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FR2972482B1 - TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION - Google Patents

TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION

Info

Publication number
FR2972482B1
FR2972482B1 FR1151815A FR1151815A FR2972482B1 FR 2972482 B1 FR2972482 B1 FR 2972482B1 FR 1151815 A FR1151815 A FR 1151815A FR 1151815 A FR1151815 A FR 1151815A FR 2972482 B1 FR2972482 B1 FR 2972482B1
Authority
FR
France
Prior art keywords
turbine
improved seal
mechanical retention
aircraft turbomachine
turbine blades
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
FR1151815A
Other languages
French (fr)
Other versions
FR2972482A1 (en
Inventor
Guy Burlet
Emmanuel Berche
Amaury Roussely-Rousseau
Jean Pierre Louis Mareix
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
Priority to FR1151815A priority Critical patent/FR2972482B1/en
Publication of FR2972482A1 publication Critical patent/FR2972482A1/en
Application granted granted Critical
Publication of FR2972482B1 publication Critical patent/FR2972482B1/en
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
    • 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
    • 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
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2240/55—Seals
    • 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
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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)
FR1151815A 2011-03-07 2011-03-07 TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION Active FR2972482B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1151815A FR2972482B1 (en) 2011-03-07 2011-03-07 TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1151815A FR2972482B1 (en) 2011-03-07 2011-03-07 TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION

Publications (2)

Publication Number Publication Date
FR2972482A1 FR2972482A1 (en) 2012-09-14
FR2972482B1 true FR2972482B1 (en) 2016-07-29

Family

ID=44310417

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1151815A Active FR2972482B1 (en) 2011-03-07 2011-03-07 TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION

Country Status (1)

Country Link
FR (1) FR2972482B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3006364B1 (en) * 2013-05-30 2018-07-13 Safran Aircraft Engines TURBOMACHINE WHEEL, IN PARTICULAR FOR LOW PRESSURE TURBINE
EP3438410B1 (en) 2017-08-01 2021-09-29 General Electric Company Sealing system for a rotary machine
US12012857B2 (en) * 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
FR3141720A1 (en) * 2022-11-04 2024-05-10 Safran Aircraft Engines sealing member for a moving blade

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE791375A (en) * 1971-12-02 1973-03-01 Gen Electric DEFLECTOR AND SHOCK ABSORBER FOR TURBOMACHINE FINS
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
GB2043797A (en) * 1979-03-10 1980-10-08 Rolls Royce Bladed Rotor for Gas Turbine Engine
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
FR2840352B1 (en) * 2002-05-30 2005-12-16 Snecma Moteurs MASTING THE LEAK AREA UNDER A DAWN PLATFORM
GB0611031D0 (en) * 2006-06-06 2006-07-12 Rolls Royce Plc An aerofoil stage and a seal for use therein
US7806662B2 (en) * 2007-04-12 2010-10-05 Pratt & Whitney Canada Corp. Blade retention system for use in a gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control

Also Published As

Publication number Publication date
FR2972482A1 (en) 2012-09-14

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