CA2638812C - Secteur de distributeur de turbine - Google Patents

Secteur de distributeur de turbine Download PDF

Info

Publication number
CA2638812C
CA2638812C CA2638812A CA2638812A CA2638812C CA 2638812 C CA2638812 C CA 2638812C CA 2638812 A CA2638812 A CA 2638812A CA 2638812 A CA2638812 A CA 2638812A CA 2638812 C CA2638812 C CA 2638812C
Authority
CA
Canada
Prior art keywords
turbine
distributor
sector
air outlet
cavity
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.)
Active
Application number
CA2638812A
Other languages
English (en)
French (fr)
Other versions
CA2638812A1 (fr
Inventor
Jean-Luc Bacha
Olivier Jean Daniel Baumas
Lucie Lanciaux
Sophie Lavison
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of CA2638812A1 publication Critical patent/CA2638812A1/fr
Application granted granted Critical
Publication of CA2638812C publication Critical patent/CA2638812C/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/313—Layer deposition by physical vapour deposition
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
    • 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
    • F05D2260/95—Preventing corrosion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
CA2638812A 2007-08-08 2008-08-07 Secteur de distributeur de turbine Active CA2638812C (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0756998A FR2919897B1 (fr) 2007-08-08 2007-08-08 Secteur de distributeur de turbine
FR0756998 2007-08-08

Publications (2)

Publication Number Publication Date
CA2638812A1 CA2638812A1 (fr) 2009-02-08
CA2638812C true CA2638812C (fr) 2015-12-01

Family

ID=39099667

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2638812A Active CA2638812C (fr) 2007-08-08 2008-08-07 Secteur de distributeur de turbine

Country Status (8)

Country Link
US (1) US8192145B2 (https=)
EP (1) EP2025872B1 (https=)
JP (1) JP5442227B2 (https=)
CN (1) CN101363328B (https=)
CA (1) CA2638812C (https=)
ES (1) ES2394229T3 (https=)
FR (1) FR2919897B1 (https=)
RU (1) RU2476680C2 (https=)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2855557B1 (fr) * 2003-05-26 2007-03-02 Snecma Moteurs Volet de tuyere a duree de vie augmentee pour turbomoteurs d'avion.
US8851846B2 (en) * 2010-09-30 2014-10-07 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8628294B1 (en) * 2011-05-19 2014-01-14 Florida Turbine Technologies, Inc. Turbine stator vane with purge air channel
US9169782B2 (en) * 2012-01-04 2015-10-27 General Electric Company Turbine to operate at part-load
FR2989608B1 (fr) * 2012-04-24 2015-01-30 Snecma Procede d'usinage du bord de fuite d'une aube de turbomachine
WO2015057310A2 (en) * 2013-09-17 2015-04-23 United Technologies Corporation Platform cooling core for a gas turbine engine rotor blade
US11021967B2 (en) * 2017-04-03 2021-06-01 General Electric Company Turbine engine component with a core tie hole
FR3074521B1 (fr) 2017-12-06 2019-11-22 Safran Aircraft Engines Secteur de distributeur de turbine pour une turbomachine d'aeronef
EP3530882A1 (en) * 2018-02-26 2019-08-28 MTU Aero Engines GmbH Method of manufacturing a guide vane segment for a gas turbine and vane segment having a goating
CN113978240A (zh) * 2021-10-29 2022-01-28 宁波信泰机械有限公司 一种主动进气格栅挤出叶片连接结构
US12044143B2 (en) * 2021-12-17 2024-07-23 Rtx Corporation Gas turbine engine component with manifold cavity and metering inlet orifices

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0693801A (ja) * 1992-09-17 1994-04-05 Hitachi Ltd ガスタービン翼
RU2088764C1 (ru) * 1993-12-02 1997-08-27 Яков Петрович Гохштейн Турбинная лопатка
RU2122123C1 (ru) * 1994-12-27 1998-11-20 Открытое акционерное общество Самарский научно-технический комплекс им.Н.Д.Кузнецова Охлаждаемая сопловая лопатка с вихревой матрицей
US6589668B1 (en) * 2000-06-21 2003-07-08 Howmet Research Corporation Graded platinum diffusion aluminide coating
EP1191189A1 (de) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gasturbinenschaufel
ITTO20010704A1 (it) * 2001-07-18 2003-01-18 Fiatavio Spa Paletta a doppia parete per una turbina, particolarmente per applicazioni aeronautiche.
US6561757B2 (en) * 2001-08-03 2003-05-13 General Electric Company Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention
FR2830874B1 (fr) * 2001-10-16 2004-01-16 Snecma Moteurs Procede de protection par aluminisation de pieces metalliques de turbomachines munies de trous et cavites
DE60217071T2 (de) * 2002-05-09 2007-07-12 General Electric Co. Kühlkonfiguration für ein Turbomaschinenschaufelblatt
US6929445B2 (en) * 2003-10-22 2005-08-16 General Electric Company Split flow turbine nozzle
RU2267616C1 (ru) * 2004-05-21 2006-01-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Охлаждаемая лопатка турбины
US7168921B2 (en) * 2004-11-18 2007-01-30 General Electric Company Cooling system for an airfoil
FR2899271B1 (fr) * 2006-03-29 2008-05-30 Snecma Sa Ensemble d'une aube et d'une chemise de refroidissement, distributeur de turbomachine comportant l'ensemble, turbomachine, procede de montage et de reparation de l'ensemble

Also Published As

Publication number Publication date
EP2025872B1 (fr) 2012-09-05
EP2025872A2 (fr) 2009-02-18
FR2919897A1 (fr) 2009-02-13
CN101363328A (zh) 2009-02-11
US20090041586A1 (en) 2009-02-12
EP2025872A3 (fr) 2011-04-20
CN101363328B (zh) 2013-04-17
CA2638812A1 (fr) 2009-02-08
ES2394229T3 (es) 2013-01-23
FR2919897B1 (fr) 2014-08-22
JP5442227B2 (ja) 2014-03-12
RU2476680C2 (ru) 2013-02-27
RU2008132630A (ru) 2010-02-20
JP2009041566A (ja) 2009-02-26
US8192145B2 (en) 2012-06-05

Similar Documents

Publication Publication Date Title
CA2638812C (fr) Secteur de distributeur de turbine
EP1840331B1 (fr) Distributeur de turbomachine
CA2254259C (fr) Aube de distributeur de turbine refroidie
EP3420198B1 (fr) Redresseur pour compresseur de turbomachine d'aeronef, comprenant des orifices de prelevement d'air de forme etiree selon la direction circonferentielle
CA2652679A1 (fr) Aubes pour roue a aubes de turbomachine avec rainure pour le refroidissement
WO2013001240A1 (fr) Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
EP4405569B1 (fr) Carter d'injection d'air de refroidissement pour turbine de turbomachine
FR2981979A1 (fr) Roue de turbine pour une turbomachine
EP4441348A1 (fr) Turbomachine axiale triple-flux avec échangeur de chaleur divergeant dans le troisième flux
WO2021023945A1 (fr) Anneau pour une turbine de turbomachine ou de turbomoteur
EP3942158B1 (fr) Aube de turbomachine équipée d'un circuit de refroidissement optimisé
WO2020239732A1 (fr) Joint d'étanchéité dynamique pour turbomachine comprenant une pièce abradable multicouche
FR3029242A1 (fr) Aube de turbomachine, comprenant des cloisons entrecroisees pour la circulation d'air en direction du bord de fuite
FR2906846A1 (fr) Canal de transition entre deux etages de turbine
CA2932004C (fr) Rotor a aubes
FR3028494A1 (fr) Pale de turbomachine, comprenant des pontets s'etendant depuis la paroi d'intrados jusqu'a la paroi d'extrados
EP4146913B1 (fr) Distributeur en cmc amélioré pour turbine de turbomachine
FR3092865A1 (fr) Disque de rotor avec arret axial des aubes, ensemble d’un disque et d’un anneau et turbomachine
EP3847339B1 (fr) Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine
FR3079848A1 (fr) Procede de depot d'un materiau anti-usure sur un element aubage pour une turbomachine d'aeronef
EP4111036B1 (fr) Pale de distributeur pour turbomachine, distributeur haute ou basse pression pour turbomachine, turbomachine et procédé de fabrication d'une pale d'un distributeur pour turbomachine
FR3095234A1 (fr) Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
FR3158534A1 (fr) Ensemble d’étanchéité, turbine et procédé de montage associés
FR3158533A1 (fr) Ensemble d’étanchéité, turbine et procédé associés
FR3161921A1 (fr) Aubage metallique pour une turbomachine d’aeronef et son procede de fabrication

Legal Events

Date Code Title Description
EEER Examination request

Effective date: 20130621

MPN Maintenance fee for patent paid

Free format text: FEE DESCRIPTION TEXT: MF (PATENT, 16TH ANNIV.) - STANDARD

Year of fee payment: 16

U00 Fee paid

Free format text: ST27 STATUS EVENT CODE: A-4-4-U10-U00-U101 (AS PROVIDED BY THE NATIONAL OFFICE); EVENT TEXT: MAINTENANCE REQUEST RECEIVED

Effective date: 20240726

U11 Full renewal or maintenance fee paid

Free format text: ST27 STATUS EVENT CODE: A-4-4-U10-U11-U102 (AS PROVIDED BY THE NATIONAL OFFICE); EVENT TEXT: MAINTENANCE FEE PAYMENT DETERMINED COMPLIANT

Effective date: 20241217

Free format text: ST27 STATUS EVENT CODE: A-4-4-U10-U11-U102 (AS PROVIDED BY THE NATIONAL OFFICE); EVENT TEXT: MAINTENANCE FEE PAYMENT PAID IN FULL

Effective date: 20241217

MPN Maintenance fee for patent paid

Free format text: FEE DESCRIPTION TEXT: MF (PATENT, 17TH ANNIV.) - STANDARD

Year of fee payment: 17

U00 Fee paid

Free format text: ST27 STATUS EVENT CODE: A-4-4-U10-U00-U101 (AS PROVIDED BY THE NATIONAL OFFICE); EVENT TEXT: MAINTENANCE REQUEST RECEIVED

Effective date: 20250724

U11 Full renewal or maintenance fee paid

Free format text: ST27 STATUS EVENT CODE: A-4-4-U10-U11-U102 (AS PROVIDED BY THE NATIONAL OFFICE); EVENT TEXT: MAINTENANCE FEE PAYMENT PAID IN FULL

Effective date: 20250724