FR3117532B1 - Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes - Google Patents

Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes Download PDF

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Publication number
FR3117532B1
FR3117532B1 FR2012975A FR2012975A FR3117532B1 FR 3117532 B1 FR3117532 B1 FR 3117532B1 FR 2012975 A FR2012975 A FR 2012975A FR 2012975 A FR2012975 A FR 2012975A FR 3117532 B1 FR3117532 B1 FR 3117532B1
Authority
FR
France
Prior art keywords
inter
turbine blade
primary flow
ejection channel
channel towards
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
FR2012975A
Other languages
English (en)
Other versions
FR3117532A1 (fr
Inventor
Jean Charles Marie Coussirou
Thomas Langevin
Benoit Guillaume Silet
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2012975A priority Critical patent/FR3117532B1/fr
Priority to CN202180083048.1A priority patent/CN116568909A/zh
Priority to US18/256,317 priority patent/US20240035391A1/en
Priority to EP21839604.2A priority patent/EP4259903A1/fr
Priority to PCT/FR2021/052170 priority patent/WO2022123148A1/fr
Publication of FR3117532A1 publication Critical patent/FR3117532A1/fr
Application granted granted Critical
Publication of FR3117532B1 publication Critical patent/FR3117532B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/122—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 with erodable or abradable material
    • 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
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • 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
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention se rapporte à une aube (60) et un élément d’étanchéité (59) formant un ensemble pour turbine de turbomachine. L’aube (60) comprend une pale (61) et une plateforme (62) à laquelle est relié l’élément d’étanchéité (59). Un canal interne (80) traverse la plateforme (62) de manière à prélever du fluide circulant dans un conduit primaire (21A) qu’elle délimite et à injecter le fluide ainsi prélevé dans une cavité inter-léchettes (50A, 51A) délimitée par l’élément d’étanchéité (59). L’invention permet de réduire la formation et l’intensité d’écoulements secondaires tout en améliorant l’étanchéité. Figure pour l’abrégé : Fig. 5
FR2012975A 2020-12-10 2020-12-10 Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes Active FR3117532B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2012975A FR3117532B1 (fr) 2020-12-10 2020-12-10 Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes
CN202180083048.1A CN116568909A (zh) 2020-12-10 2021-12-01 用于飞行器涡轮机的设置有用于向唇缘间空腔喷射主流的通道的涡轮轮叶
US18/256,317 US20240035391A1 (en) 2020-12-10 2021-12-01 Turbine blade for an aircraft turbomachine, provided with a channel for ejecting a primary flow towards an inter-lip cavity
EP21839604.2A EP4259903A1 (fr) 2020-12-10 2021-12-01 Aube de turbine pour turbomachine d'aéronef, pourvue d'un canal d'éjection de flux primaire vers une cavité inter-léchettes
PCT/FR2021/052170 WO2022123148A1 (fr) 2020-12-10 2021-12-01 Aube de turbine pour turbomachine d'aéronef, pourvue d'un canal d'éjection de flux primaire vers une cavité inter-léchettes

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2012975A FR3117532B1 (fr) 2020-12-10 2020-12-10 Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes
FR2012975 2020-12-10

Publications (2)

Publication Number Publication Date
FR3117532A1 FR3117532A1 (fr) 2022-06-17
FR3117532B1 true FR3117532B1 (fr) 2024-05-24

Family

ID=74758985

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2012975A Active FR3117532B1 (fr) 2020-12-10 2020-12-10 Aube de turbine pour turbomachine d’aéronef, pourvue d’un canal d’éjection de flux primaire vers une cavité inter-léchettes

Country Status (5)

Country Link
US (1) US20240035391A1 (fr)
EP (1) EP4259903A1 (fr)
CN (1) CN116568909A (fr)
FR (1) FR3117532B1 (fr)
WO (1) WO2022123148A1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55146201A (en) * 1979-05-04 1980-11-14 Hitachi Ltd Moving blade for turbine
JPS5647603A (en) * 1979-09-28 1981-04-30 Hitachi Ltd Moving blade of turbine
US4534701A (en) * 1982-06-29 1985-08-13 Gerhard Wisser Rotor or guide wheel of a turbine engine with shroud ring
DE102008029605A1 (de) * 2008-06-23 2009-12-24 Rolls-Royce Deutschland Ltd & Co Kg Schaufeldeckband mit Durchlass
FR2999249B1 (fr) * 2012-12-07 2015-01-09 Snecma Compresseur pour turbomachine dote de moyens de refroidissement d'un joint tournant assurant l'etancheite entre un redresseur et un rotor
JP6684842B2 (ja) * 2018-03-29 2020-04-22 三菱重工業株式会社 タービン動翼及び回転機械

Also Published As

Publication number Publication date
US20240035391A1 (en) 2024-02-01
WO2022123148A1 (fr) 2022-06-16
CN116568909A (zh) 2023-08-08
EP4259903A1 (fr) 2023-10-18
FR3117532A1 (fr) 2022-06-17

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