1843009A1 (fr) * 2006-04-06 2007-10-10 Siemens Aktiengesellschaft Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine
FR2923526B1 (fr) * 2007-11-13 2013-12-13 Snecma Etage de turbine ou de compresseur de turbomachine
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
FR2985792B1 (fr) * 2012-01-18 2014-02-07 Snecma Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
EP2787178B1 (fr) 2013-04-03 2016-03-02 MTU Aero Engines AG Ensemble d'aube directrice
DE102014209057A1 (de) * 2014-05-14 2015-11-19 MTU Aero Engines AG Gasturbinengehäuseanordnung
GB2533544B (en) 2014-09-26 2017-02-15 Rolls Royce Plc A shroud segment retainer
DE102016203567A1 (de) 2016-03-04 2017-09-07 Siemens Aktiengesellschaft Strömungsmaschine mit mehreren Leitschaufelstufen und Verfahren zur teilweisen Demontage einer solchen Strömungsmaschine
FR3083820B1 (fr) * 2018-07-11 2020-10-02 Safran Aircraft Engines Dispositif de maintien ameliore pour distributeur de turbomachine
DE102020201448A1 (de) 2020-02-06 2021-08-12 Siemens Aktiengesellschaft Additiv hergestellte Turbinenschaufel mit Verdrehsicherung und Justageverfahren
CN112177689A (zh) * 2020-09-29 2021-01-05 中国航发湖南动力机械研究所 发动机的涡轮导向器定位结构和发动机

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5669757A (en) * 1995-11-30 1997-09-23 General Electric Company Turbine nozzle retainer assembly
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6537022B1 (en) * 2001-10-05 2003-03-25 General Electric Company Nozzle lock for gas turbine engines
GB0318609D0 (en) * 2003-08-08 2003-09-10 Rolls Royce Plc An arrangement for mounting a non-rotating component

Also Published As

Publication number Publication date
DE10312956B4 (de) 2011-08-11
EP1462616A2 (fr) 2004-09-29
EP1462616A3 (fr) 2009-09-30
DE10312956A1 (de) 2004-09-30

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