FR3083566B1 - TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE - Google Patents

TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE Download PDF

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Publication number
FR3083566B1
FR3083566B1 FR1856105A FR1856105A FR3083566B1 FR 3083566 B1 FR3083566 B1 FR 3083566B1 FR 1856105 A FR1856105 A FR 1856105A FR 1856105 A FR1856105 A FR 1856105A FR 3083566 B1 FR3083566 B1 FR 3083566B1
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FR
France
Prior art keywords
turbine assembly
sealing device
vanes
aircraft turbomachine
cooling circuit
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
FR1856105A
Other languages
French (fr)
Other versions
FR3083566A1 (en
Inventor
Erwan Perrot
Camille Maryse Martine Palomba
Antoine Frederic Jean Satre
Marc-Antoine Anatole Got
Stephane Sylvain Bois
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 FR1856105A priority Critical patent/FR3083566B1/en
Publication of FR3083566A1 publication Critical patent/FR3083566A1/en
Application granted granted Critical
Publication of FR3083566B1 publication Critical patent/FR3083566B1/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • 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)

Abstract

L'invention concerne un ensemble de turbine pour turbomachine d'aéronef, comprenant un disque (17) portant des aubes rotatives (18), un dispositif de rétention axiale des aubes sur ce disque incluant un organe de retenue (32) axiale des aubes maintenu en appui contre le disque et les aubes par une extrémité d'appui (34) d'un flasque annulaire (33), et un dispositif d'étanchéité comprenant au moins un élément d'étanchéité (48) qui inclut une première portion d'attache enserrée axialement entre le disque (17) et l'organe de retenue axiale (32), et une portion d'étanchéité qui prolonge la première portion d'attache en s'étendant vers le flasque (33) pour être en contact avec ce flasque (33).The invention relates to a turbine assembly for an aircraft turbomachine, comprising a disk (17) carrying rotary vanes (18), a device for axially retaining the vanes on this disk including an axial retaining member (32) of the vanes maintained bearing against the disc and the vanes by a bearing end (34) of an annular flange (33), and a sealing device comprising at least one sealing element (48) which includes a first portion of fastener clamped axially between the disc (17) and the axial retaining member (32), and a sealing portion which extends the first fastener portion by extending towards the flange (33) to be in contact with this flange (33).

FR1856105A 2018-07-03 2018-07-03 TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE Active FR3083566B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1856105A FR3083566B1 (en) 2018-07-03 2018-07-03 TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1856105 2018-07-03
FR1856105A FR3083566B1 (en) 2018-07-03 2018-07-03 TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE

Publications (2)

Publication Number Publication Date
FR3083566A1 FR3083566A1 (en) 2020-01-10
FR3083566B1 true FR3083566B1 (en) 2020-10-02

Family

ID=63638058

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1856105A Active FR3083566B1 (en) 2018-07-03 2018-07-03 TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH DISC COOLING CIRCUIT EQUIPPED WITH A SEALING DEVICE

Country Status (1)

Country Link
FR (1) FR3083566B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4669959A (en) * 1984-07-23 1987-06-02 United Technologies Corporation Breach lock anti-rotation key
JP5358031B1 (en) * 2013-03-22 2013-12-04 三菱重工業株式会社 Turbine rotor, turbine, and seal plate removal method
WO2015129580A1 (en) * 2014-02-26 2015-09-03 三菱日立パワーシステムズ株式会社 Rotor blade retention device, rotor blade fixing member pressing device, and manufacture method, assembly method and disassembly method of rotating machine
TWI696751B (en) * 2016-12-13 2020-06-21 日商三菱日立電力系統股份有限公司 Disassembly and assembly method of gas turbine, seal plate assembly, gas turbine roller, gas turbine, and method of manufacturing gas turbine

Also Published As

Publication number Publication date
FR3083566A1 (en) 2020-01-10

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