US20160352174A1 - Rotor assembly for an electric machine - Google Patents
Rotor assembly for an electric machine Download PDFInfo
- Publication number
- US20160352174A1 US20160352174A1 US15/027,464 US201315027464A US2016352174A1 US 20160352174 A1 US20160352174 A1 US 20160352174A1 US 201315027464 A US201315027464 A US 201315027464A US 2016352174 A1 US2016352174 A1 US 2016352174A1
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- Prior art keywords
- cap
- post
- rotor assembly
- core
- corner
- Prior art date
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- Abandoned
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/46—Fastening of windings on the stator or rotor structure
- H02K3/52—Fastening salient pole windings or connections thereto
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K19/00—Synchronous motors or generators
- H02K19/16—Synchronous generators
- H02K19/38—Structural association of synchronous generators with exciting machines
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/02—Details of the magnetic circuit characterised by the magnetic material
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/24—Rotor cores with salient poles ; Variable reluctance rotors
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/26—Rotor cores with slots for windings
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/26—Rotor cores with slots for windings
- H02K1/265—Shape, form or location of the slots
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/28—Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/32—Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/32—Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
- H02K1/325—Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium between salient poles
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K19/00—Synchronous motors or generators
- H02K19/02—Synchronous motors
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K19/00—Synchronous motors or generators
- H02K19/16—Synchronous generators
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
- H02K3/18—Windings for salient poles
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/46—Fastening of windings on the stator or rotor structure
- H02K3/52—Fastening salient pole windings or connections thereto
- H02K3/527—Fastening salient pole windings or connections thereto applicable to rotors only
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/22—Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/22—Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
- H02K9/227—Heat sinks
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/19—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
- H02K9/197—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil in which the rotor or stator space is fluid-tight, e.g. to provide for different cooling media for rotor and stator
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/22—Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
- H02K9/223—Heat bridges
Definitions
- Electric machines such as electric motors and/or electric generators, are used in energy conversion.
- an electric motor having a combination of motor and generator modes, where the electric machine, in motor mode, is used to start an aircraft engine, and, depending on the mode, functions as a generator, too, to supply electrical power to the aircraft systems.
- the machines typically include a rotor having main windings that are driven to rotate by a source of rotation, such as a mechanical or electrical machine, which for some aircraft may be a gas turbine engine.
- a rotor assembly for an electric machine includes a core having at least one post about which a winding may be wound to define a pole for the electric machine, with the at least one post at least partially defining a winding seat, a cap overlying the post and the winding seat to collectively define an axial extending winding slot with the core, and an interlock removably coupling the cap and the post.
- FIG. 1 is a sectional view of an electric machine capable of operation as a starter/generator and having a rotor assembly according to various aspects described herein.
- FIG. 2 is a partial perspective view of the rotor assembly of FIG. 1 sectioned along line 2 - 2 of FIG. 1 .
- FIG. 3 is an enlarged portion of the area labeled III of the rotor assembly of FIG. 2 .
- FIG. 4 is a perspective view of a rotor core from the rotor assembly of FIG. 2 .
- FIG. 5 is a partial sectional view of the rotor assembly according to various aspects described herein.
- FIG. 6 is a partial sectional view of the rotor assembly according to various aspects described herein.
- FIG. 7 is a partial sectional view of the rotor assembly according to various aspects described herein.
- embodiments of the innovation may be implemented in any environment using synchronous electric machine or main machine, a specific example of which is a generator.
- the generator is currently contemplated to be implemented in a jet engine environment.
- Embodiments of the innovation may alternatively include a starter/generator and may provide turbine engine starting capabilities, wherein the starter/generator provides the mechanical power to drive the turbine engine through a starting method.
- a starter/generator may provide turbine engine starting capabilities, wherein the starter/generator provides the mechanical power to drive the turbine engine through a starting method.
- FIG. 1 illustrates an electric machine assembly 10 mounted on or within a gas turbine aircraft engine.
- the gas turbine engine may be a turbofan engine, such as a General Electric GEnx or CF6 series engine, commonly used in modern commercial and military aviation or it could be a variety of other known gas turbine engines such as a turboprop or turboshaft.
- the electrical machine assembly 10 comprises a first machine 12 having an exciter rotor 14 and an exciter stator 16 , and a synchronous second machine 18 having a main machine rotor 20 and a main machine stator 22 .
- At least one power connection is provided on the exterior of the electrical machine assembly 10 to provide for the transfer of electrical power to and from the electrical machine assembly 10 . Power is transmitted by this power connection, shown as an electrical power cable 30 , directly or indirectly, to the electrical load and may provide for a three phase with a ground reference output from the electrical machine assembly 10 .
- the electrical machine assembly 10 further comprises a rotatable shaft 32 mechanically coupled to a source of axial rotation, which may be a gas turbine engine, about an axis of rotation 34 .
- the rotatable shaft 32 is supported by spaced bearings 36 .
- the exciter rotor 14 and main machine rotor 20 are mounted to the rotatable shaft 32 for rotation relative to the stators 16 , 22 , which are rotationally fixed within the electrical machine assembly 10 .
- the stators 16 , 22 may be mounted to any suitable part of a housing portion of the electrical machine assembly 10 .
- the rotatable shaft 32 is configured such that mechanical force from a running turbine engine provides rotation to the shaft 32 .
- rotation of the rotatable shaft 32 of the electrical machine assembly 10 during a starting mode produces a mechanical force that is transferred through the shaft 32 to provide rotation to the turbine engine.
- FIG. 2 illustrates a perspective view of the main machine rotor assembly 40 with at least a portion of the axial front end of the assembly 40 cut away.
- the rotor assembly 40 is shown comprising a core 42 having at least one post 44 extending radially from the core 42 , about which a rotor winding 46 , which may be electrically isolated from each other, may be wound to define a pole 48 for the assembly 40 .
- each of four poles 48 of the rotor assembly 40 includes one rotor winding 46 , wound axially about a post 44 to define a rotor winding set 50 .
- the core 42 may be, for instance, molded, formed, or bored from a non-laminated or non-lamination, solid or unitary body material.
- a core body material may be steel. Alternate body materials and formations of the core 42 are envisioned, for instance, using additive manufacturing.
- Each pole 48 of the rotor assembly 40 further comprises a cap 52 .
- the rotor assembly 40 further comprises additional radial elements 54 spaced radially about the assembly 40 , adjacent to, and in an alternating arrangement with, the multitude of caps 52 .
- Each cap 52 at least partially overlies each post 44 , pole 48 , and rotor winding set 50 , and is spaced from each adjacent cap 52 by the radial element 54 , such that the collective cap 52 , radial element 54 , and posts 44 of the core 42 at least partially define an axially extending winding slot 56 for receiving the rotor windings 46 .
- Each cap 52 may be formed or comprised by a plurality of laminations, for instance, cobalt laminations.
- cobalt laminations may comprise the cap 52 due to its high magnetic and electrical resistance properties, and thus, its ability to minimize eddy currents at the surface of each pole 48 .
- Cobalt laminations are merely one example of a material used to construct the cap 52 , and alternate material composition or compositions are envisioned. Comparing the cap 52 to the core 46 , the cap 52 may be less electrically conductive and less thermally conductive than the core 42 .
- each cap 52 is removably coupled with the posts 44 of the core 42 via an interlocking of the cap 52 with the posts 44 .
- the interlock comprises a projection 58 on the cap 52 and a recess 60 on the post 44 , wherein both the cap projection 58 and post recess 60 have partially circular, complementary cross sections, such that the projection 58 is received within the post recess 60 to removably couple the cap 52 to the post 44 .
- the interlocking elements are reversed, for example, a projection 58 on the post 44 , and a recess 60 on the cap 52 .
- the core 42 further at least partially defines internal coolant passages 62 on the posts 44 , located adjacent to, and extending axially in parallel with, the winding slots 56 , and radial coolant passages 64 extending radially from the center of the core 42 to each internal coolant passage 62 .
- the internal coolant passages 62 may be, for example, molded, formed, or bored into the core 42 , and are at least partially separated from the rotor windings 46 by, for instance, a thin portion of the post 44 , allowing for thermal transfer between the windings 46 and the coolant.
- the rotatable shaft 32 may additionally include a plurality of coolant passage holes 66 that are radially spaced about the shaft 32 such that they align with radial coolant passages 64 , and allows for coolant to flow from the central coolant passage 28 to and from the radial coolant passages 64 .
- the assembled rotatable shaft 32 with coolant passage holes 66 and central coolant passage 28 , and core 42 with internal coolant passages 62 and radial coolant passages 64 defines a coolant path wherein coolant may fluidly traverse, flow, or be forcibly pumped from the coolant passage holes 66 , through the radial coolant passage 64 , to the internal coolant passage 62 , and returned to the central coolant passage 28 .
- the rear axial end of the rotor assembly 40 may comprise a duplicate set of coolant passage holes 66 and radial coolant passages 64 such that the coolant may traverse, flow, or be forcibly pumped axially along the central coolant passage 28 and internal coolant passages 62 to form a coolant loop.
- the entire coolant loop may be internal to the core 42 .
- Alternative flows, paths, and loops of the coolant through the coolant passage holes 66 , radial coolant passages 64 , and internal coolant passages 62 , and central coolant passage 28 are envisioned.
- the rotor assembly 40 is shown further comprising a second projection 68 on at least a portion of the post 44 that is keyed to be received in a second recess 70 of the radial element 54 .
- the second projection 68 and second recess 70 have similar cross sections such that the projection 68 received within the recess 70 to removably couple the radial element 54 to the core 42 .
- the radial element 54 is shown further abutting a biasing element, such as a wedge 72 , configured such that the coupling of the radial element 54 to the core 42 biases or secures the rotor windings 46 into the winding slot 56 .
- the biasing of the rotor windings 46 into the winding slot 56 ensures a physical contact between the windings 46 and slot 56 , which serves to enhance the thermal transfer via conduction.
- Alternative couplings are envisioned wherein removably coupling the compressive radial 54 to the core 42 biases the rotor windings 46 into the winding slot 56 .
- the core 42 further comprises a winding seat 74 at the interface of the rotor windings 46 and the posts 44 , for receiving the rotor windings 46 .
- the winding seat 74 may further comprise a thermally conductive, electrically isolating layer 76 separating the rotor windings 46 from the posts 44 .
- This thermally conductive layer 76 may be, for example, formed by a coating applied to the winding seat 74 .
- Alternative thermally conductive layer 76 formations and assemblies are envisioned, such as adhesion by glue, mechanical fastening, etc.
- the radial coolant passage 64 may further extend along a channel 78 of the winding seat 74 , wherein the channel 78 is not adjacent to the internal coolant passage 62 .
- the channel 78 may further comprise additional internal coolant passages 62 that run axially along the axis of rotation 34 , parallel to, or intersecting with the existing passages 62 .
- FIG. 4 illustrates one embodiment of the core 42 of the rotor assembly 40 with the cap 52 , radial elements 54 , rotor windings 46 , and other removable components detached.
- the rotor assembly 40 is rotated about the axis of rotation 34 by a mechanical force, such as a turbine engine, coupled with the rotatable shaft 32 .
- a mechanical force such as a turbine engine
- the rotor windings 46 are energized to create a pole 48 , for example, DC power from a rectified AC power output of the exciter rotor 14 .
- the rotation of the pole 48 relative to the main machine stator 22 generates a power output, such as an AC power output, which is then transmitted by the electrical power cable 30 to an electrical system, for instance, a power distribution node.
- the DC current transmitted through the energized rotor windings 46 generates heat in the windings 46 . Since the core 42 is more thermally conductive than the cap 52 , a portion of the generated heat is transferred away from the rotor winding 46 via the thermally conductive layer 76 of the winding seat 74 , to the core 42 . Additionally, the wedges 72 bias the rotor windings 46 toward the winding seat 74 to ensure a firm thermal conduction interface between the windings 46 and the seat 74 .
- the rotor assembly 40 is also configured to remove heat generated in the rotor windings 46 , as well as heat transferred to the core 42 , via the above described coolant paths and loops 28 , 62 , 64 , 66 , 78 .
- the coolant traversing through the rotor assembly 40 may directly remove the heat generated by the rotor windings 46 via the thermally conductive layer 76 directly adjacent to the internal coolant passages 62 .
- the heat generated may be first transferred to the core 42 as described above, and then transferred to the coolant via the coolant paths and loops 28 , 62 , 64 , 66 , 78 .
- the collective coupling of the cap 52 , the radial element 54 , and the wedges 74 to the rotor assembly 40 tend to oppose the centrifugal forces on the rotor windings 46 , and help improve the thermal transfer from the windings 46 to the coolant via conduction, by ensuring the winding 46 stays in place and in contact with the thermally conductive layer 76 of the winding seat 74 .
- the projection 58 and recess 60 also provides a secured interlocking of the cap 52 to the posts 44 and the core 42 .
- centrifugal forces may attempt to separate the cap 52 from the posts 44 and core 42 .
- the interlocking of the cap 52 to the posts 44 and the core 42 by the interlocked projection 58 and the recess 60 prevents or retards this separation.
- the interlocking of the cap 52 to the posts 44 and the core 42 provides an anti-rotation lock configured to retard the relative rotation of the cap 52 and the post 44 .
- the assembly of the radial elements 54 further support the anti-rotation lock configuration.
- FIG. 5 illustrates an alternative rotor assembly 140 according to a second embodiment of the innovation.
- the second embodiment is similar to the first embodiment; therefore, like parts will be identified with like numerals increased by 100, with it being understood that the description of the like parts of the first embodiment applies to the second embodiment, unless otherwise noted.
- the cap 152 alternatively comprises at least a partial trapezoidal projection 158 cross section.
- the core 142 will have a complementary trapezoidal cross section in the recess 160 of the post 144 for removably coupling the cap 152 to the core 142 .
- Alternate trapezoidal, or otherwise interlocking cross sections, are envisioned
- FIG. 6 illustrates an alternative rotor assembly 240 according to a third embodiment of the innovation.
- the third embodiment is similar to the first and second embodiments; therefore, like parts will be identified with like numerals increased by 200, with it being understood that the descriptions of the like parts of the first and second embodiments apply to the third embodiment, unless otherwise noted.
- a difference between the third embodiment and the first and second embodiments is that the cap 252 further comprises at least a second projection, shown as a corner finger 290 spaced from and on each side of the projection 158 , extending from the cap 252 , and abutting the opposing corners of the post 244 of the core 242 .
- interlocking elements are reversed, for example, corner fingers 290 on the post 244 , and a corner finger channels 292 on the cap 252 .
- corner fingers 290 and corresponding corner finger channels 292 are shown, alternative numbers of corner fingers 290 and corresponding corner finger channels 292 are envisioned.
- FIG. 7 illustrates an alternative rotor assembly 340 according to a fourth embodiment of the innovation.
- the fourth embodiment is similar to the first, second, and third embodiments; therefore, like parts will be identified with like numerals increased by 300, with it being understood that the descriptions of the like parts of the first, second, and third embodiments apply to the fourth embodiment, unless otherwise noted.
- a difference between the fourth embodiment and the first, second, and third embodiments is that the corner fingers 390 of the cap 352 are spaced from and on each side of the projection 158 , extending from cap 352 , but not abutting the opposing corners of the post 344 of the core 342 .
- the corner fingers 390 have at least a partial trapezoidal cross section, but may have alternative cross sections for removably coupling to and/or interlocking with the core 342 .
- the corner finger channel 392 of the post 344 will have a complementary cross section.
- the interlocking elements are reversed, for example, corner fingers 390 on the post 344 , and a corner finger channels 392 on the cap 352 .
- corner fingers 390 and corresponding corner finger channels 392 are shown, alternative numbers of corner fingers 390 and corresponding corner finger channels 392 are envisioned.
- one embodiment of the innovation contemplates more or fewer of the electrical machine assembly 10 components mentioned, such as poles 48 , caps 52 , rotor windings 46 , etc.
- Another embodiment of the innovation contemplates using wedges 72 configured on different sides of the rotor windings 46 to bias the windings 46 into the winding seats 74 .
- additional wedges 72 may be included to bias more than one side of the rotor windings 46 into the winding seats 74 .
- Another embodiment of the innovation contemplates additional coolant passage holes 66 and radial coolant passages 64 spaced axially along the rotatable shaft 32 , such that additional coolant paths and/or loops may be utilized to improve cooling. Additionally, the design and placement of the various components may be rearranged such that a number of different in-line configurations could be realized.
- the rotor windings set 50 and winding seats 74 may be configured with, for instance a 10° clockwise and counter-clockwise rotation, compared to the illustrated example. It is envisioned that, for instance, the rotor windings 46 on one side of the pole 44 may be configured in a counter-clockwise orientation, while the corresponding windings 46 on the opposing side of the pole may be configured in a clockwise orientation. In this example, each rotated rotor windings 46 may be held in place by one or more wedges 72 , to ensure thermal contact between the windings 46 and the winding seat 74 .
- cap 52 and thermally conductive layer 76 may also include slightly angled surfaces to match the rotated rotor windings 46 .
- a 10° counter-clockwise rotation is one example of a configuration, and other angles are envisioned in both a clockwise and counter-clockwise direction.
- the embodiments disclosed herein provide a generator rotor with a cap and core assembly.
- One advantage that may be realized in the above embodiments is that the above described embodiments have significantly improved thermal conduction to remove heat from the assembly.
- the improved thermal conductivity of the core, compared to a core comprising laminated materials, coupled with the coolant paths and/or loops provide for heat removal in a much more effective fashion from the windings to the coolant.
- Another advantage of the above embodiments is that the thermally conductive layer replaces the typical slot liner in the rotor in a way to provide improved mechanical integrity, along with improved thermal conductivity.
- the thermally conductive layer also replaces thermal conduction or cooling tubes and/or fins, reducing the number of parts, and thus increasing the reliability of the rotor assembly.
- the increased thermal dissipation of the rotor assembly allows for a higher speed rotation, which may otherwise generate too much heat. A higher speed rotation may result in improved power generation or improved generator efficiency without increasing generator size.
- the embodiments have significantly reduced manufacturing costs due to reduction in the amount of laminated materials, which are typically costly to produce, by replacing the core with a non-laminated material, which is typically less costly to produce. Additionally, by using a solid body core, costs can further be reduced by manufacturing processes such as boring, and auto-winding of the rotor windings. Furthermore, additional cooling tubes and fins may be eliminated from construction and assembly, wherein the prior process of welding the tubes to the assembly provided increases costs.
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Iron Core Of Rotating Electric Machines (AREA)
- Motor Or Generator Cooling System (AREA)
- Insulation, Fastening Of Motor, Generator Windings (AREA)
Abstract
A rotor assembly for an electric machine includes a core and a cap wherein electrical windings are wound about the rotor assembly to define a pole. The rotation of the rotor and rotor pole relative to a stator generates a current supplied from the electric machine to a power consuming device.
Description
- This application claims priority under 35 U.S.C. §119 to International Application No. PCT/US2013/058424, filed Sep. 6, 2013, which is incorporated herein by reference in its entirety.
- Electric machines, such as electric motors and/or electric generators, are used in energy conversion. In the aircraft industry, it is common to find an electric motor having a combination of motor and generator modes, where the electric machine, in motor mode, is used to start an aircraft engine, and, depending on the mode, functions as a generator, too, to supply electrical power to the aircraft systems. Regardless of the mode, the machines typically include a rotor having main windings that are driven to rotate by a source of rotation, such as a mechanical or electrical machine, which for some aircraft may be a gas turbine engine.
- A rotor assembly for an electric machine includes a core having at least one post about which a winding may be wound to define a pole for the electric machine, with the at least one post at least partially defining a winding seat, a cap overlying the post and the winding seat to collectively define an axial extending winding slot with the core, and an interlock removably coupling the cap and the post.
- In the drawings:
-
FIG. 1 is a sectional view of an electric machine capable of operation as a starter/generator and having a rotor assembly according to various aspects described herein. -
FIG. 2 is a partial perspective view of the rotor assembly ofFIG. 1 sectioned along line 2-2 ofFIG. 1 . -
FIG. 3 is an enlarged portion of the area labeled III of the rotor assembly ofFIG. 2 . -
FIG. 4 is a perspective view of a rotor core from the rotor assembly ofFIG. 2 . -
FIG. 5 is a partial sectional view of the rotor assembly according to various aspects described herein. -
FIG. 6 is a partial sectional view of the rotor assembly according to various aspects described herein. -
FIG. 7 is a partial sectional view of the rotor assembly according to various aspects described herein. - While embodiments of the innovation may be implemented in any environment using synchronous electric machine or main machine, a specific example of which is a generator. The generator is currently contemplated to be implemented in a jet engine environment. Embodiments of the innovation may alternatively include a starter/generator and may provide turbine engine starting capabilities, wherein the starter/generator provides the mechanical power to drive the turbine engine through a starting method. A brief summary of the contemplated generator environment should aid in a more complete understanding.
-
FIG. 1 illustrates anelectric machine assembly 10 mounted on or within a gas turbine aircraft engine. The gas turbine engine may be a turbofan engine, such as a General Electric GEnx or CF6 series engine, commonly used in modern commercial and military aviation or it could be a variety of other known gas turbine engines such as a turboprop or turboshaft. - The
electrical machine assembly 10 comprises afirst machine 12 having anexciter rotor 14 and anexciter stator 16, and a synchronoussecond machine 18 having amain machine rotor 20 and amain machine stator 22. At least one power connection is provided on the exterior of theelectrical machine assembly 10 to provide for the transfer of electrical power to and from theelectrical machine assembly 10. Power is transmitted by this power connection, shown as anelectrical power cable 30, directly or indirectly, to the electrical load and may provide for a three phase with a ground reference output from theelectrical machine assembly 10. - The
electrical machine assembly 10 further comprises arotatable shaft 32 mechanically coupled to a source of axial rotation, which may be a gas turbine engine, about an axis ofrotation 34. Therotatable shaft 32 is supported byspaced bearings 36. Theexciter rotor 14 andmain machine rotor 20 are mounted to therotatable shaft 32 for rotation relative to thestators electrical machine assembly 10. Thestators electrical machine assembly 10. Therotatable shaft 32 is configured such that mechanical force from a running turbine engine provides rotation to theshaft 32. Alternatively, in the example of a starter/generator, rotation of therotatable shaft 32 of theelectrical machine assembly 10 during a starting mode produces a mechanical force that is transferred through theshaft 32 to provide rotation to the turbine engine. - The
rotatable shaft 32 may further include acentral coolant passage 28 extending axially along the interior of theshaft 32. Thecentral coolant passage 28 allows coolant, for example, oil or air, to flow through the interior of therotatable shaft 32. In the illustrated embodiment, thesecond machine 18 is located in the rear of theelectric machine assembly 10 and thefirst machine 12 is positioned in the front of theelectric machine assembly 10. Other positions of thefirst machine 12 and thesecond machine 18 are envisioned. -
FIG. 2 illustrates a perspective view of the main machine rotor assembly 40 with at least a portion of the axial front end of the assembly 40 cut away. The rotor assembly 40 is shown comprising acore 42 having at least onepost 44 extending radially from thecore 42, about which a rotor winding 46, which may be electrically isolated from each other, may be wound to define apole 48 for the assembly 40. As shown, each of fourpoles 48 of the rotor assembly 40 includes one rotor winding 46, wound axially about apost 44 to define a rotor winding set 50. Thecore 42 may be, for instance, molded, formed, or bored from a non-laminated or non-lamination, solid or unitary body material. One such example of a core body material may be steel. Alternate body materials and formations of thecore 42 are envisioned, for instance, using additive manufacturing. - Each
pole 48 of the rotor assembly 40 further comprises acap 52. The rotor assembly 40 further comprises additionalradial elements 54 spaced radially about the assembly 40, adjacent to, and in an alternating arrangement with, the multitude ofcaps 52. Eachcap 52 at least partially overlies eachpost 44,pole 48, and rotor winding set 50, and is spaced from eachadjacent cap 52 by theradial element 54, such that thecollective cap 52,radial element 54, andposts 44 of thecore 42 at least partially define an axially extendingwinding slot 56 for receiving therotor windings 46. - Each
cap 52 may be formed or comprised by a plurality of laminations, for instance, cobalt laminations. In this instance, cobalt laminations may comprise thecap 52 due to its high magnetic and electrical resistance properties, and thus, its ability to minimize eddy currents at the surface of eachpole 48. Cobalt laminations are merely one example of a material used to construct thecap 52, and alternate material composition or compositions are envisioned. Comparing thecap 52 to thecore 46, thecap 52 may be less electrically conductive and less thermally conductive than thecore 42. - Each
cap 52 is removably coupled with theposts 44 of thecore 42 via an interlocking of thecap 52 with theposts 44. As shown, the interlock comprises aprojection 58 on thecap 52 and arecess 60 on thepost 44, wherein both thecap projection 58 andpost recess 60 have partially circular, complementary cross sections, such that theprojection 58 is received within thepost recess 60 to removably couple thecap 52 to thepost 44. Alternatively, embodiments are envisioned wherein the interlocking elements are reversed, for example, aprojection 58 on thepost 44, and arecess 60 on thecap 52. - The
core 42 further at least partially definesinternal coolant passages 62 on theposts 44, located adjacent to, and extending axially in parallel with, thewinding slots 56, andradial coolant passages 64 extending radially from the center of thecore 42 to eachinternal coolant passage 62. Theinternal coolant passages 62 may be, for example, molded, formed, or bored into thecore 42, and are at least partially separated from therotor windings 46 by, for instance, a thin portion of thepost 44, allowing for thermal transfer between thewindings 46 and the coolant. Therotatable shaft 32 may additionally include a plurality ofcoolant passage holes 66 that are radially spaced about theshaft 32 such that they align withradial coolant passages 64, and allows for coolant to flow from thecentral coolant passage 28 to and from theradial coolant passages 64. - The assembled
rotatable shaft 32 withcoolant passage holes 66 andcentral coolant passage 28, andcore 42 withinternal coolant passages 62 andradial coolant passages 64 defines a coolant path wherein coolant may fluidly traverse, flow, or be forcibly pumped from thecoolant passage holes 66, through theradial coolant passage 64, to theinternal coolant passage 62, and returned to thecentral coolant passage 28. The rear axial end of the rotor assembly 40 may comprise a duplicate set ofcoolant passage holes 66 andradial coolant passages 64 such that the coolant may traverse, flow, or be forcibly pumped axially along thecentral coolant passage 28 andinternal coolant passages 62 to form a coolant loop. In this example, the entire coolant loop may be internal to thecore 42. Alternative flows, paths, and loops of the coolant through thecoolant passage holes 66,radial coolant passages 64, andinternal coolant passages 62, andcentral coolant passage 28 are envisioned. - Turning now to
FIG. 3 , the rotor assembly 40 is shown further comprising asecond projection 68 on at least a portion of thepost 44 that is keyed to be received in asecond recess 70 of theradial element 54. Thesecond projection 68 andsecond recess 70 have similar cross sections such that theprojection 68 received within therecess 70 to removably couple theradial element 54 to thecore 42. Additionally, theradial element 54 is shown further abutting a biasing element, such as awedge 72, configured such that the coupling of theradial element 54 to thecore 42 biases or secures therotor windings 46 into thewinding slot 56. The biasing of therotor windings 46 into thewinding slot 56 ensures a physical contact between thewindings 46 andslot 56, which serves to enhance the thermal transfer via conduction. Alternative couplings are envisioned wherein removably coupling thecompressive radial 54 to the core 42 biases therotor windings 46 into the windingslot 56. - The core 42 further comprises a winding
seat 74 at the interface of therotor windings 46 and theposts 44, for receiving therotor windings 46. The windingseat 74 may further comprise a thermally conductive, electrically isolatinglayer 76 separating therotor windings 46 from theposts 44. This thermallyconductive layer 76 may be, for example, formed by a coating applied to the windingseat 74. Alternative thermallyconductive layer 76 formations and assemblies are envisioned, such as adhesion by glue, mechanical fastening, etc. Also as shown, theradial coolant passage 64 may further extend along achannel 78 of the windingseat 74, wherein thechannel 78 is not adjacent to theinternal coolant passage 62. Alternatively, thechannel 78 may further comprise additionalinternal coolant passages 62 that run axially along the axis ofrotation 34, parallel to, or intersecting with the existingpassages 62. -
FIG. 4 illustrates one embodiment of thecore 42 of the rotor assembly 40 with thecap 52,radial elements 54,rotor windings 46, and other removable components detached. - During generating operation, the rotor assembly 40 is rotated about the axis of
rotation 34 by a mechanical force, such as a turbine engine, coupled with therotatable shaft 32. During rotation, therotor windings 46 are energized to create apole 48, for example, DC power from a rectified AC power output of theexciter rotor 14. The rotation of thepole 48 relative to themain machine stator 22 generates a power output, such as an AC power output, which is then transmitted by theelectrical power cable 30 to an electrical system, for instance, a power distribution node. - The DC current transmitted through the energized
rotor windings 46 generates heat in thewindings 46. Since thecore 42 is more thermally conductive than thecap 52, a portion of the generated heat is transferred away from the rotor winding 46 via the thermallyconductive layer 76 of the windingseat 74, to thecore 42. Additionally, thewedges 72 bias therotor windings 46 toward the windingseat 74 to ensure a firm thermal conduction interface between thewindings 46 and theseat 74. - The rotor assembly 40 is also configured to remove heat generated in the
rotor windings 46, as well as heat transferred to thecore 42, via the above described coolant paths andloops rotor windings 46 via the thermallyconductive layer 76 directly adjacent to theinternal coolant passages 62. In another instance, the heat generated may be first transferred to the core 42 as described above, and then transferred to the coolant via the coolant paths andloops - As the rotor assembly 40 rotates at the anticipated high rotations per minute (RPMs), the centrifugal forces tend to push the
rotor windings 46 radially outward, which may create a gap between the thermallyconductive layer 76 and thewindings 46. This thermal transfer by convection across the gap between therotor windings 46 and the thermallyconductive layer 76 is less effective, and thus, undesirable. The collective coupling of thecap 52, theradial element 54, and thewedges 74 to the rotor assembly 40 tend to oppose the centrifugal forces on therotor windings 46, and help improve the thermal transfer from thewindings 46 to the coolant via conduction, by ensuring the winding 46 stays in place and in contact with the thermallyconductive layer 76 of the windingseat 74. - Additionally, during generating operation, the rotation of the rotor assembly 40 relative to the
main machine stator 22 typically causes eddy current losses due to the changing magnetic field and/or magnetic flux harmonics in the air gap between theenergized poles 48 andstator 22. Since these eddy current losses occur mainly at or near thepole 48 surface, the losses may be minimized due to the lamination structure of thecap 52, which is less electrically conductive, and thus less magnetically affected, by the losses. Fewer eddy current losses also results in less heat generated by the losses at or near thepole 48 surface. - During generating operation, the
projection 58 andrecess 60 also provides a secured interlocking of thecap 52 to theposts 44 and thecore 42. For instance, during rotation, centrifugal forces may attempt to separate thecap 52 from theposts 44 andcore 42. The interlocking of thecap 52 to theposts 44 and the core 42 by the interlockedprojection 58 and therecess 60 prevents or retards this separation. Also, the interlocking of thecap 52 to theposts 44 and thecore 42 provides an anti-rotation lock configured to retard the relative rotation of thecap 52 and thepost 44. The assembly of theradial elements 54 further support the anti-rotation lock configuration. -
FIG. 5 illustrates analternative rotor assembly 140 according to a second embodiment of the innovation. The second embodiment is similar to the first embodiment; therefore, like parts will be identified with like numerals increased by 100, with it being understood that the description of the like parts of the first embodiment applies to the second embodiment, unless otherwise noted. A difference between the first embodiment and the second embodiment is that thecap 152 alternatively comprises at least a partialtrapezoidal projection 158 cross section. Correspondingly, thecore 142 will have a complementary trapezoidal cross section in therecess 160 of thepost 144 for removably coupling thecap 152 to thecore 142. Alternate trapezoidal, or otherwise interlocking cross sections, are envisioned -
FIG. 6 illustrates analternative rotor assembly 240 according to a third embodiment of the innovation. The third embodiment is similar to the first and second embodiments; therefore, like parts will be identified with like numerals increased by 200, with it being understood that the descriptions of the like parts of the first and second embodiments apply to the third embodiment, unless otherwise noted. A difference between the third embodiment and the first and second embodiments is that thecap 252 further comprises at least a second projection, shown as acorner finger 290 spaced from and on each side of theprojection 158, extending from thecap 252, and abutting the opposing corners of thepost 244 of thecore 242. As illustrated, thecorner fingers 290 have at least a partial trapezoidal cross section, but may have alternative cross sections for removably coupling to and/or interlocking with thecore 242. Correspondingly, thecore 242 will have a complementary cross section in at least a second recess, such as acorner finger channel 292 of thepost 244. - Alternatively, embodiments are envisioned wherein the interlocking elements are reversed, for example,
corner fingers 290 on thepost 244, and acorner finger channels 292 on thecap 252. Additionally, while twocorner fingers 290 and correspondingcorner finger channels 292 are shown, alternative numbers ofcorner fingers 290 and correspondingcorner finger channels 292 are envisioned. - The
corner fingers 290 may further provide secured interlocking of thecap 252 to thecore 242 during generating operation. During rotation, centrifugal forces may attempt to separate thecap 252 ends, farthest from thepole 48, from theposts 244 andcore 242. The additional interlocking of thecap 252 to thecore 242 by thecorner fingers 290 and correspondingcorner finger channels 292 further secures thecap 252 ends, preventing separation. Also, the additional interlocking of thecap 252 to thecore 242 by thecorner fingers 290 and correspondingcorner finger channels 292 provides an additional anti-rotation lock configured to retard the relative rotation of thecap 252 andpost 244. -
FIG. 7 illustrates analternative rotor assembly 340 according to a fourth embodiment of the innovation. The fourth embodiment is similar to the first, second, and third embodiments; therefore, like parts will be identified with like numerals increased by 300, with it being understood that the descriptions of the like parts of the first, second, and third embodiments apply to the fourth embodiment, unless otherwise noted. A difference between the fourth embodiment and the first, second, and third embodiments is that thecorner fingers 390 of thecap 352 are spaced from and on each side of theprojection 158, extending fromcap 352, but not abutting the opposing corners of thepost 344 of thecore 342. As illustrated, thecorner fingers 390 have at least a partial trapezoidal cross section, but may have alternative cross sections for removably coupling to and/or interlocking with thecore 342. Correspondingly, thecorner finger channel 392 of thepost 344 will have a complementary cross section. Alternatively, embodiments are envisioned wherein the interlocking elements are reversed, for example,corner fingers 390 on thepost 344, and acorner finger channels 392 on thecap 352. Additionally, while twocorner fingers 390 and correspondingcorner finger channels 392 are shown, alternative numbers ofcorner fingers 390 and correspondingcorner finger channels 392 are envisioned. - Many other possible embodiments and configurations in addition to that shown in the above figures are contemplated by the present disclosure. For example, one embodiment of the innovation contemplates more or fewer of the
electrical machine assembly 10 components mentioned, such aspoles 48, caps 52,rotor windings 46, etc. Another embodiment of the innovation contemplates usingwedges 72 configured on different sides of therotor windings 46 to bias thewindings 46 into the windingseats 74. Alternatively,additional wedges 72 may be included to bias more than one side of therotor windings 46 into the windingseats 74. Another embodiment of the innovation contemplates additional coolant passage holes 66 andradial coolant passages 64 spaced axially along therotatable shaft 32, such that additional coolant paths and/or loops may be utilized to improve cooling. Additionally, the design and placement of the various components may be rearranged such that a number of different in-line configurations could be realized. - In yet another embodiment of the innovation, the rotor windings set 50 and winding
seats 74 may be configured with, for instance a 10° clockwise and counter-clockwise rotation, compared to the illustrated example. It is envisioned that, for instance, therotor windings 46 on one side of thepole 44 may be configured in a counter-clockwise orientation, while the correspondingwindings 46 on the opposing side of the pole may be configured in a clockwise orientation. In this example, each rotatedrotor windings 46 may be held in place by one ormore wedges 72, to ensure thermal contact between thewindings 46 and the windingseat 74. Also, additional components such as thecap 52 and thermallyconductive layer 76 may also include slightly angled surfaces to match the rotatedrotor windings 46. A 10° counter-clockwise rotation is one example of a configuration, and other angles are envisioned in both a clockwise and counter-clockwise direction. - The embodiments disclosed herein provide a generator rotor with a cap and core assembly. One advantage that may be realized in the above embodiments is that the above described embodiments have significantly improved thermal conduction to remove heat from the assembly. The improved thermal conductivity of the core, compared to a core comprising laminated materials, coupled with the coolant paths and/or loops provide for heat removal in a much more effective fashion from the windings to the coolant. Another advantage of the above embodiments is that the thermally conductive layer replaces the typical slot liner in the rotor in a way to provide improved mechanical integrity, along with improved thermal conductivity. The thermally conductive layer also replaces thermal conduction or cooling tubes and/or fins, reducing the number of parts, and thus increasing the reliability of the rotor assembly. The increased thermal dissipation of the rotor assembly allows for a higher speed rotation, which may otherwise generate too much heat. A higher speed rotation may result in improved power generation or improved generator efficiency without increasing generator size.
- Yet another advantage of the above embodiments is that the embodiments have significantly reduced manufacturing costs due to reduction in the amount of laminated materials, which are typically costly to produce, by replacing the core with a non-laminated material, which is typically less costly to produce. Additionally, by using a solid body core, costs can further be reduced by manufacturing processes such as boring, and auto-winding of the rotor windings. Furthermore, additional cooling tubes and fins may be eliminated from construction and assembly, wherein the prior process of welding the tubes to the assembly provided increases costs.
- When designing aircraft components, important factors to address are size, weight, and reliability. The above described rotor assemblies have a decreased number of parts, making the complete system inherently more reliable. This results in possibly a lower weight, smaller sized, increased performance, and increased reliability system. The lower number of parts and reduced maintenance will lead to a lower product costs and lower operating costs. Reduced weight and size correlate to competitive advantages during flight.
- To the extent not already described, the different features and structures of the various embodiments may be used in combination with each other as desired. That one feature may not be illustrated in all of the embodiments is not meant to be construed that it may not be, but is done for brevity of description. Thus, the various features of the different embodiments may be mixed and matched as desired to form new embodiments, whether or not the new embodiments are expressly described. All combinations or permutations of features described herein are covered by this disclosure.
- This written description uses examples to disclose the innovation, including the best mode, and also to enable any person skilled in the art to practice the innovation, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the innovation is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (15)
1. A rotor assembly for an electric machine comprising:
a core having at least one post about which a winding may be wound to define a pole for the electric machine, with the at least one post at least partially defining a winding seat;
a cap overlying the post and the winding seat to collectively define an axial extending winding slot with the core; and
an interlock removably coupling the cap and the post.
2. The rotor assembly of claim 1 wherein the interlock comprises a projection on one of the cap and the post and a recess on the other of the cap and the post, wherein the projection is received within the recess to removably couple the cap to the post.
3. The rotor assembly of claim 2 wherein the projection and the recess have complementary cross sections.
4. The rotor assembly of claim 3 wherein the complementary cross sections are at least one of: at least partially circular or at least partially trapezoidal.
5. The rotor assembly of claim 2 wherein the interlock further comprises at least one corner finger extending from one of the cap and the post and abutting a corner of the other of the cap and the post.
6. The rotor assembly of claim 5 wherein the corner finger is spaced from the projection.
7. The rotor assembly of claim 6 wherein there are at least two corner fingers, with at least one corner finger on each side of the projection.
8. The rotor assembly of claim 7 wherein the projection extends from the cap, a corresponding recess is formed in the post, and the corner fingers extend from the cap and abut opposing corners on the post.
9. The rotor assembly of claim 8 wherein the post comprises a channel along at least one corner and the corresponding finger is received within the channel.
10. The rotor assembly of claim 1 further comprising an anti-rotation lock configured to retard the relative rotation of the cap and the post.
11. The rotor assembly of claim 10 wherein the anti-rotation lock comprises at least one corner finger extending from one of the cap and the post and abutting a corner of the other of the cap and the post.
12. The rotor assembly of claim 10 wherein the core comprises at least one of a solid body or a unitary body.
13. The rotor assembly of claim 1 wherein the cap comprises a plurality of laminations and the core does not comprise a plurality of laminations.
14. The rotor assembly of claim 1 wherein the core comprises at least one internal cooling passage adjacent at least a portion of the winding slot.
15. The rotor assembly of claim 1 wherein the core further comprises a thermal conductor provided on the winding seat.
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PCT/US2013/068299 WO2015034544A2 (en) | 2013-09-06 | 2013-11-04 | Rotor assembly for an electric machine |
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US15/029,917 Active 2034-03-18 US10554088B2 (en) | 2013-09-06 | 2013-11-04 | Rotor assembly for an electric machine having a coolant passage |
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Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10424989B2 (en) | 2017-01-13 | 2019-09-24 | General Electric Company | Methods for manufacturing a housing for an electrical machine |
US10476358B2 (en) | 2017-01-13 | 2019-11-12 | General Electric Company | Methods for manufacturing an electric machine |
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Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2922185A1 (en) * | 2014-03-21 | 2015-09-23 | Siemens Aktiengesellschaft | Cooling of an active part of an electric machine |
DE102014226129B3 (en) * | 2014-12-16 | 2016-02-04 | Magna powertrain gmbh & co kg | Electric machine, stator for an electric machine and vehicle |
US9653958B2 (en) | 2015-01-16 | 2017-05-16 | Hamilton Sundstrand Corporation | Rotor wedge with arms |
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US11837917B2 (en) | 2022-01-28 | 2023-12-05 | Ge Aviation Systems Llc | Method and apparatus for cooling a rotor assembly |
US11984766B2 (en) | 2022-01-28 | 2024-05-14 | Ge Aviation Systems Llc | Method and apparatus for cooling a rotor assembly |
Citations (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2386673A (en) * | 1944-06-10 | 1945-10-09 | Gen Electric | Winding slot wedge |
US2736829A (en) * | 1952-10-11 | 1956-02-28 | Gen Electric Canada | Dynamoelectric machine rotor |
US3235758A (en) * | 1962-04-02 | 1966-02-15 | Ampex | Controlled drive mechanisms |
US4862024A (en) * | 1987-12-14 | 1989-08-29 | United Technologies Corp. | Heat dissipation in an electric motor |
US5932948A (en) * | 1998-09-22 | 1999-08-03 | Caterpillar Inc. | Rotor V-block assembly |
US20030030333A1 (en) * | 2001-08-08 | 2003-02-13 | Johnsen Tyrone A. | Cooling of a rotor for a rotary electric machine |
US20050253476A1 (en) * | 2004-05-14 | 2005-11-17 | Ping Zhong | Pole body and pole tip connections used with rotating machines |
US20070063612A1 (en) * | 2005-09-16 | 2007-03-22 | Sinhan Precision Ind. Co., Ltd. | Motor rotor having insulator including glass fiber |
US7492073B2 (en) * | 2006-06-30 | 2009-02-17 | General Electric Company | Superconducting rotating machines with stationary field coils |
US7687928B2 (en) * | 2006-06-14 | 2010-03-30 | Smiths Aerospace, Llc | Dual-structured aircraft engine starter/generator |
US20100295411A1 (en) * | 2009-05-20 | 2010-11-25 | Gm Global Technology Operations, Inc. | Methods and apparatus for a continuous wound laminate rotor flux path |
US20100295301A1 (en) * | 2009-05-19 | 2010-11-25 | Hao Huang | Aircraft engine starting/generating system and method of control |
US20120025639A1 (en) * | 2010-07-30 | 2012-02-02 | Jan Zywot | Apparatus for a high speed sleeveless rotor |
US20120126643A1 (en) * | 2010-11-19 | 2012-05-24 | Ping Zhong | Apparatuses useful for cooling windings of rotor assemblies |
US20140265660A1 (en) * | 2013-03-15 | 2014-09-18 | Teco Westinghouse Motor Company | Assemblies and Methods for Cooling Electric Machines |
Family Cites Families (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US918498A (en) * | 1907-06-08 | 1909-04-20 | Bullock Electric Company | Revolving field-magnet structure. |
JPS5594549A (en) | 1979-01-11 | 1980-07-18 | Toshiba Corp | Salient-pole rotor |
JPS55173255U (en) | 1979-05-29 | 1980-12-12 | ||
JPS5666146A (en) | 1979-11-02 | 1981-06-04 | Hitachi Ltd | Field device of electric rotary machine |
JPS5721240U (en) | 1980-07-09 | 1982-02-03 | ||
JPS5877009U (en) | 1981-11-19 | 1983-05-24 | 神鋼電機株式会社 | Laminated core for electrical equipment |
JPS5913544U (en) | 1982-07-20 | 1984-01-27 | 石川島建材工業株式会社 | Trailer coupling device in trailer three-dimensional storage system |
JPS59103544U (en) * | 1982-12-27 | 1984-07-12 | 株式会社東芝 | salient pole rotor |
DE59003435D1 (en) | 1989-08-29 | 1993-12-16 | Asea Brown Boveri | Arrangement for guiding the cooling medium in salient pole machines. |
DE9003390U1 (en) * | 1990-03-20 | 1990-06-21 | Siemens AG, 1000 Berlin und 8000 München | Electric synchronous machine with a salient pole rotor |
US5189325A (en) * | 1990-06-15 | 1993-02-23 | General Electric Company | Liquid cooling the rotor of an electrical machine |
JPH06351203A (en) | 1993-06-10 | 1994-12-22 | Toshiba Corp | Lump-shaped salient-pole synchronous motor |
GB9505072D0 (en) * | 1995-03-14 | 1995-05-03 | Lucas Ind Plc | A winding end support for a rotary electrical component |
JPH09247879A (en) | 1996-03-06 | 1997-09-19 | Toshiba Corp | Salient-pole type electric rotating machine |
JP2000166139A (en) | 1998-11-24 | 2000-06-16 | Nishishiba Electric Co Ltd | Salient-pole electric rotating machine |
US6727634B2 (en) * | 2001-08-30 | 2004-04-27 | Honeywell International, Inc. | System and method for end turn retention on a high speed generator rotor |
JP2004088876A (en) | 2002-08-26 | 2004-03-18 | Tma Electric Corp | Rotor for dynamo electric machine |
US6794792B2 (en) * | 2002-11-13 | 2004-09-21 | General Electric Company | Cold structural enclosure for multi-pole rotor having super-conducting field coil windings. |
GB0314636D0 (en) | 2003-06-24 | 2003-07-30 | Goodrich Control Sys Ltd | Dynamo electric machines |
US6952070B1 (en) * | 2004-04-29 | 2005-10-04 | General Electric Company | Capped flat end windings in an electrical machine |
JP2007189849A (en) | 2006-01-16 | 2007-07-26 | Toshiba Mitsubishi-Electric Industrial System Corp | Rotor of salient pole electric rotating machine |
US20090009012A1 (en) | 2007-07-03 | 2009-01-08 | General Electric Company | Assembly and method for magnetization of permanent magnet rotors in electrical machines |
JP2009136063A (en) | 2007-11-29 | 2009-06-18 | Nishishiba Electric Co Ltd | Rotor of salient-pole type rotary electric machine |
US20110025160A1 (en) | 2009-08-03 | 2011-02-03 | Gm Global Technology Operations, Inc. | Rectangular cross-section windings for electrical machine rotors |
US7821171B2 (en) | 2008-12-02 | 2010-10-26 | Hamilton Sundstrand Corporation | Generator wedge with reduced eddy current losses |
US8018114B2 (en) | 2009-03-26 | 2011-09-13 | Hamilton Sundstrand Corporation | Generator rotor with improved wedges |
CN201781344U (en) | 2010-09-09 | 2011-03-30 | 上海电气集团上海电机厂有限公司 | Interelectrode-wiring structure of high-speed motor rotor |
FR2981220B1 (en) | 2011-10-06 | 2014-06-27 | Leroy Somer Moteurs | ROTOR COMPRISING POLAR COAL CHANNEL FLURRIES. |
WO2013076791A1 (en) | 2011-11-21 | 2013-05-30 | トヨタ自動車株式会社 | Rotating electric machine |
DE102011121793B4 (en) | 2011-12-21 | 2017-05-24 | Sew-Eurodrive Gmbh & Co Kg | electric motor |
US9559569B2 (en) | 2012-02-13 | 2017-01-31 | Ge Aviation Systems Llc | Arrangement for cooling an electric machine with a layer of thermally conducting and electrically insulating material |
US9203284B2 (en) * | 2012-02-14 | 2015-12-01 | GM Global Technology Operations LLC | Rotor cooling structures |
KR101558349B1 (en) * | 2013-05-20 | 2015-10-08 | 현대자동차 주식회사 | Rotor structure of drive motor |
WO2015034514A1 (en) | 2013-09-06 | 2015-03-12 | Ge Aviation Systems Llc | Rotor assembly for an electric machine |
US9041232B2 (en) * | 2013-10-11 | 2015-05-26 | General Electric Company | Electric generator system |
US20160211715A1 (en) | 2015-01-16 | 2016-07-21 | Hamilton Sundstrand Corporation | Rotor wedge for a generator |
-
2013
- 2013-09-06 WO PCT/US2013/058424 patent/WO2015034514A1/en active Application Filing
- 2013-09-06 EP EP13762971.3A patent/EP3042442A1/en active Pending
- 2013-09-06 CN CN201380079387.8A patent/CN105637744B/en active Active
- 2013-09-06 CA CA2922464A patent/CA2922464A1/en not_active Abandoned
- 2013-09-06 US US14/916,700 patent/US10523079B2/en active Active
- 2013-09-06 JP JP2016540859A patent/JP6334711B2/en not_active Expired - Fee Related
- 2013-11-04 CA CA2928465A patent/CA2928465A1/en not_active Abandoned
- 2013-11-04 CN CN201380080795.5A patent/CN105706336A/en active Pending
- 2013-11-04 US US15/027,464 patent/US20160352174A1/en not_active Abandoned
- 2013-11-04 EP EP13792816.4A patent/EP3044851A2/en not_active Ceased
- 2013-11-04 US US15/029,917 patent/US10554088B2/en active Active
- 2013-11-04 EP EP13792815.6A patent/EP3042436A2/en not_active Withdrawn
- 2013-11-04 WO PCT/US2013/068299 patent/WO2015034544A2/en active Application Filing
- 2013-11-04 CN CN201380080797.4A patent/CN105706345B/en active Active
- 2013-11-04 WO PCT/US2013/068307 patent/WO2015034545A2/en active Application Filing
- 2013-11-04 CA CA2928462A patent/CA2928462A1/en not_active Abandoned
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2386673A (en) * | 1944-06-10 | 1945-10-09 | Gen Electric | Winding slot wedge |
US2736829A (en) * | 1952-10-11 | 1956-02-28 | Gen Electric Canada | Dynamoelectric machine rotor |
US3235758A (en) * | 1962-04-02 | 1966-02-15 | Ampex | Controlled drive mechanisms |
US4862024A (en) * | 1987-12-14 | 1989-08-29 | United Technologies Corp. | Heat dissipation in an electric motor |
US5932948A (en) * | 1998-09-22 | 1999-08-03 | Caterpillar Inc. | Rotor V-block assembly |
US20030030333A1 (en) * | 2001-08-08 | 2003-02-13 | Johnsen Tyrone A. | Cooling of a rotor for a rotary electric machine |
US20050253476A1 (en) * | 2004-05-14 | 2005-11-17 | Ping Zhong | Pole body and pole tip connections used with rotating machines |
US20070063612A1 (en) * | 2005-09-16 | 2007-03-22 | Sinhan Precision Ind. Co., Ltd. | Motor rotor having insulator including glass fiber |
US7687928B2 (en) * | 2006-06-14 | 2010-03-30 | Smiths Aerospace, Llc | Dual-structured aircraft engine starter/generator |
US7492073B2 (en) * | 2006-06-30 | 2009-02-17 | General Electric Company | Superconducting rotating machines with stationary field coils |
US20100295301A1 (en) * | 2009-05-19 | 2010-11-25 | Hao Huang | Aircraft engine starting/generating system and method of control |
US8148834B2 (en) * | 2009-05-19 | 2012-04-03 | General Electric Company | Aircraft engine starting/generating system and method of control |
US20100295411A1 (en) * | 2009-05-20 | 2010-11-25 | Gm Global Technology Operations, Inc. | Methods and apparatus for a continuous wound laminate rotor flux path |
US20120025639A1 (en) * | 2010-07-30 | 2012-02-02 | Jan Zywot | Apparatus for a high speed sleeveless rotor |
US8232702B2 (en) * | 2010-07-30 | 2012-07-31 | Ge Aviation Systems, Llc | Apparatus for a high speed sleeveless rotor |
US20120126643A1 (en) * | 2010-11-19 | 2012-05-24 | Ping Zhong | Apparatuses useful for cooling windings of rotor assemblies |
US20140265660A1 (en) * | 2013-03-15 | 2014-09-18 | Teco Westinghouse Motor Company | Assemblies and Methods for Cooling Electric Machines |
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US10554088B2 (en) | 2013-09-06 | 2020-02-04 | Ge Aviation Systems Llc | Rotor assembly for an electric machine having a coolant passage |
US10424989B2 (en) | 2017-01-13 | 2019-09-24 | General Electric Company | Methods for manufacturing a housing for an electrical machine |
US10476358B2 (en) | 2017-01-13 | 2019-11-12 | General Electric Company | Methods for manufacturing an electric machine |
US10523096B2 (en) | 2017-01-13 | 2019-12-31 | Ge Aviation Systems Llc | Method for manufacturing a stator assembly of an electrical machine |
US10792750B2 (en) | 2017-01-13 | 2020-10-06 | Ge Aviation Systems Llc | Methods for manufacturing a rotor assembly for an electrical machine |
US11177708B2 (en) | 2017-01-13 | 2021-11-16 | Ge Aviation Systems Llc | Method for manufacturing an integrated stator and housing for an electrical machine |
US11081920B2 (en) | 2017-09-29 | 2021-08-03 | Hamilton Sundstrand Corporation | Rotor wedges and layers and heat sinks |
US20210336501A1 (en) * | 2017-09-29 | 2021-10-28 | Hamilton Sundstrand Corporation | Rotor wedges and methods of making rotor wedges |
US10826363B2 (en) | 2018-05-10 | 2020-11-03 | Ge Aviation Systems Llc | Additively manufactured assemblies for electrical machines |
EP3916963A1 (en) * | 2020-05-28 | 2021-12-01 | Honeywell International Inc. | Conformal cooling devices for rotating generator elements and additive manufacturing processes for fabricating the same |
US11552523B2 (en) | 2020-05-28 | 2023-01-10 | Honeywell International Inc. | Conformal cooling devices for rotating generator elements and additive manufacturing processes for fabricating the same |
Also Published As
Publication number | Publication date |
---|---|
WO2015034545A3 (en) | 2015-10-01 |
CA2928465A1 (en) | 2015-03-12 |
EP3042442A1 (en) | 2016-07-13 |
US10554088B2 (en) | 2020-02-04 |
CN105637744A (en) | 2016-06-01 |
CA2928462A1 (en) | 2015-03-12 |
CN105706336A (en) | 2016-06-22 |
JP6334711B2 (en) | 2018-05-30 |
US10523079B2 (en) | 2019-12-31 |
CN105706345A (en) | 2016-06-22 |
CA2922464A1 (en) | 2015-03-12 |
WO2015034545A2 (en) | 2015-03-12 |
WO2015034544A3 (en) | 2015-09-24 |
CN105706345B (en) | 2019-02-22 |
US20160204663A1 (en) | 2016-07-14 |
WO2015034544A2 (en) | 2015-03-12 |
US20160285332A1 (en) | 2016-09-29 |
EP3042436A2 (en) | 2016-07-13 |
EP3044851A2 (en) | 2016-07-20 |
WO2015034514A1 (en) | 2015-03-12 |
CN105637744B (en) | 2019-11-15 |
JP2016530869A (en) | 2016-09-29 |
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