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FR3010442B1 - Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef - Google Patents

Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef

Info

Publication number
FR3010442B1
FR3010442B1 FR1358646A FR1358646A FR3010442B1 FR 3010442 B1 FR3010442 B1 FR 3010442B1 FR 1358646 A FR1358646 A FR 1358646A FR 1358646 A FR1358646 A FR 1358646A FR 3010442 B1 FR3010442 B1 FR 3010442B1
Authority
FR
France
Prior art keywords
monobloc
reduced
aircraft turbomachine
drawing disk
wave foot
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
FR1358646A
Other languages
English (en)
Other versions
FR3010442A1 (fr
Inventor
Damien Merlot
Remi Sers
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 FR1358646A priority Critical patent/FR3010442B1/fr
Priority to US14/466,044 priority patent/US9765637B2/en
Priority to GB1415103.9A priority patent/GB2519845B/en
Publication of FR3010442A1 publication Critical patent/FR3010442A1/fr
Application granted granted Critical
Publication of FR3010442B1 publication Critical patent/FR3010442B1/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
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • 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
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR1358646A 2013-09-09 2013-09-09 Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef Active FR3010442B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1358646A FR3010442B1 (fr) 2013-09-09 2013-09-09 Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef
US14/466,044 US9765637B2 (en) 2013-09-09 2014-08-22 Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan
GB1415103.9A GB2519845B (en) 2013-09-09 2014-08-26 Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1358646A FR3010442B1 (fr) 2013-09-09 2013-09-09 Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef

Publications (2)

Publication Number Publication Date
FR3010442A1 FR3010442A1 (fr) 2015-03-13
FR3010442B1 true FR3010442B1 (fr) 2015-10-09

Family

ID=49998359

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1358646A Active FR3010442B1 (fr) 2013-09-09 2013-09-09 Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef

Country Status (3)

Country Link
US (1) US9765637B2 (fr)
FR (1) FR3010442B1 (fr)
GB (1) GB2519845B (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3028574B1 (fr) 2014-11-17 2019-09-20 Safran Aircraft Engines Disque aubage monobloc pour soufflante de turbomachine comportant un evidement amont et ou aval conferant une plus grande flexibilite a ses aubes
FR3033359B1 (fr) * 2015-03-02 2017-04-07 Snecma Disque aubage monobloc comportant un moyeu ayant une face evidee a laquelle est rapporte un organe de comblement
FR3053083B1 (fr) * 2016-06-22 2019-11-01 Safran Aircraft Engines Anneau de carenage de roue a aubes
FR3056630B1 (fr) 2016-09-26 2018-12-07 Safran Aircraft Engines Disque aubage monobloc de soufflante pour turbomachine d'aeronef
FR3077599B1 (fr) * 2018-02-08 2020-03-06 Safran Aircraft Engines Roue mobile de turbine pour turbomachine d'aeronef, comprenant un anneau de retention axiale fixe aux pieds des aubes
FR3079008B1 (fr) 2018-03-19 2020-02-28 Safran Aircraft Engines Disque aubage monobloc souple en partie basse des aubes
FR3081186B1 (fr) * 2018-05-16 2022-12-23 Safran Aircraft Engines Aube mobile de turbine renforcee

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
FR2639402B1 (fr) * 1988-11-23 1990-12-28 Snecma Disque ailete de rotor de turbomachine
FR2679599A1 (fr) * 1991-07-24 1993-01-29 Snecma Perfectionnement aux roues a aubes de turbomachines.
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
US6219916B1 (en) * 1997-12-19 2001-04-24 United Technologies Corporation Method for linear friction welding and product made by such method
US6273683B1 (en) * 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
JP4346412B2 (ja) * 2003-10-31 2009-10-21 株式会社東芝 タービン翼列装置
DE102009023840A1 (de) * 2009-06-04 2010-12-09 Mtu Aero Engines Gmbh Rotor einer Strömungsmaschine mit separatem Deckband
FR2974864B1 (fr) * 2011-05-04 2016-05-27 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR2983234B1 (fr) * 2011-11-29 2014-01-17 Snecma Aube pour disque aubage monobloc de turbomachine
US20140186166A1 (en) * 2012-12-27 2014-07-03 General Electric Company Hybrid Continuous Fiber Chopped Fiber Polymer Composite Structure
US9759129B2 (en) * 2012-12-28 2017-09-12 United Technologies Corporation Removable nosecone for a gas turbine engine

Also Published As

Publication number Publication date
US9765637B2 (en) 2017-09-19
GB2519845B (en) 2020-03-18
GB201415103D0 (en) 2014-10-08
US20150267545A1 (en) 2015-09-24
FR3010442A1 (fr) 2015-03-13
GB2519845A (en) 2015-05-06

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