MX373357B - Método para el montaje de una fase de estator de un motor de turbina de gas. - Google Patents

Método para el montaje de una fase de estator de un motor de turbina de gas.

Info

Publication number
MX373357B
MX373357B MX2016015771A MX2016015771A MX373357B MX 373357 B MX373357 B MX 373357B MX 2016015771 A MX2016015771 A MX 2016015771A MX 2016015771 A MX2016015771 A MX 2016015771A MX 373357 B MX373357 B MX 373357B
Authority
MX
Mexico
Prior art keywords
adjustment pin
central section
assembling
gas turbine
turbine engine
Prior art date
Application number
MX2016015771A
Other languages
English (en)
Other versions
MX2016015771A (es
Inventor
Jed Fentem
Paul Jenkinson
Original Assignee
Siemens Energy Global Gmbh & Co Kg
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 Siemens Energy Global Gmbh & Co Kg filed Critical Siemens Energy Global Gmbh & Co Kg
Publication of MX2016015771A publication Critical patent/MX2016015771A/es
Publication of MX373357B publication Critical patent/MX373357B/es

Links

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
    • 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
    • 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
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • 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
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Iron Core Of Rotating Electric Machines (AREA)
  • Manufacture Of Motors, Generators (AREA)

Abstract

La presente invención se refiere a un método para un montaje de una fase (10) de estator de un motor (12) de una turbina de gas, que comprende: insertar un pasador (30, 30a, 30b, 30c, 30d) de ajuste en el orificio (26) pasante, en donde el pasador (30, 30a, 30b, 30c, 30d) de ajuste comprende dos secciones (32, 32d; 34, 34d) extremas y una porción (36) intermedia que se extiende entre las secciones (32, 34) extremas y que tiene al menos un dispositivo (38) de accionamiento, insertar el al menos un segmento (18) de pared del segmento (14) de álabe en la ranura (24) de la sección (16) central, de manera que el hueco (20) se alinea circunferencialmente con el orificio (26) pasante de la sección (16) central, girar el pasador (30, 30a, 30b, 30c, 30d) de ajuste en su dirección (22) circunferencial, de manera que la sección (16) central se sitúe correctamente en la fase (10) de estator a través de la interacción del al menos un segmento (18) de pared con el al menos un dispositivo (38) de accionamiento del pasador (30, 30a, 30b, 30c, 30d) de ajuste, deformar una parte (40) deformable del pasador (30, 30a, 30b, 30c, 30d) de ajuste de manera que la parte (40) ahora deformada establece un ajuste de fuerza con al menos un segmento (42) de la estructura (44) correspondiente de la sección (16) central y por lo tanto bloquear el pasador (30, 30a, 30b, 30c, 30d) de ajuste y por tanto la sección (16) central en una posición fija en la fase (10) de estator.
MX2016015771A 2014-06-02 2015-05-22 Método para el montaje de una fase de estator de un motor de turbina de gas. MX373357B (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14170842.0A EP2952688A1 (en) 2014-06-02 2014-06-02 Method for assembling a stator stage of a gas turbine engine
PCT/EP2015/061452 WO2015185382A1 (en) 2014-06-02 2015-05-22 Method for assembling a stator stage of a gas turbine engine

Publications (2)

Publication Number Publication Date
MX2016015771A MX2016015771A (es) 2017-02-27
MX373357B true MX373357B (es) 2020-07-06

Family

ID=50884269

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2016015771A MX373357B (es) 2014-06-02 2015-05-22 Método para el montaje de una fase de estator de un motor de turbina de gas.

Country Status (6)

Country Link
US (1) US10436046B2 (es)
EP (2) EP2952688A1 (es)
CN (1) CN106414906B (es)
MX (1) MX373357B (es)
RU (1) RU2666836C2 (es)
WO (1) WO2015185382A1 (es)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201616969D0 (en) * 2016-10-06 2016-11-23 Rolls Royce Plc Stator assembly for a gas turbine engine
US10865650B2 (en) * 2017-09-12 2020-12-15 Raytheon Technologies Corporation Stator vane support with anti-rotation features
EP3870808B1 (en) * 2018-11-30 2022-08-17 Siemens Energy Global GmbH & Co. KG Mid-frame section of a gas turbine engine
IT201900007440A1 (it) * 2019-05-28 2020-11-28 Sabaf Spa Bruciatore a gas
US20230265862A1 (en) 2022-02-21 2023-08-24 General Electric Company Turbofan engine having angled inlet pre-swirl vanes
US11725526B1 (en) 2022-03-08 2023-08-15 General Electric Company Turbofan engine having nacelle with non-annular inlet
US12209557B1 (en) 2023-11-30 2025-01-28 General Electric Company Gas turbine engine with forward swept outlet guide vanes
US12385430B2 (en) 2023-11-30 2025-08-12 General Electric Company Gas turbine engine with forward swept outlet guide vanes
US12228037B1 (en) 2023-12-04 2025-02-18 General Electric Company Guide vane assembly with fixed and variable pitch inlet guide vanes
US12313021B1 (en) 2024-03-14 2025-05-27 General Electric Company Outer nacelle with inlet guide vanes and acoustic treatment

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
RU1077380C (ru) 1982-03-22 1995-06-19 Запорожское машиностроительное конструкторское бюро "Прогресс" Рабочее колесо турбомашины
US4890978A (en) 1988-10-19 1990-01-02 Westinghouse Electric Corp. Method and apparatus for vane segment support and alignment in combustion turbines
US5271714A (en) * 1992-07-09 1993-12-21 General Electric Company Turbine nozzle support arrangement
US5772401A (en) * 1995-10-13 1998-06-30 Dresser-Rand Company Diaphragm construction for turbomachinery
RU55443U1 (ru) 2006-03-24 2006-08-10 Государственное унитарное предприятие Тушинское машиностроительное конструкторское бюро "Союз" Штифтовое радиальное соединение вращающихся деталей (варианты)
EP2218873A1 (de) 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Rotorabschnitt für einen Rotor einer Turbomaschine, Laufschaufel für eine Turbomaschine und Blockierelement
US9133732B2 (en) 2010-05-27 2015-09-15 Siemens Energy, Inc. Anti-rotation pin retention system
US8992167B2 (en) * 2011-09-07 2015-03-31 General Electric Company Turbine casing assembly mounting pin
EP2594743A1 (en) * 2011-11-21 2013-05-22 Siemens Aktiengesellschaft Eccentric diaphragm adjusting pins for a gas turbine engine
DE102012219354A1 (de) * 2012-10-23 2014-04-24 Olympus Winter & Ibe Gmbh Aktuator für ein chirurgisches Instrument

Also Published As

Publication number Publication date
WO2015185382A1 (en) 2015-12-10
US10436046B2 (en) 2019-10-08
EP2952688A1 (en) 2015-12-09
RU2016147075A3 (es) 2018-07-10
EP3149285B1 (en) 2018-03-14
CN106414906B (zh) 2020-02-14
RU2016147075A (ru) 2018-07-10
CN106414906A (zh) 2017-02-15
RU2666836C2 (ru) 2018-09-12
US20170089209A1 (en) 2017-03-30
MX2016015771A (es) 2017-02-27
EP3149285A1 (en) 2017-04-05

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