WO2022122367A1 - Moteur électrique pour moteur d'aéronef - Google Patents

Moteur électrique pour moteur d'aéronef Download PDF

Info

Publication number
WO2022122367A1
WO2022122367A1 PCT/EP2021/082528 EP2021082528W WO2022122367A1 WO 2022122367 A1 WO2022122367 A1 WO 2022122367A1 EP 2021082528 W EP2021082528 W EP 2021082528W WO 2022122367 A1 WO2022122367 A1 WO 2022122367A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
electric motor
linear bearings
stator
bearing
Prior art date
Application number
PCT/EP2021/082528
Other languages
English (en)
Inventor
Gergely György BALAZS
Janos Dorogi
Daniel Kutrovich
Original Assignee
Rolls-Royce Deutschland Ltd & Co Kg
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 Rolls-Royce Deutschland Ltd & Co Kg filed Critical Rolls-Royce Deutschland Ltd & Co Kg
Publication of WO2022122367A1 publication Critical patent/WO2022122367A1/fr

Links

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/08—Structural association with bearings
    • H02K7/086—Structural association with bearings radially supporting the rotor around a fixed spindle; radially supporting the rotor directly
    • H02K7/088—Structural association with bearings radially supporting the rotor around a fixed spindle; radially supporting the rotor directly radially supporting the rotor directly
    • 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
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
    • H02K5/173—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings
    • H02K5/1737—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings radially supporting the rotor around a fixed spindle; radially supporting the rotor directly
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans

Definitions

  • the present disclosure relates to an electric motor, to an engine and to an aircraft.
  • an electric motor comprising a stator defining an inner space, a rotor arranged in the inner space of the stator, and a bearing arrangement rotatably supporting the rotor on the stator and comprising a plurality of linear bearings.
  • the electric motor may be an electric motor for an engine, in particular for an aircraft engine.
  • the rotor is rotatable about a rotational axis with respect to the stator.
  • a plurality of linear bearings e.g., two, three or more linear bearings may be spaced apart from one another, particularly in circumferential direction with respect to the rotational axis, and/or be arranged within the same plane, the plane being perpendicular to the rotational axis.
  • the rotor extends between two axial end faces thereof, wherein the linear bearings are arranged at one or both of the axial end faces of the rotor.
  • the linear bearings do not have to be positioned in radial direction between the rotor and the stator, but can be arranged besides the rotor and/or stator. Therefore, the diameter of the inner rotor can be increased without the need of increasing the size of other parts, particularly of the bearings.
  • the bearing arrangement comprises a plurality of (e.g., three) linear bearings on each of two opposing sides of the rotor (e.g., the axial end faces of the rotor). This allows a reliable design of the electric motor.
  • the linear bearings on one of the two opposing sides of the rotor are pretensioned against the linear bearings on the other one of the two opposing sides of the rotor. This allows a particularly secure support of the rotor.
  • each one of the linear bearings is spaced apart from each one of the other linear bearings.
  • the linear bearings on one side of the rotor are spaced equidistantly from adjacent linear bearings in the circumferential direction.
  • At least one, or each of the linear bearings is an integrated recirculating ball bearing guide.
  • the (or each) linear bearing may comprise a carrier that holds a plurality of roller elements, in particular balls.
  • the rotor may comprise at least one bearing path for the linear bearings, in particular two bearing paths, each one on the opposing end faces of the rotor.
  • the bearing path (or each of the bearing paths) may have an annular shape. This allows a simple but robust design and a simplified manufacturing.
  • the bearing path provides a race track for one or more roller elements of the linear bearings.
  • the at least one bearing path is formed on an inner circumferential surface of the rotor. This allows a particularly simple manufacturing of the electric motor and a robust connection with the linear bearings.
  • the rotor comprises a plurality of permanent magnets and/or the stator comprises a plurality of electromagnetic coils.
  • the electric motor is a direct-drive electric motor, in particular a torque motor.
  • the electric motor may be brushless.
  • the rotor may have an inner aperture.
  • the electric motor may be a hollowshaft electric motor. This allows a particularly lightweight design, also at large diameters.
  • the aperture is coaxial with the rotational axis of the rotor with respect to the stator. Further components may be inserted into the aperture.
  • an engine in particular an aircraft engine.
  • the engine comprises the electric motor according to any embodiment described herein, and a fan (or any other bladed device, such as a turbine) fixed to the rotor of the electric motor.
  • a fan or any other bladed device, such as a turbine fixed to the rotor of the electric motor.
  • the rotor of the electric motor may have the inner aperture, particularly coaxial with the rotational axis, and the fan may be arranged in the inner aperture of the rotor.
  • an electric engine is provided that has an outer casing and an inner airstream through the casing. In various applications this can be aerodynamically advantageous. Also, the fan is protected in the inner space.
  • an aircraft comprising at least one engine according to any embodiment described herein.
  • Figure 1 is a view of a hollow-shaft electric motor with an outer stator and an inner rotor;
  • Figure 2 is a view of the back side of the electric motor of Figure 1 , and of a fan to be mounted within the rotor;
  • Figure 3 is a view of an engine comprising the electric motor of Figure 1 and the fan of Figure 2 mounted within the rotor;
  • Figure 4 is a view of a linear bearing and a bearing path of the electric motor of Figure 1 ;
  • Figures 5 and 6 are views of different embodiments of linear bearings and bearing paths.
  • Figure 7 is a view of an aircraft with a plurality of engines.
  • Figure 1 shows an electric motor 1 having a stator 10 defining an inner space 100, a rotor 11 arranged within the inner space 100 of the stator 10, and a bearing arrangement 12.
  • the electric motor 1 is a torque motor.
  • the stator 10 comprises a plurality of electric coils 101 distributed around a rotational axis of the rotor 11 with respect to the stator 10.
  • the stator 10 may be mounted to a support structure, e.g., a case of an engine.
  • the stator 11 comprises a plurality of mounting points 103, e.g., screw holes or the like.
  • the stator 10 further comprises integrated coolant pipes 102 surrounding the arrangement of coils 101 in order to cool the coils 101 by guiding a coolant through the coolant pipes 102.
  • the rotor 11 has a plurality of permanent magnets 114, two of which being indicated in Figure 1 by means of dashed lines. Adjacent permanent magnets 114 are arranged with alternating polarity aligned with the radial direction.
  • the rotor 11 has a generally cylindrical shape, wherein the cylinder axis is coaxial with the rotational axis R.
  • the rotor 11 defines an inner aperture 113, so that other components may extend through and/or be arranged within the rotor 11 .
  • the inner aperture 113 is coaxial with the rotational axis R. In the direction of the rotational axis R, the rotor 11 extends between two axial end faces 110A, 110B. Further, the rotor 11 has a plurality of mounting points 115, e.g., screw holes, for mounting another component to the rotor 11 .
  • a fan 20 is shown to be mounted within the aperture 113 of the rotor 11 .
  • the fan 20 may be mounted on the mounting points 115 of the rotor 11 .
  • the fan 20 comprises a plurality of blades.
  • the rotor 11 has generally at least one bearing path.
  • the rotor 11 has two bearing paths 111 , one on each axial side of the rotor 11 .
  • Each bearing path 111 has an annular shape.
  • Each bearing path 111 provides a track for at least one rolling element.
  • the bearing paths 111 may be milled into the material of the rotor 11 , particularly on a hub of the rotor 11 .
  • the bearing arrangement 12 rotatably supports the rotor 11 on the stator 10.
  • the bearing arrangement 12 serves to transfer all axial and radial loads on the rotor 11 to the stator 10.
  • the bearing arrangement 12 houses the rotor 11 on both axial sides thereof.
  • the bearing arrangement 12 comprises a plurality of linear bearings 120.
  • the number and size of the linear bearings 120 may be adapted to the operating loads of the respective application.
  • the bearing arrangement 12 comprises a plurality of (more precisely: three) linear bearings 120 on each axial side or the rotor 11 .
  • the linear bearings are arranged at the axial end faces 110A, 110B of the rotor 11.
  • the linear bearings 120 on each axial side are arranged spaced with respect to one another.
  • the three axial bearings on each side are arranged equidistantly.
  • the linear bearings 120 are arranged with an offset of 120 degrees with respect to the adjacent linear bearings 120 in the circumferential direction.
  • the linear bearings 120 have the same construction compared to one another.
  • the linear bearings 120 on one side of the rotor 11 are pre-tensioned against the linear bearings 120 on the opposing side of the rotor 11. Therefore, the rotor is rotatably supported, but stiffly held in the axial and radial directions on the stator 10 by means of the bearing arrangement 12.
  • Each linear bearing 120 has a carrier 121 fixed to the stator 10 and extending radially inward towards the rotational axis R.
  • each carrier 121 has a cutout. Possible embodiments of the linear bearings 121 including the carrier 121 will be described in further detail below with reference to Figures 4 to 6.
  • the application of the linear bearings on the axial sides of the rotor 11 allows to increase the diameter of the electric motor 1 and, particularly, of the rotor 11 while maintaining a comparably low weight. Further, the diameter of the inner aperture 113 of the rotor 11 can be designed particularly large.
  • Figure 3 shows an engine 2 for an aircraft comprising the electric motor 1 and the fan 20 fixed to the rotor 11 in the aperture 113 of the rotor 11 .
  • the engine 2 may comprise a case that houses the electric motor 1 and fan 20.
  • Figure 4 shows a portion of the rotor 11 of the electric motor 1 including a section of one of the bearing paths 111 , as well as one of the linear bearings 120.
  • the linear bearing 120 comprises the carrier 121 and a plurality of balls 122.
  • the carrier 121 defines at least one, in the present case two (alternatively more than two) recirculation tracks 123 for a plurality of the balls 122 each.
  • the linear bearing 120 thus, forms a recirculating ball bearing guide with the circular bearing path 111.
  • Each recirculation track 123 allows the balls 122 to roll along a section of the bearing path 111 and along the carrier 121 in one direction with respect to the carrier 121 along a first section of the recirculation track 123, and then to recirculate and be pushed by the other balls 122 back in the opposite direction with respect to the carrier 121 along a second section of the recirculation track 123 parallel to the first section of the recirculation track 123. Therefore, a comparably low number of balls 122 are sufficient to support the rotor 11 and thus to reduce the weight of the electric motor 1 .
  • the bearing paths 111 are arranged at inner circumferential surfaces 112 of the rotor 11 .
  • the bearing paths 111 are arranged at the axial end faces 110A, 110B of the rotor 11 .
  • Figures 5 and 6 show different alternatives for the number and arrangement of recirculation tracks 123 of the corresponding carrier 121.
  • the carrier 121 comprises two recirculation tracks 123 spaced apart with respect to one another in a direction parallel to the rotational axis R.
  • the bearing path 111 limits the movement in both directions along the rotational axis R.
  • Figure 6 only one recirculation track 123 is provided.
  • Figure 7 illustrates an aircraft 3 in the form of a passenger airplane.
  • the aircraft 3 comprises several (i.e., two) engines 2 in accordance with Figure 3.
  • the electric motor 1 with the fan 20 are arranged within an outer casing 21 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

L'invention concerne un moteur électrique (1) qui comprend un stator (10) définissant un espace intérieur (100) ; un rotor (11) disposé dans l'espace intérieur (100) du stator (10) ; et un ensemble paliers (12) portant de manière rotative le rotor (11) sur le stator (10) et comprenant une pluralité de paliers linéaires (120).
PCT/EP2021/082528 2020-12-11 2021-11-22 Moteur électrique pour moteur d'aéronef WO2022122367A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102020215765.0 2020-12-11
DE102020215765 2020-12-11

Publications (1)

Publication Number Publication Date
WO2022122367A1 true WO2022122367A1 (fr) 2022-06-16

Family

ID=78822013

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2021/082528 WO2022122367A1 (fr) 2020-12-11 2021-11-22 Moteur électrique pour moteur d'aéronef

Country Status (1)

Country Link
WO (1) WO2022122367A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE29823336U1 (de) * 1998-03-25 1999-04-22 Kloecker Entwicklungs Gmbh Vorrichtung zum Bilden einer Dreherkante mit einem Elektromotor umfassend einen Rotor und einen den Rotor aufnehmenden Stator
WO2010125629A1 (fr) * 2009-04-27 2010-11-04 Ikeda Kaidou Réduction d'épaisseur et de poids d'armature introduite dans une section creuse de conduit rotatif sensiblement en forme de u
US20110194669A1 (en) * 2010-02-09 2011-08-11 Daren Paul Tremaine Diagnostic Scanning Apparatus
US8354768B2 (en) * 2008-01-21 2013-01-15 Avio S.P.A. Modular electromagnetic device with reversible generator-motor operation
US8933598B2 (en) * 2009-09-29 2015-01-13 Openhydro Ip Limited Hydroelectric turbine with coil cooling
US20190288580A1 (en) * 2015-08-11 2019-09-19 Genesis Robotics And Motion Technologies Canada, Ulc Axial gap electric machine with permanent magnets arranged between posts

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE29823336U1 (de) * 1998-03-25 1999-04-22 Kloecker Entwicklungs Gmbh Vorrichtung zum Bilden einer Dreherkante mit einem Elektromotor umfassend einen Rotor und einen den Rotor aufnehmenden Stator
US8354768B2 (en) * 2008-01-21 2013-01-15 Avio S.P.A. Modular electromagnetic device with reversible generator-motor operation
WO2010125629A1 (fr) * 2009-04-27 2010-11-04 Ikeda Kaidou Réduction d'épaisseur et de poids d'armature introduite dans une section creuse de conduit rotatif sensiblement en forme de u
US8933598B2 (en) * 2009-09-29 2015-01-13 Openhydro Ip Limited Hydroelectric turbine with coil cooling
US20110194669A1 (en) * 2010-02-09 2011-08-11 Daren Paul Tremaine Diagnostic Scanning Apparatus
US20190288580A1 (en) * 2015-08-11 2019-09-19 Genesis Robotics And Motion Technologies Canada, Ulc Axial gap electric machine with permanent magnets arranged between posts

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