WO2014081829A2 - Ensemble rotor et son procédé d'utilisation - Google Patents

Ensemble rotor et son procédé d'utilisation Download PDF

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Publication number
WO2014081829A2
WO2014081829A2 PCT/US2013/071005 US2013071005W WO2014081829A2 WO 2014081829 A2 WO2014081829 A2 WO 2014081829A2 US 2013071005 W US2013071005 W US 2013071005W WO 2014081829 A2 WO2014081829 A2 WO 2014081829A2
Authority
WO
WIPO (PCT)
Prior art keywords
sleeve
channel
magnetic attachment
rotor shaft
sleeve apparatus
Prior art date
Application number
PCT/US2013/071005
Other languages
English (en)
Other versions
WO2014081829A3 (fr
Inventor
John Kuczaj
Original Assignee
Turbogen, Llc
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 Turbogen, Llc filed Critical Turbogen, Llc
Publication of WO2014081829A2 publication Critical patent/WO2014081829A2/fr
Publication of WO2014081829A3 publication Critical patent/WO2014081829A3/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/026—Shaft to shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C3/00—Shafts; Axles; Cranks; Eccentrics
    • F16C3/02—Shafts; Axles
    • F16C3/023—Shafts; Axles made of several parts, e.g. by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C32/00—Bearings not otherwise provided for
    • F16C32/04—Bearings not otherwise provided for using magnetic or electric supporting means
    • F16C32/0406—Magnetic bearings
    • F16C32/0408—Passive magnetic bearings
    • 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
    • H02K7/003—Couplings; Details of 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • 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
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H02K7/1807—Rotary generators
    • H02K7/1823—Rotary generators structurally associated with turbines or similar engines

Definitions

  • the field of the invention relates generally to power systems and, more particularly, to a rotor assembly that may be used in power systems.
  • At least some known systems use at least one turbine engine that is coupled to a load, wherein the load is an electrical system, such as an electrical generator or inverter.
  • a rotating element such as a drive shaft, of the turbine engine is coupled to a rotor shaft of the generator.
  • the drive shaft rotates to enable the turbine engine to generate mechanical rotational energy.
  • the generator rotor shaft rotates and the generator is able to convert the mechanical energy to electrical energy.
  • Some power systems may use high speed generators to facilitate an increased power density.
  • high speed generators When using high speed generators, relatively high rotational speeds are implemented by the rotor shaft of the generator. The rotational speeds result in centrifugal forces being applied to the rotor shaft. The centrifugal forces cause mechanical stress on the rotor shaft, which may cause misalignment of rotor shaft and/or the generator with respect to the drive shaft and/or the turbine engine. Such misalignment may lead to a failure of at least one component of the power system and/or adversely affect the operation of the power system. [0005] Accordingly, there is a need for a rigid rotor apparatus or system that may be used with high speed generators that is configured to facilitate a secure connection with a turbine engine and to maintain proper alignment during operation.
  • a rotor assembly generally comprises a sleeve apparatus that includes a first sleeve portion and a second sleeve portion positioned a predefined distance from the first sleeve portion.
  • the sleeve apparatus also includes at least one channel defined between the first sleeve portion and the second sleeve portion.
  • a rotor shaft is coupled to the sleeve apparatus such that at least a portion of the rotor shaft is positioned within the sleeve apparatus, wherein the rotor shaft includes an end portion that is configured to be removably coupled to a drive shaft.
  • At least one magnetic attachment is removably coupled within the channel to facilitate maintaining the rotor shaft in alignment within the sleeve apparatus during operation of the rotor assembly.
  • a power system in another embodiment, generally comprises a turbine engine that includes a drive shaft and a load that is coupled to the turbine engine.
  • the load includes a rotor assembly that includes a sleeve apparatus having a first sleeve portion and a second sleeve portion positioned a predefined distance from the first sleeve portion.
  • the sleeve apparatus also includes at least one channel defined between the first sleeve portion and the second sleeve portion.
  • a rotor shaft is coupled to the sleeve apparatus such that at least a portion of the rotor shaft is positioned within the sleeve apparatus, wherein the rotor shaft includes an end portion that is configured to be removably coupled to the drive shaft. At least one magnetic attachment is removably coupled within the channel to facilitate maintaining the rotor shaft in alignment within the sleeve apparatus during operation of the rotor assembly.
  • a method for using a rotor assembly is provided.
  • a sleeve apparatus is provided, wherein the sleeve apparatus includes a first sleeve portion and a second sleeve portion positioned a predefined distance from the first sleeve portion.
  • the sleeve apparatus further includes at least one channel defined between the first sleeve portion and the second sleeve portion.
  • At least a portion of a rotor shaft is positioned within the sleeve apparatus, wherein the rotor shaft includes an end portion that is configured to be removably coupled to a drive shaft.
  • At least one magnetic attachment is removably coupled within the channel to facilitate maintaining the rotor shaft in alignment within the sleeve apparatus during operation of the rotor assembly.
  • FIG. 1 is a block diagram of an exemplary power system
  • FIG. 2 is a perspective view of an exemplary rotor assembly that may be used with the power system shown in FIG. 1 and taken from area 2;
  • FIG. 3 is an exploded view of the rotor assembly shown in
  • the exemplary apparatus, systems, and methods described herein provide a substantially rigid rotor assembly that may be used with a load, such as a high speed generator, wherein the rotor assembly is configured to facilitate a secure connection with a turbine engine, and the rotor assembly is configured to maintain proper alignment during operation.
  • the rotor assembly generally comprises a sleeve apparatus that includes at least one channel.
  • a rotor shaft is coupled to the sleeve apparatus such that at least a portion of the rotor shaft is positioned within the sleeve apparatus.
  • the rotor shaft includes an end portion that is configured to be removably coupled to, for example, a drive shaft of a turbine engine.
  • FIG. 1 illustrates an exemplary power system 100.
  • the power system 100 includes a turbine engine 102. More specifically, in the exemplary embodiment, the turbine engine 102 is a gas turbine engine. While the exemplary embodiment includes a gas turbine engine, the present invention is not limited to any one particular engine, and one of ordinary skill in the art will appreciate that the current disclosure may be used in connection with other engines.
  • the turbine engine 102 includes an intake section 1 12, a compressor section 1 14 coupled downstream from the intake section 1 12, a combustor section 1 16 coupled downstream from the compressor section 1 14, a turbine section 118 coupled downstream from the combustor section 1 16, and an exhaust section 120.
  • the term "couple” is not limited to a direct mechanical, thermal, communication, and/or an electrical connection between components, but may also include an indirect mechanical, thermal, communication and/or electrical connection between multiple components.
  • the turbine section 1 18, in the exemplary embodiment, is coupled to the compressor section 1 14 via a drive shaft 122.
  • the combustor section 1 16 includes a plurality of combustors 124.
  • the combustor section 1 16 is coupled to the compressor section 1 14 such that each combustor 124 is positioned in flow communication with the compressor section 114.
  • the turbine section 1 18 is coupled to the compressor section 1 14 and to at least one load 128 via the drive shaft 122.
  • the load 128 may be an electrical system, such as a high speed electrical generator.
  • the load 128 may be enclosed with a housing apparatus (not shown), such as the housing apparatus described in co-pending U. S. Patent Application No.
  • the load 128 may also be a part of a load apparatus (not shown), which may be the load apparatus that is described in co-pending U.S. Patent Application No. 13/682,313 entitled LOAD APPARATUS AND METHOD OF USING SAME (attorney docket no. F9941-00005), filed November 20, 2012, which is incorporated herein by reference in its entirety.
  • the load 128 includes a rotor assembly 130 that includes a rotor shaft (not shown in FIG. 1) that is coupled to the drive shaft 122 of the turbine engine 102.
  • the compressor section 1 14 and the turbine section 118 includes at least one rotor disk assembly (not shown) that is coupled to the drive shaft 122.
  • the intake section 112 channels air towards the compressor section 1 14 wherein the air is compressed to a higher pressure and temperature prior to being discharged towards the combustor section 116.
  • the compressed air is mixed with fuel and other fluids and ignited to generate combustion gases that are channeled towards the turbine section 118.
  • fuel such as natural gas and/or fuel oil, air, diluents, and/or Nitrogen gas (N 2 )
  • N 2 Nitrogen gas
  • the blended mixtures are ignited to generate high temperature combustion gases that are channeled towards the turbine section 118.
  • the turbine section 1 18 converts the thermal energy from the gas stream to mechanical rotational energy, as the combustion gases impart rotational energy to the turbine section 1 18 and to the rotor disk assembly.
  • the mechanical rotational energy is converted to electrical energy via the load 128.
  • the mechanical rotational energy that is generated by the turbine section 1 18 is enabled by the rotation of the drive shaft 122.
  • the rotor assembly 128 rotates. More specifically, the rotor shaft of the rotor assembly 130 rotates. Due to the high rotational speeds implemented by the drive shaft and/or the rotor shaft, mechanical stress may be endured by the rotor shaft. The mechanical stress may cause misalignment of the rotor shaft, the rotor assembly 130, and/or the load 128 with respect to the drive shaft 122 and/or the turbine engine 102.
  • the rotor assembly 130 is substantially rigid and facilitates a secure coupling between the rotor shaft and the drive shaft 122 of the turbine engine 102. The rotor assembly also maintains proper alignment during operation.
  • FIG. 2 is a perspective view of the rotor assembly 130 taken from area 2 (shown in FIG. 1).
  • FIG. 3 is an exploded view of the rotor assembly 130.
  • the rotor assembly 130 includes a sleeve apparatus 200 having a first sleeve portion 202 and a second sleeve portion 204 that is positioned a predefined distance 206 from the first sleeve portion 202. While only one two sleeve portions 202 and 204 are illustrated in the exemplary embodiment, the sleeve apparatus 200 may have any suitable number of sleeve portions that enable the rotor assembly 130 and/or the power system 100 to function as described herein.
  • the first sleeve portion 202 includes an outer sleeve 201 and an inner sleeve 203 that are each substantially cylindrical, wherein the outer diameter of the inner sleeve 203 is smaller than the inner diameter of the outer sleeve 201.
  • the second sleeve portion 204 includes an outer sleeve 205 and an inner sleeve 207 that are each substantially cylindrical, wherein the diameter (not shown) of the inner sleeve 207 is smaller than the diameter of the outer sleeve 205.
  • each outer sleeve 201 and 205 and each inner sleeve 203 and 207 may have any suitable shape and size that enables the rotor assembly 130 and/or the power system 100 (shown in FIG. 1) to function as described herein.
  • the outer sleeve 201 of the first sleeve portion 202 includes an opening (not shown) extending therethrough and the inner sleeve 203 includes an opening (not shown) that is substantially concentrically aligned with the opening of the outer sleeve 201.
  • the outer sleeve 205 of the second sleeve portion 204 includes an opening 209 and the inner sleeve 207 includes an opening (not shown) that is substantially concentrically aligned with the opening of the outer sleeve 205.
  • the first sleeve portion 202 is oriented with respect to the second sleeve portion 204 such that the openings of the outer sleeve 201 and the inner sleeve 203 of the first sleeve portion 202 are each substantially coaxially aligned with the openings of the outer sleeve 205 and the inner sleeve 207 of the second sleeve portion 204.
  • first sleeve portion 202 and the second sleeve portion 204 are coupled together with at least one support leg, such as a first support leg 214 and a second support leg 216.
  • Each support leg 214 and 216 in the exemplary embodiment, has a substantially rectangular prism shape.
  • each support leg 214 and 216 may have any suitable shape that enables the rotor assembly 130 and/or the power system 100 to function as described herein.
  • the first support leg 214 extends from the first sleeve portion 202 to the second sleeve portion 204.
  • the second support leg 216 extends from the first sleeve portion 202 and the second sleeve portion 204. More specifically, each of the support legs 214 and 216 extend from the outer sleeve 201 of the first sleeve portion 202 to the outer sleeve 205 of the second sleeve portion 204.
  • first and second support legs 214 and 216 are oriented such that the second support leg 216 is substantially parallel with respect to the first support leg 214 to define a first opening or channel 218 and a second opening or channel 220 between the first sleeve portion 202 and the second sleeve portion 204. More specifically, the channels 218 and 220 are defined between the outer sleeve 201 of the first sleeve portion 202 and the outer sleeve 205 of the second sleeve portion 204.
  • the support legs 214 and 216 may have any suitable orientation that enables the rotor assembly 130 and/or the power system 100 to function as described herein.
  • first sleeve portion 202, the second sleeve portion 204, the first support leg 214, and the second support leg 216 are formed integrally together such that the sleeve apparatus 200 is a single unitary component.
  • one or more of the components may be formed separate and removably or permanently coupled together.
  • Each of the first sleeve portion 202, the second sleeve portion 204, the first support leg 214, and the second support leg 216 may be formed via a variety of manufacturing processes known in the art, such as, but not limited to, molding processes, drawing processes or machining processes.
  • One or more types of materials may be used to fabricate the sleeve apparatus 200 and the components therein with the materials selected based on suitability for one or more manufacturing techniques, dimensional stability, cost, moldability, workability, rigidity, and/or other characteristic of the material(s).
  • the sleeve apparatus 200 and the components therein may be at least partially formed from a crystalline particle, such as a Nanocrystal.
  • each of the first sleeve portion 202, the second sleeve portion 204, the first support leg 214, and the second support leg 216 are formed from the same material(s).
  • different and varying materials may be used to form each of the components.
  • the rotor assembly 130 also includes a substantially cylindrical rotor shaft 230 that is coupled to the sleeve apparatus 200 such that at least a portion of the rotor shaft 230 is positioned within the sleeve apparatus 200. More specifically, in the exemplar ⁇ ' embodiment, the rotor shaft 230 includes a first end portion 234, a middle portion 236, and a second portion 238. The rotor shaft 230 is positioned within the sleeve apparatus 200 such that at least a portion of the middle portion 236 is positioned within the sleeve apparatus 200, and the first end portion 234 and the second end portion 238 are not positioned within the sleeve apparatus 200.
  • the first end portion 234 of the rotor shaft 230 extends outwardly from the opening of the inner sleeve 203 of the first sleeve portion 202 and the second end portion 238 extends outwardly from the opening of the inner sleeve 207 of the second sleeve portion 204.
  • the second end portion 238 of the rotor shaft 230 has a diameter that is substantially equal to the diameter of the middle portion 236.
  • the first end portion 234 of the rotor shaft 230 is configured to be removably coupled to the drive shaft 122 (shown in FIG. 1) of the turbine engine 102 (shown in FIG. 1). More specifically, the first end portion 234 includes a first surface 250 that is substantially arcuate and a second surface 252 that is substantially planar such that the first end portion 234 is positionable within an opening (not shown) on an end portion (not shown) of the drive shaft 122.
  • the opening on the end portion of the drive shaft 122 may be configured to receive the first end portion 234 of the rotor shaft 230.
  • first end portion 234, the middle portion 236, and the second end portion 238 of the rotor shaft 230 are formed integrally together such that the rotor shaft 230 is a single unitary component.
  • one or more of the components of the rotor shaft 230 may be formed separate and removably or permanently coupled together.
  • Each of the first end portion 234, the middle portion 236, and the second end portion 238 may be formed via a variety of manufacturing processes known in the art, such as, but not limited to, molding processes, drawing processes, or machining processes.
  • the rotor shaft 230 may be at least partially formed from lightweight and rigid materials, such as an alumina material, a ceramic material, and/or a metal matrix composite material.
  • the metal matrix composite material may include a first metal material and at least one other material, such as a second metal material and/or a ceramic compound.
  • the rotor shaft 230 may be formed of any suitable material that enables the rotor assembly 130 and/or the power system 100 to function as described herein.
  • the rotor assembly 130 also includes at least one magnetic attachment, such as a first magnetic attachment 300 and a second magnetic attachment 302 that are removably coupled to the sleeve apparatus 200. More specifically, the first magnetic attachment 300 is coupled withm the first channel 218 of the sleeve apparatus 200 and the second magnetic attachment 302 is coupled within the second channel 220 of the sleeve apparatus 200.
  • each magnetic attachment 300 and 302 has a substantially arcuate outer surface 312 and an opposing arcuate inner surface 314.
  • the first magnetic attachment 300 and the second magnetic attachment 302 are positioned between the first sleeve portion 202 and the second sleeve portion 204 such that the sleeve apparatus 200 with the magnetic attachments 300 and 302 form a substantially cylindrical structure that substantially encloses at least a portion of the middle portion 236 of the rotor shaft 230. Accordingly, the magnetic attachments 300 and 302 facilitate maintaining the rotor shaft 230 in alignment within the sleeve apparatus 200 during operation of the rotor assembly 130 and/or of the power system 100.
  • the rotor assembly 130 also includes a substantially cylindrical housing 330 that includes an opening 334 extending therethrough such that the housing 330 substantially circumscribes at least a portion of the sleeve apparatus 200 and at least a portion of the magnetic attachments 300 and 302 to facilitate securing the magnetic attachments 300 and 302 within the channels 218 and 220, respectively.
  • the housing 330 may be formed onto the sleeve apparatus 200 and the magnetic attachments 300 and 302 via any suitable method known in the art, such as via heating.
  • the housing 330 may be cured in at a temperature of, for example, 300° F, for approximately one hour.
  • the housing 330 is at least partially formed from a fiber-reinforced polymer, such as carbon fiber.
  • the housing 330 may be formed from any suitable material that enables the rotor assembly 130 and/or the power system 100 to function as described herein.
  • the turbine section 1 18 (shown in FIG. 1 ) converts the thermal energy from the gas stream to mechanical rotational energy, as the combustion gases impart rotational energy to the turbine section 1 18 and to a rotor disk assembly (not shown).
  • the mechanical rotational energy is then converted to electrical energy via the load 128.
  • the mechanical rotational energy that is generated by the turbine section 1 18 is enabled by the rotation of the drive shaft 122.
  • the rotor assembly 128 rotates. More specifically, the rotor shaft 230 of the rotor assembly 130 rotates.
  • the rotor shaft 230 may undergo mechanical stress that results in a misalignment of the rotor shaft 230, the rotor assembly 130, and/or the load 128 with respect to the drive shaft 122 and/or the turbine engine 102.
  • the rotor assembly 130 is substantially rigid and facilitates a secure connection between the rotor shaft 230 and the drive shaft 122 of the turbine engine 102, and the rotor assembly 130 maintains proper alignment during operation of the power system 100. More specifically, because the first end portion 234 of the rotor shaft 230 includes the first surface 250 that is substantially arcuate and the second surface 252 that is substantially planar, the first end portion 234 is positionable within an opening on an end portion of the drive shaft 122. Moreover, when positioned within the drive shaft 122, the shape of the first end portion 234 of the rotor shaft 230 enables a secure connection with the drive shaft 122.
  • the rotor shaft 230 when at least a portion of the rotor shaft 230 is positioned within the sleeve apparatus 200 and the magnetic attachments 300 and 302 are coupled to the sleeve apparatus 200, then the rotor shaft 230 is substantially enclosed within the substantially cylindrical structure formed by the sleeve apparatus 200 and the magnetic attachments 300 and 302. Such an enclosure prevents the rotor shaft 230 from deviating from proper alignment during operation of the rotor assembly 130 and/or the power system 100.
  • the embodiments described herein provides a substantially rigid rotor assembly that facilitates a secure connection with a turbine engine, and the rotor assembly is configured to maintain proper alignment during operation.
  • the rotor assembly generally comprises a sleeve apparatus that includes at least one channel.
  • a rotor shaft is coupled to the sleeve apparatus such that at least a portion of the rotor shaft is positioned within the sleeve apparatus.
  • the rotor shaft includes an end portion that is configured to be removably coupled to, for example, a drive shaft of a turbine engine.
  • at least one magnetic attachment is removably coupled within the channel to facilitate maintaining the rotor shaft in alignment within the sleeve apparatus during operation of the rotor assembly.
  • sy stems, apparatus, and methods are described above in detail.
  • the systems, apparatus, and methods are not limited to the specific embodiments described herein, but rather, components of each system, apparatus, and/or method may be utilized independently and separately from other components described herein.
  • each system may also be used in combination with other systems and is not limited to practice with only systems as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other applications.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Power Engineering (AREA)
  • Manufacture Of Motors, Generators (AREA)
  • Iron Core Of Rotating Electric Machines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

Ensemble rotor comprenant de manière générale un appareil manchon qui comporte une première partie de manchon et une seconde partie de manchon positionnée à une distance prédéfinie de la première partie de manchon. L'appareil manchon comprend également au moins un canal délimité entre la première partie de manchon et la seconde partie de manchon. Un arbre de rotor est accouplé à l'appareil manchon de sorte qu'au moins une partie de l'arbre de rotor soit positionnée dans l'appareil manchon, l'arbre de rotor comprenant une partie d'extrémité qui est configurée pour être accouplée amovible à un arbre d'entraînement. Au moins un accessoire magnétique est accouplé amovible dans le canal pour faciliter l'entretien de l'arbre de rotor en alignement dans l'appareil manchon pendant le fonctionnement de l'ensemble rotor.
PCT/US2013/071005 2012-11-20 2013-11-20 Ensemble rotor et son procédé d'utilisation WO2014081829A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/682,378 US20140140857A1 (en) 2012-11-20 2012-11-20 Rotor assembly and method of using same
US13/682,378 2012-11-20

Publications (2)

Publication Number Publication Date
WO2014081829A2 true WO2014081829A2 (fr) 2014-05-30
WO2014081829A3 WO2014081829A3 (fr) 2015-03-05

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Application Number Title Priority Date Filing Date
PCT/US2013/071005 WO2014081829A2 (fr) 2012-11-20 2013-11-20 Ensemble rotor et son procédé d'utilisation

Country Status (2)

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US (1) US20140140857A1 (fr)
WO (1) WO2014081829A2 (fr)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4549341A (en) * 1983-07-19 1985-10-29 The Garrett Corporation Method for producing a permanent magnet rotor
US4617726A (en) * 1984-12-06 1986-10-21 The Garrett Corporation Maximum stiffness permanent magnet rotor and construction method
US5627423A (en) * 1993-06-11 1997-05-06 Askoll S.P.A. Permanent-magnet rotor for electric motors and method of manufacturing the same
EP0996212A1 (fr) * 1998-10-21 2000-04-26 Technische Universiteit Eindhoven Rotor à aimant permanent et procédé pour sa fabrication
JP2005042838A (ja) * 2003-07-23 2005-02-17 Ntn Corp 流体軸受装置
FR2955717B1 (fr) * 2010-01-26 2012-03-02 Converteam Technology Ltd Rotor de machine electrique tournante equipe d'une frette
US8475114B2 (en) * 2010-02-08 2013-07-02 Hamilton Sundstrand Corporation Air cycle machine air bearing shaft
DE102010041399A1 (de) * 2010-09-27 2012-03-29 Zf Friedrichshafen Ag Hohlwelle eines Getriebes einer Baureihe, insbesondere Hauptwelle
KR101579738B1 (ko) * 2010-12-23 2016-01-05 삼성전자주식회사 현상기 및 이를 채용한 화상형성장치

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WO2014081829A3 (fr) 2015-03-05

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