Classifications

• • 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
  • B64C11/30—Blade pitch-changing mechanisms
  • B64C11/44—Blade pitch-changing mechanisms electric
• • 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
  • 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
  • F04D29/34—Blade mountings
  • F04D29/36—Blade mountings adjustable
  • F04D29/362—Blade mountings adjustable during rotation
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• • 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
  • F05D2270/00—Control
  • F05D2270/01—Purpose of the control system
  • F05D2270/02—Purpose of the control system to control rotational speed (n)
  • F05D2270/023—Purpose of the control system to control rotational speed (n) of different spools or shafts
• • 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
  • F05D2270/00—Control
  • F05D2270/60—Control system actuates means
  • F05D2270/62—Electrical actuators
• • 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

Definitions

• the invention relates to a rotating electromechanical system comprising a member mounted on a movable shaft, which is able to be moved relative to the movable shaft.
• the electromechanical system comprises a frictionless drive device having a component movable relative to the movable shaft, the service life of which is improved by reducing friction between moving parts.
• the blades are carried by a shaft rotatably mounted around its main axis.
• Each blade is further mounted movable relative to the shaft about a radial axis relative to the main axis of the shaft, to change the pitch of the blade.
• the driving of the rotating blades is achieved by means of a drive system which is connected to the blades and a part of which is mounted on the structural element of the turbomachine.
• the drive means of the blades consist of hydraulic systems with rotating joints or electrical or electronic systems with rotating contacts.
• the object of the invention is to propose a mechanical system for which the means for driving the blades in displacement relative to the shaft are made in such a way as to limit the friction between the moving elements.
• the invention proposes a mechanical system comprising:
• a shaft which is rotatably mounted about its main axis with respect to a structural element
• a movable member which is mounted on the shaft in such a way that it is integral with the shaft in rotation around the main axis and in such a way that it is able to be displaced with respect to the shaft of selectively;
• means for driving the movable member in displacement relative to the shaft which comprise a first fixed part which is mounted on the structural element and a second movable part which is mounted on the shaft and which is connected to to the mobile organ,
• the drive means comprises an electromechanical actuator with an air gap between the first portion and the second portion.
• the gap between the two parts of the actuator eliminates any contact between the elements connected to the structural element and the elements that are movable relative to the structural element, which therefore reduces friction.
• the drive means consist of an electromechanical actuator with radial-field air gap.
• the drive means consist of an electromechanical actuator with air gap at axial field.
• the second portion of the drive means is rotatably mounted coaxially with the shaft and is connected to the shaft by rotation guide means about the main axis of the shaft.
• the mechanical system comprises means for transforming the rotational movement of the second part with respect to the shaft in a displacement of the movable member relative to the shaft which comprises a movement input member connected to the second part, said movement input member being rotatable selectively relative to the shaft during the moving the movable member.
• the mechanical system comprises means for controlling the drive means for controlling the rotational speed of the second part of the drive means relative to the first part, as a function of the speed of rotation of the shaft.
• control means are made to cause rotation of the movement input member around the shaft to cause movement of the movable member relative to the shaft.
• the movable member is mounted to rotate relative to the shaft about a secondary axis (B) radially oriented relative to the main axis, said secondary axis (B) being integral with the shaft rotating around the main axis.
• the invention also provides an aircraft turbomachine characterized in that it comprises a mechanical system according to any one of the preceding claims, wherein the movable member consists of a blade with variable orientation.
• the turbomachine comprises a plurality of blades distributed around the main axis of the shaft.
• FIG. 1 is a schematic representation of a mechanical system according to the invention
• FIG. 2 is a view similar to that of FIG. 1, showing a second embodiment of the motion transformation means
• FIG. 3 is a schematic representation in detail of a mechanical system according to the invention for which the drive means consist of a synchronous or asynchronous machine with magnets;
• FIG. 4 is a view similar to that of FIG. 3, in which the drive means consist of a synchronous machine with a wound inductor;
• FIG. 5 is a view similar to that of FIG. 3, in which the drive means consist of a synchronous machine with axial air gap.
• a mechanical system 10 such as a turbomachine rotor comprising a shaft 12 rotatable about its main axis A, with respect to a structural element 14 of the turbomachine.
• This structural element may itself be fixed in the turbomachine, or it may be movable in the turbomachine.
• the structural element 14 will be considered as being fixed with respect to the shaft 12.
• the shaft carries a plurality of blades 16 which are evenly distributed around the shaft 12 with respect to the main axis A and which are integral with the shaft 12 in rotation with respect to the structural element 14, around the main axis A.
• the mechanical system 10 comprises means for adjusting the pitch of the blades 16 to adapt it to the operating conditions of the turbomachine.
• each blade 16 is mounted movably relative to the shaft 12 about a secondary axis B of principal orientation radial with respect to the main axis A.
• Each secondary axis B is a main axis of the associated blade 16, it is thus rotatable about the main axis A in solidarity with the shaft 12.
• the means for adjusting the pitch of the blades 16 comprise drive means 18 for each blade 16 in rotation around the associated secondary axis B.
• the drive means comprise mainly a first fixed part 20 which is fixed to the structural element 14 and a second movable part 22 which is connected to each blade 16.
• the second part is mounted movable relative to the structural element 14 in rotation around the main axis A.
• the first part 20 and the second part 22 are coaxial with the shaft 12 and consist of two elements of revolution which are superimposed radially on the shaft 12.
• the drive means 18 consist of an electromechanical actuator with air gap. That is to say, a game is present between the fixed part 20 and the mobile part 22.
• the drive of the mobile part 22 in rotation relative to the fixed part 20 is made by electromagnetic forces requiring no contact between the two parts 20, 22.
• the drive means 18 consist of a permanent magnet synchronous machine.
• the mobile part 22 carries one or more permanent magnets (not shown) and the fixed part 20 comprises means for producing an electromagnetic field that causes the rotation of the movable part carrying the permanent magnet or magnets.
• the drive means 18 consist of a synchronous machine with a wound inductor.
• the mobile part 22 carries one or more coils which are supplied with electric current so as to form one or more electromagnets.
• the movable portion 22 is supplied via a current induction system 24 which is also of the type without contacts.
• the drive means 18 consist of an asynchronous machine.
• the shaft 12 and the movable portion 22 both rotate about the main axis A.
• the mechanical system 10 is made such that the second part 22 is able to rotate at a speed different from the speed of rotation of the shaft 12 to allow the blades 16 to move.
• the second portion 22 of the drive means 18 is furthermore connected to the blades 16 via means of transforming the movement 28.
• the movement transformation means 28 are mounted on the shaft 12 so that they are integral with the shaft 12 in rotation about the main shaft A.
• the movement transformation means 28 comprise an input member of movement 36 which is connected to the second portion 22 of the drive means 18.
• the movement transformation member 36 is able to rotate about the shaft 12 selectively depending on the speed of rotation of the second portion 22 driving means 18 around the main axis A.
• the movement transformation means 28 are made so that when the movement input member 36 rotates relative to the shaft 12, each blade 16 rotates about the associated secondary axis B.
• the movement transformation means 28 are of the type comprising a conical gear coupling 32.
• the movement transformation means 28 are of the type comprising a crankshaft system 34.
• the movement input member 36 is connected to the second portion 22 of the drive means 18 via a gear system 30 to change the speed of rotation of the input member of the drive. 36 movement around the axis main A with respect to the speed of rotation of the second portion 22 about the main axis A.
• the reduction ratio of this gear system 30 is determined so as to reduce or increase the rotational speed of the second part 22, according to the type of actuator constituting the drive means 18 and the speed ranges of rotation of the shaft 12.
• the second portion 22 of the drive means 18 is connected directly to the movement input member 36.
• the drive means 18 also comprise regulating means (not shown) which are designed to regulate the speed of rotation of the second portion 22 with respect to the structural element 14 as a function of the rotational speed of the 12 with respect to the structural element 14 and depending on the reduction ratio of the gear system 30.
• the regulating means are made so as to selectively cause a rotation of the movement input member relative to the shaft 12, when the orientation of the blades 16 is to be changed.
• the movement input member 36 must remain stationary relative to the shaft 12, c that is, it rotates at the same speed as the shaft 12 relative to the structural element 14.
• the speed of rotation of the second portion 22 with respect to the structural element 14 is defined so that the rotational speed of the movement input member 36 relative to the structural element 14 is equal to the speed of rotation of the shaft 12 with respect to the structural element 14.
• the regulation means modify the speed of rotation of the second part 22 with respect to the structural element 14 for a certain time so that the input member movement 36 rotates relative to the shaft 12 by a predefined angle corresponding to the change of angular position of each blade 16.
• the change in the rotational speed of the second part 22 with respect to the structural element 14 may consist of an increase, a decrease or an inversion of the speed of rotation of the second part 22.
• the regulation means modify the speed of rotation of the second portion 22 with respect to the structural element 14 so that the movement input member 36 rotates at the same speed as the shaft 12 relative to the structural element 14 and therefore for the movement input member 36 is stationary relative to the shaft 12.
• the supply frequency at the fixed part 20 must compensate the speed of rotation of the shaft 12 relative to to the main axis A.
• F12 is defined as being the differential rotation frequency of the shaft 12 with respect to the first portion 20 (for example for a rotational speed of the shaft 12 with respect to the main axis A of 1200 rpm). this corresponds to a frequency F12 of 20 Hz).
• P is also defined as the number of pole pairs of the synchronous magnet machine.
• the supply frequency of the asynchronous machine is defined by the formula p * (F12 + F22 + Fr) where Fr is the frequency of the rotor currents in the second part 22.
• Fr is more or less important depending on the torque exerted and the point of operation.
• the drive means 18 are of the radial-field gap type, that is to say that the fixed part 20 and the mobile part 22 are coaxial and are offset radially. one with respect to the other.
• the invention is not limited to this embodiment and that the drive means 18 may be of another type, such as for example shown in FIG. 5, in which the drive means are air gap type axial field.
• the fixed portion 20 and the movable portion 22 are offset axially relative to each other.
• the drive means 18 are of the type combining a radial field gap and an axial field gap.
• the invention has been described in association with blades 16 of the turbomachine which are rotatable relative to the secondary axis B. It will be understood that the invention is not limited to this embodiment and that the invention may be associated with any element which is mounted mobile along the secondary axis B in translation along the secondary axis B or in a movement combining translation and rotation with respect to the secondary axis B.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Transmission Devices (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Magnetic Bearings And Hydrostatic Bearings (AREA)
• Dynamo-Electric Clutches, Dynamo-Electric Brakes (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

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Family Applications (1)

Country Status (9)

Families Citing this family (5)

Family Cites Families (12)

• 2011
  • 2011-11-24 FR FR1160764A patent/FR2983235B1/fr active Active
• 2012
  • 2012-11-23 WO PCT/FR2012/052710 patent/WO2013076431A1/fr active Application Filing
  • 2012-11-23 CN CN201280057778.5A patent/CN103958346B/zh active Active
  • 2012-11-23 US US14/357,623 patent/US20140322017A1/en not_active Abandoned
  • 2012-11-23 JP JP2014542919A patent/JP2015500933A/ja active Pending
  • 2012-11-23 CA CA2854991A patent/CA2854991A1/fr not_active Abandoned
  • 2012-11-23 BR BR112014012388-8A patent/BR112014012388B1/pt not_active IP Right Cessation
  • 2012-11-23 EP EP12806560.4A patent/EP2782827A1/de not_active Ceased
  • 2012-11-23 RU RU2014125431A patent/RU2642683C2/ru active

Non-Patent Citations (2)

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