EP1977499A1 - Moteur à réaction avec support magnétique actif - Google Patents

Moteur à réaction avec support magnétique actif

Info

Publication number
EP1977499A1
EP1977499A1 EP07702377A EP07702377A EP1977499A1 EP 1977499 A1 EP1977499 A1 EP 1977499A1 EP 07702377 A EP07702377 A EP 07702377A EP 07702377 A EP07702377 A EP 07702377A EP 1977499 A1 EP1977499 A1 EP 1977499A1
Authority
EP
European Patent Office
Prior art keywords
jet engine
electromechanical unit
bearing
stator
electromechanical
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP07702377A
Other languages
German (de)
English (en)
Inventor
John Sharp
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1977499A1 publication Critical patent/EP1977499A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/08—Structural association with bearings
    • H02K7/09—Structural association with bearings with 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
    • H02K7/18—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 present invention relates to a jet engine, in particular for an aircraft, with at least one in at least one bearing about a central axis rotatably mounted hollow shaft and / or low pressure shaft on which at least one high and / or low pressure compressor and at least one each high and / or Low-pressure turbine is disposed, wherein the jet engine further comprising an electromechanical unit to provide at least one engine function for starting the jet engine and / or a generator function for power supply, wherein the electromechanical unit is arranged centrally about the central axis and wherein the electromechanical unit (10) further is designed as active magnetic bearing, which supports the hollow shaft (7) and / or low pressure shaft (8).
  • jet engines are well known, wherein the means for starting the jet engine and the means for generating the electric power are arranged separately from each other on the jet engine.
  • the jet engine must be started mechanically for commissioning, in a two-shaft engine, the shaft of the high-pressure compressor is rotated by a mechanical engagement in rotation.
  • jet engines have means for generating an electric power, which may be arranged in the form of a generator in or on the engine.
  • the electrical power is required for the operation of various electrical equipment of the aircraft, with recent developments show that the required electrical power of the aircraft continues to increase due to increasing electrification of various aggregates.
  • the jet engine contemplated in accordance with the present invention is directed to a fan engine configured as a two-shaft engine and the fan is a low-pressure compressor which feeds into the engine precompressed incoming air and generates a sheath flow around the centrally ejected hot exhaust gas jet.
  • a generic jet engine which has a generator which is integrated in the high-pressure compressor of the jet engine.
  • the engine has compressor blades, which are sheathed, wherein outside of the sheath, an electric generator is arranged.
  • This consists of a stator which comprises an electric coil and a rotor which is connected to the engine shaft in such a way that it likewise performs a rotational movement.
  • the rotor assembly performs a rotational movement within the stator, and induces an electrical voltage in the coil of the stator.
  • the rotor elements are arranged on the outside of the blade elements of the high-pressure compressor and extend radially outward into the stator of the generator.
  • the bearing of the hollow shaft, on which the high-pressure compressor is rotatably arranged, as well as the bearing of the low-pressure shaft on which the low-pressure compressor is arranged, are mounted on mechanical bearings, such as roller bearings.
  • the at least one shaft of the jet engine can be rotatably supported via active magnetic bearings, wherein the active magnetic bearing according to the prior art is only a respective partial storage of the waves.
  • a so-called gear box is necessary, which is arranged inside the engine nacelle on the outside of the jet engine and 'driven by a shaft arrangement, the so-called Powershaft, by means of an output of at least the low pressure shaft and / or the hollow shaft.
  • the Gearbox can include both a starter function and a generator function, which requires a considerable amount of space circumferentially on the jet engine, represents a large weight and has a high maintenance requirements.
  • Another disadvantage is that the Gearbox to start the Jet engine formed means which must be carried during flight operations as unusable means and thus causes a "dead weight”.
  • the invention includes the technical teaching that the electromechanical unit (10) is designed as a transverse flux machine.
  • the electromechanical unit formed in addition to a motor-generator function also includes the function of an active magnetic bearing.
  • the electrical power provided by the generator function of the electromechanical unit can be so great that, in addition to the supply of the internal active magnetic bearing, an external electrical power supply of the aircraft can also take place.
  • the electromechanical unit it is possible to remove the otherwise required for a mechanical bearing lubrication system, which is mainly provided in the externally arranged gearbox. If the electromechanical unit also has a generator function for generating electricity as well as a starter function in the form of an electric drive motor for the shafts of the jet engine, it is possible to remove the gearbox as well as the Powershaft from the design of the jet engine.
  • the electromechanical unit is inventively designed as a transverse flux machine, in which both the motor / generator function and the bearing function is integrated.
  • the Be2020lten the respective modules ensures that all poles of the stator have the required polarity. Thus, it can be ensured that the opposite polarized permanent magnet segment is rotated in the correct position is.
  • each module contributes one-twelfth of the power supply.
  • Another switching algorithm of the power electronics is necessary to fulfill the motor function.
  • the rotor position can be measured, this can be done either with an additional device or by measuring the change of electrical parameters, such as the inductance.
  • the electromechanical unit is designed as a radial and / or axial bearing.
  • the thrust bearing acts mainly in the thrust direction to transmit the axial thrust of the jet engine to the stationary parts of the engine and thus to the aircraft.
  • the rotational movement is caused by tangential force components to produce a torque.
  • This magnetic force also referred to as "Lorenz” force, is initially used for the motor-generator function in the proposed electromechanical unit, while the function of the active-magnetic bearing is based on the so-called “Maxwell” force, which results in a magnetic repulsion force between one Stator and a rotor, whereby an air gap between these components is maintained.
  • a further advantageous embodiment of the invention provides that the jet engine has an electrical storage device in order to electrically compensate for mechanical load peaks of the active magnetic bearing.
  • these peak loads may be due to increased g loads, or may be caused by shocks such as landing the aircraft.
  • the load peaks require an increased magnetic flux, which requires for a short time an increased electrical power that can not or not sufficiently be provided by the generator function of the electromechanical unit.
  • memory devices may be provided which comprise, for example, batteries, capacitors or other electrical storage means. The short-term additional power can be switched from the said storage devices briefly to the actual power supply by the generator, wherein the adjusting air gap between the bearing components is used as a reference variable for a control device.
  • the electromechanical unit has sections which can be selectively switched over to a motor and / or a bearing function.
  • the generator function of the electromechanical unit can preferably be perceived in order to provide a correspondingly large electrical power for the aircraft.
  • the active magnetic bearing requires only a small proportion of the power of the electromechanical unit, which is sufficient for the transmission of the normal bearing forces.
  • the electrical power management system within the aircraft may require a greater proportion of the activation of the active magnetic bearing, and this switching capability may also be assisted by the aforementioned memory device.
  • the electromechanical unit comprises control means to actively damp vibrations by means of the active magnetic bearing, which arise in particular by the rotating hollow shaft and / or the low pressure wave.
  • This active damping can be realized by an electrodynamic countersteering in order to eliminate occurring vibrations.
  • non-contact storage via active-magnetic components offers the design advantage that a vibration transmission can not take place due to a solid state contact.
  • the electromechanical unit has electrically operated means to cool them.
  • due to the omission of an external oil supply system for mechanical bearings also eliminates the cooling function via an oil flow.
  • Possible thermal problems can be remedied by means of electrical cooling, which prevent excessive heat development in the electromechanical unit.
  • the electromagnetic unit may preferably be arranged on the inside of the first or at least one of the first high-pressure compressor stages, wherein a generator may be provided on the low-pressure stage. In principle, however, it is possible to arrange the function of the electromechanical unit of any size at any position of the jet engine, where storage is required.
  • a purely active magnetic bearing at a second location by means of a arranged at a first location integrated electromechanical storage by the power supply of the generator part of the electromagnetic unit is branched off at the first location to the active magnetic bearing at the second location.
  • the possibility can be used to provide the axial bearing, via which the thrust of the jet engine is transmitted, at the first location where the electromechanical unit is arranged with full functionality, wherein the single active magnetic bearing can be designed as a radial bearing.
  • the at least one section of the electromechanical unit for fulfilling the function of the active magnetic bearing is preferably formed by additional line windings in the stator.
  • the "Maxwell" forces can be controlled by a corresponding power control so that a switching of the proportional motor or bearing function is possible.
  • the control of the current through the additional windings allows the unit the function of active magnetic bearing and compensates any tendency of one eccentric movement of the shaft, which would otherwise be formed by a mechanical bearing.
  • the electromechanical unit is made up of individual modules which can be electrically controlled separately in order to minimize magnetic interactions between the modules. These are separately controllable, so that the modular design leads to a high reliability or fault tolerance, which is required in aerospace applications in particular and also allows an even more flexible control of the optional operating modes of the electromechanical unit.
  • the electromechanical unit is formed of at least twelve individual modules, each comprising at least one stator, a rotor designed with permanent magnets and power electronics to arrange at least twelve mutually independent electromechanical sections on a common shaft.
  • advantageous developments of the invention provide that the rotor moves around the stator, wherein a profiled stator, which is below the rotating permanent magnet segments, is formed wave-shaped with Stator lakespitzen.
  • a profiled stator which is below the rotating permanent magnet segments, is formed wave-shaped with Stator lakespitzen.
  • advantageously corresponds to the distance between two Stator vomierispitzen with the width of rotor permanent magnet segment surfaces.
  • FIG. 1 shows a cross section through a jet engine with an electromechanical unit, which in the plane of rotation of the first compressor stages of the high-pressure compressor is arranged;
  • Fig. 2 shows a possible distribution of north and south poles between a stator and a rotor of an electromechanical unit
  • Fig. 3 is a partially advantageous embodiment of a module of a motor / bearing assembly.
  • the jet engine 1 shown in FIG. 1 has a high-pressure compressor 2, which comprises a compressor housing 3.
  • a high-pressure compressor 2 which comprises a compressor housing 3.
  • a plurality of compressor stages 4 are rotatably mounted, wherein the compressor stages 4 have blade elements 5, which compress via an inflow channel 6 incoming air.
  • the compression of the incoming air takes place stepwise successively over a plurality of compressor stages 4, which follow one another in the flow direction of the air to be compressed in a parallel arrangement.
  • the compressor stages 4 are rotatably mounted on a hollow shaft 7, wherein a low pressure shaft 8 extends through the hollow shaft 7 therethrough.
  • a fan 9 is rotatably mounted, which as a low-pressure stage precompresses the incoming air, and generates a bypass flow around the inner flow region, which is formed by the high-pressure compressor 2.
  • an electromechanical unit 10 is arranged by way of example at the level of the first and second compressor stage 4, which extends circumferentially around the compressor housing 3 in an annular manner.
  • the outside of the compressor housing disposed part of the electromechanical unit 10 includes a stator 11, which forms the stationary part of the electromechanical unit 10.
  • the arrangement of the electromechanical unit 10 may also be in the range of Low-pressure compressor 12, which arrangement is not shown in FIG. 1 for the sake of simplicity.
  • the stator 11 is connected, regardless of the location of the arrangement of the electromechanical unit 10 in a stationary manner to the stator construction of the jet engine 1, and forms both the stationary part of the motor / generator module and the stationary part of the active magnetic bearing.
  • the electromechanical unit 10 comprises a rotor 13, which is mechanically connected to the rotating arrangement of the compressor stages 4.
  • the rotor 13 forms the rotating part of the electromechanical unit 10, which forms both the radial bearing part and the axial bearing part of the active magnetic bearing, and at the same time comprises the rotating armature part of the motor / generator modules.
  • a gearbox 14 is shown in dashed lines, which is mechanically connected to the hollow shaft 7 via a drive train 15, also shown in dashed lines.
  • the drive train 15 engages via a bevel gear a rotational movement of the hollow shaft 7 and drives various units, which are arranged in the gearbox 14, wherein the gearbox 14 may also be included a starter function for starting the jet engine 1.
  • a gearbox 14 and a drive train 15 are shown, this being only to illustrate the construction of a jet engine 1 according to the prior art.
  • the gearbox 14 and the drive train 15 can be omitted according to the present invention, since neither an electric power supply through the Gearbox 14 nor an oil supply is necessary if the electromechanical unit 10 according to the proposed embodiment, the function of the power supply, the starter of the jet engine 1 as well the bearing function is met, so that lubrication by means of a lubrication system is no longer required.
  • FIG. 13 The arrangement of the magnetic polings between the stator 11 and the rotor 13 is shown in FIG.
  • eight magnetic poles are shown, this being the simplification, since in a technical implementation of the proposed solution about 50 to about 100 magnetic poles of North Pole N and South Tru S on the Circumference of the rotor 13 may be arranged.
  • a repulsive force can be generated, depending on the arrangement of poles present to one another.
  • attractive forces can arise when opposing polarity is opposed. If the respective repulsive and attractive forces are equal to one another, ie that they cancel each other out, it becomes clear that as far as no active magnetic bearing function can be realized.
  • the stator can be electromagnetically excited and the flux density in the range of 2 Tesla (T) can be generated depending on the type of soft iron material.
  • T 2 Tesla
  • the magnetic segments are magnetized with about 1.2 T (Nd 2 B Fe), whereby an achievable magnetic saturation can not achieve any further increase in the magnetic flux through the magnetic segments.
  • the magnetic flux is compressed, which can be done for example by an eccentric alignment of the rotor 13 relative to the stator 11, which results in the magnetic flux density in the air gap due to a superposition of the two separate Values give a value of 3.2 T, whereby a maximum value can be generated.
  • the density of the magnetic flux is limited to the value of the magnetic segment of 1.2T.
  • FIG. 3 shows a detail of an advantageous embodiment of a module of a motor / bearing arrangement, wherein the rotor 13, which carries the permanent magnet, moves about the stator 11 which carries the electric coils in order to provide the electromagnetic field.
  • the profiled stator surface 20, which is under the permanent magnet segments rotating above it has a wave pattern with stator surface tips 19, the length of each "wave” corresponding to the width of the rotor permanent-magnet segment surface 18.
  • the maximum air gap 16 is in accordance with this design "Wellental", while the minimum air gap 17 is located at the Stator vomspitze 19. Further, in Figure 3, the inner surface of the stator 21 is shown.
  • the gap should typically be about 0.8 mm with a minimum gap set to 0.2 mm. This is determined on the one hand by the maximum allowable radial displacement in a gas turbine between rotating components and housing components, which is about 1 mm. The minimum gap must therefore be less than 1 mm. On the other hand, this is defined by the output power of an electrical machine of 150 kVA, where the operating gap is typically between 0.5 mm and 1 mm.
  • the invention is not limited in its execution to the above-mentioned preferred embodiment. Rather, a number of variants is conceivable, which makes use of the illustrated solution even with fundamentally different types of use.

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Abstract

Moteur (1) à réaction, notamment pour un aéronef, comprenant au moins un arbre (7) creux et/ou un arbre (8) à basse pression logés dans au moins un palier de manière à pouvoir tourner autour d'un axe central sur lequel sont disposés au moins respectivement un compresseur (2, 12) à haute et/ou à basse pression et au moins respectivement une turbine à haute et/ou à basse pression, le moteur (1) à réaction présentant en outre une unité (10) électromécanique pour accomplir au moins une fonction de moteur pour le démarrage du moteur (1) à réaction et/ou une fonction de générateur pour l'alimentation électrique, l'unité (10) électromécanique étant disposée de manière centrée autour de l'axe central, l'unité (10) électromécanique comprenant en plus la fonction d'un support magnétique actif pour former au moins un support pour ledit ou lesdits arbres (7) creux et/ou arbres (8) à basse pression et l'unité (10) électromécanique étant réalisée sous la forme d'une machine à flux transversal. On obtient ainsi un moteur (1) à réaction amélioré avec lequel les moyens destinés à supporter ledit or lesdits arbres de moteur ainsi que les moyens d'alimentation en énergie du support magnétique actif et l'aéronef ainsi que les moyens de démarrage du moteur à réaction sont réalisés dans un faible encombrement et avec un poids réduit et forment une unité intégrée.
EP07702377A 2006-01-27 2007-01-19 Moteur à réaction avec support magnétique actif Withdrawn EP1977499A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006003884A DE102006003884A1 (de) 2006-01-27 2006-01-27 Strahltriebwerk mit aktivmagnetischer Lagerung
PCT/DE2007/000096 WO2007085229A1 (fr) 2006-01-27 2007-01-19 Moteur à réaction avec support magnétique actif

Publications (1)

Publication Number Publication Date
EP1977499A1 true EP1977499A1 (fr) 2008-10-08

Family

ID=37964487

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07702377A Withdrawn EP1977499A1 (fr) 2006-01-27 2007-01-19 Moteur à réaction avec support magnétique actif

Country Status (4)

Country Link
US (1) US8133004B2 (fr)
EP (1) EP1977499A1 (fr)
DE (1) DE102006003884A1 (fr)
WO (1) WO2007085229A1 (fr)

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DE102005046208A1 (de) * 2005-09-28 2007-03-29 Mtu Aero Engines Gmbh Strahltriebwerk
US8519555B2 (en) * 2010-11-29 2013-08-27 Pratt & Whitney Canada Corp. Combination low spool generator and ram air turbine generator
WO2014137424A1 (fr) * 2013-03-03 2014-09-12 Rolls-Royce North American Technologies, Inc. Moteur à turbine à gaz
DE102013209388B4 (de) * 2013-05-22 2021-07-22 Robert Bosch Gmbh Hybridantrieb für kraftgetriebenes Luftfahrzeug, kraftgetriebenes Luftfahrzeug mit Hybridantrieb und zugehöriges Betriebsverfahren
US20160348589A1 (en) * 2014-11-24 2016-12-01 Hamilton Sundstrand Corporation Aircraft engine assembly and method of generating electric energy for an aircraft power system
US9431877B2 (en) * 2014-12-03 2016-08-30 The Boeing Company Concentric ring generators
DE102016207517A1 (de) * 2016-05-02 2017-11-02 Siemens Aktiengesellschaft Antriebssystem für Luftfahrzeug mit elektrischem Generator
DE202017103131U1 (de) * 2017-05-23 2018-08-24 ENGIRO GmbH Luftfahrzeug mit mindestens einem Range-Extender

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GB9606546D0 (en) * 1996-03-28 1996-06-05 Rolls Royce Plc Gas turbine engine system
EP0899855B1 (fr) * 1997-08-25 2006-03-08 Levitronix LLC Dispositif rotatif avec palier magnétique
WO1999040334A1 (fr) 1998-02-03 1999-08-12 Sulzer Electronics Ag Procede et dispositif d'amorçage de systemes a enroulement pour force portante et a enroulement pour force d'entrainement dans des machines electriques a palier magnetique, et entrainement electrique
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Also Published As

Publication number Publication date
US8133004B2 (en) 2012-03-13
US20100143100A1 (en) 2010-06-10
WO2007085229A1 (fr) 2007-08-02
DE102006003884A1 (de) 2007-08-02

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