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FR2942454B1 - Dispositif de retenue d'aube pour helice de turbomachine. - Google Patents

Dispositif de retenue d'aube pour helice de turbomachine.

Info

Publication number
FR2942454B1
FR2942454B1 FR0951132A FR0951132A FR2942454B1 FR 2942454 B1 FR2942454 B1 FR 2942454B1 FR 0951132 A FR0951132 A FR 0951132A FR 0951132 A FR0951132 A FR 0951132A FR 2942454 B1 FR2942454 B1 FR 2942454B1
Authority
FR
France
Prior art keywords
retention device
blade retention
turbomachine propeller
turbomachine
propeller
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
FR0951132A
Other languages
English (en)
Other versions
FR2942454A1 (fr
Inventor
Laurent Lafont
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations 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 Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR0951132A priority Critical patent/FR2942454B1/fr
Priority to US12/709,793 priority patent/US8496438B2/en
Publication of FR2942454A1 publication Critical patent/FR2942454A1/fr
Application granted granted Critical
Publication of FR2942454B1 publication Critical patent/FR2942454B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/79—Bearing, support or actuation arrangements therefor
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR0951132A 2009-02-23 2009-02-23 Dispositif de retenue d'aube pour helice de turbomachine. Active FR2942454B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0951132A FR2942454B1 (fr) 2009-02-23 2009-02-23 Dispositif de retenue d'aube pour helice de turbomachine.
US12/709,793 US8496438B2 (en) 2009-02-23 2010-02-22 Blade retaining device for turbo machine propeller

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0951132A FR2942454B1 (fr) 2009-02-23 2009-02-23 Dispositif de retenue d'aube pour helice de turbomachine.

Publications (2)

Publication Number Publication Date
FR2942454A1 FR2942454A1 (fr) 2010-08-27
FR2942454B1 true FR2942454B1 (fr) 2012-09-14

Family

ID=41202294

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0951132A Active FR2942454B1 (fr) 2009-02-23 2009-02-23 Dispositif de retenue d'aube pour helice de turbomachine.

Country Status (2)

Country Link
US (1) US8496438B2 (fr)
FR (1) FR2942454B1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2943985B1 (fr) 2009-04-07 2011-05-13 Airbus France Helice pour turbomachine d'aeronef comprenant un anneau de retention d'aubes monte autour du moyeu.
FR2948425B1 (fr) 2009-07-22 2011-09-23 Airbus Operations Sas Dispositif de retenue d'aube pour helice de turbomachine
EP2535519A3 (fr) 2011-06-14 2014-11-12 Rolls-Royce plc Dispositif de retenue pour pale rotative
GB2491811B (en) 2011-06-14 2013-10-09 Rolls Royce Plc Mounting system
FR2984847B1 (fr) * 2011-12-23 2013-12-27 Ratier Figeac Soc Pale a ancrage redondant dans un moyeu, helice, turbopropulseur et aeronef
GB201211133D0 (en) * 2012-06-22 2012-08-08 Rolls Royce Plc A catcher ring arrangement
FR3025246B1 (fr) * 2014-08-29 2016-12-09 Snecma Roue aubagee a calages variables
FR3025247B1 (fr) 2014-08-29 2016-11-11 Snecma Roue aubagee a calages variables
FR3030444B1 (fr) * 2014-12-22 2017-01-27 Airbus Operations Sas Helice pour turbomachine d'aeronef, comprenant une structure de retention de pales traversee par la partie aerodynamique de chaque pale
US9243512B1 (en) 2015-01-14 2016-01-26 General Electric Company Rotary machine with a frangible composite blade
US9878501B2 (en) 2015-01-14 2018-01-30 General Electric Company Method of manufacturing a frangible blade
US9828862B2 (en) 2015-01-14 2017-11-28 General Electric Company Frangible airfoil
FR3040191B1 (fr) * 2015-08-20 2017-08-11 Airbus Operations Sas Helice pour turbomachine d'aeronef comprenant des moyens ameliores de retention radiale de pale d'helice
FR3050718B1 (fr) * 2016-04-28 2022-02-18 Airbus Operations Sas Helice pour turbomachine d'aeronef comprenant des moyens simplifies de retention radiale de pale d'helice
US11644046B2 (en) * 2018-01-05 2023-05-09 Aurora Flight Sciences Corporation Composite fan blades with integral attachment mechanism
US11092020B2 (en) 2018-10-18 2021-08-17 Raytheon Technologies Corporation Rotor assembly for gas turbine engines
US10815795B2 (en) * 2018-12-20 2020-10-27 General Electric Company Pre-tension and retention structure for composite fan blade
FR3109569B1 (fr) * 2020-04-23 2022-05-06 Safran Aircraft Engines Pivot d’aube à orientation réglable et à intégrité sauvegardée pour moyeu de soufflante de turbomachine
US11073030B1 (en) 2020-05-21 2021-07-27 Raytheon Technologies Corporation Airfoil attachment for gas turbine engines
FR3116081B1 (fr) * 2020-11-06 2023-06-02 Safran Aircraft Engines Aube de turbomachine comprenant un connecteur électrique placé au niveau d’un pivot
US12331647B2 (en) 2021-08-31 2025-06-17 Safran Aircraft Engines System for controlling the pitch setting of a propeller vane for an aircraft turbine engine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2302054A (en) * 1942-11-17 Automatic variable pitch sheet met
US1454977A (en) * 1921-02-18 1923-05-15 Middleton Thomas Metal propeller for aeroplanes, dirigibles, balloons, and the like
US1449685A (en) * 1922-02-18 1923-03-27 Luther Carl Engine-cooling fan
US1769801A (en) * 1924-11-15 1930-07-01 Hamilton Standard Propeller Co Propeller
DE1503480A1 (de) * 1965-01-29 1970-07-02 Kuehnle Kopp Kausch Ag Verstellbare Laufschaufel fuer axiale Stroemungsmaschinen
US3480373A (en) * 1966-11-01 1969-11-25 Cooling Dev Ltd Fans
GB2051967B (en) * 1979-05-22 1982-11-17 Colchester Woods Variable pitch axial flow fan impeller
US4524499A (en) * 1981-11-16 1985-06-25 Trw Inc. Method of fabricating an aircraft propeller assembly with composite blades
GB2192238B (en) 1986-07-02 1990-05-23 Rolls Royce Plc Gas turbine engine power turbine
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
DE4015207C1 (en) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh Bearing for aircraft engine rotor blade - incorporates torsional tie rod in compact design
US6155784A (en) * 1997-01-09 2000-12-05 Cartercopters, Llc. Variable pitch aircraft propeller
GB0712561D0 (en) * 2007-06-28 2007-08-08 Rolls Royce Plc A blade mounting
EP2025947B1 (fr) * 2007-07-31 2013-02-27 R.E.M. Holding S.R.L. Système de connexion de profil de moyeu pour ventilateur axial et ventilateur axial doté de ce système de connexion

Also Published As

Publication number Publication date
US20100215499A1 (en) 2010-08-26
US8496438B2 (en) 2013-07-30
FR2942454A1 (fr) 2010-08-27

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