EP1709300B1 - Device for the adjustment of guide blades - Google Patents

Device for the adjustment of guide blades Download PDF

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Publication number
EP1709300B1
EP1709300B1 EP05706718A EP05706718A EP1709300B1 EP 1709300 B1 EP1709300 B1 EP 1709300B1 EP 05706718 A EP05706718 A EP 05706718A EP 05706718 A EP05706718 A EP 05706718A EP 1709300 B1 EP1709300 B1 EP 1709300B1
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EP
European Patent Office
Prior art keywords
generator
rotor
stator
torque motor
turbine
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.)
Not-in-force
Application number
EP05706718A
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German (de)
French (fr)
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EP1709300A1 (en
Inventor
Hubert Herrmann
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MTU Aero Engines AG
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MTU Aero Engines GmbH
MTU Aero Engines AG
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Publication of EP1709300A1 publication Critical patent/EP1709300A1/en
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • F01D17/22—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical
    • F01D17/24—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical electrical
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/404—Transmission of power through magnetic drive coupling

Definitions

  • the invention relates to a device for adjusting guide vanes according to the preamble of patent claim 1.
  • Gas turbines in particular aircraft engines, consist of several assemblies, such as a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines.
  • a fan fan
  • a combustion chamber preferably a plurality of compressors and a plurality of turbines.
  • a plurality of stationary vanes and a plurality of rotating blades are arranged in a turbine and in a compressor of the gas turbine.
  • the guide vanes are stationary with respect to a housing of the gas turbine.
  • the blades are associated with at least one rotor and rotate with respect to the fixed vanes and the fixed housing.
  • guide vanes and rotor blades are alternately arranged one behind the other in the axial direction or in the direction of flow, wherein at an axial position, i.e. at an axial position, ie. along the circumference of the rotor or the housing, also a plurality of blades or vanes are arranged which form so-called vane rings or blade rings.
  • the fixed guide vanes of a compressor or a turbine can be designed to be adjustable or pivotable about an axis.
  • the DE 39 13 102 C1 an apparatus for adjusting vanes, wherein the vanes of a vane ring outside a housing of the gas turbine are pivotally connected via adjusting levers with a collar, wherein the or each adjusting lever having a first end to the collar and with a first end opposite the second end at one end a shaft of the respective vane attacks.
  • the adjustment of the guide vanes via hydraulic means, preferably via hydraulic piston.
  • the GB 1 499 531 additionally discloses an adjustment of Leitochaafelm with an electric motor.
  • the present invention based on the problem to provide a novel device for adjusting vanes.
  • a rotor of a torque motor is associated with the adjusting ring, wherein a stator of the torque motor concentrically surrounds the rotor of the torque motor.
  • the adjusting ring is designed as a rotor of the torque motor.
  • the electrical energy required for operating the torque motor is provided by a generator of the gas turbine, the generator comprising a stator and a rotor, and wherein the rotor of the generator is designed as a free-running generator turbine, which is driven by a gas flow rotates relative to the stator of the generator and thus generates electrical energy from the kinetic energy of the gas flow.
  • the stator of the torque motor and the stator of the generator are mounted on a common support, wherein the stator of the generator concentrically surrounds the stator of the torque motor, which are both made of a sheet metal section. Accordingly, the stator of the torque motor surrounds the rotor of the torque motor, the stator of the generator encloses the stator of the torque motor and thus the rotor of the torque motor, and the rotor of the generator encloses the stator of the generator and thus the stator and the rotor of the torque motor.
  • FIGS Fig. 1 described in more detail.
  • Fig. 1 shows a partial cross section through a high-pressure compressor 10 of a gas turbine, namely an aircraft engine. So shows Fig. 1 a flow channel 11 of the high pressure compressor 10, wherein in the flow channel 11 in the axial direction or in the flow direction of the same successively fixed guide vanes 12 and rotating blades 13 are positioned. At an axial position and distributed over the circumference of the high pressure compressor 10 arranged vanes 12 form vane rings, arranged at an axial position blades 13 form blade rings. In Fig. 1 only one vane ring consisting of vanes 12 and a blade ring consisting of blades 13 is shown. It is understood that in the direction of flow of the high pressure compressor 11 more such vane rings and blade rings can be arranged alternately one behind the other.
  • the flow channel 11 of the high pressure compressor is limited by a housing 14.
  • the fixed vanes 12 have at a radially outer end via a shaft 15 with which they penetrate the housing 14.
  • On the shaft 15 of each adjustable guide vane 12 engages an adjusting lever 16, wherein the adjusting lever 16 is further connected to a collar 17.
  • All levers 16 of the guide vanes 12 of a vane ring are connected to the same adjusting ring 17. Accordingly, all the guide vanes 12 of a vane ring can be adjusted or pivoted together by turning the adjusting ring 17.
  • the adjusting ring 17 is associated with a rotor of a torque motor, wherein the adjusting ring 17 is preferably designed as a rotor of the torque motor.
  • a stator 18 of the torque motor surrounds the trained as a rotor of the torque motor collar 17 concentric, namely radially outward.
  • the electrical energy required to operate the torque motor is provided by a generator 19 of the gas turbine.
  • the generator 19 of the gas turbine has as well as the torque motor via a rotor 20 and a stator 21.
  • the rotor 20 of the generator 19 is formed as a free-running generator turbine, which rotates driven by a gas flow relative to the stator 21 of the generator 19 and so from the kinetic energy the gas flow generates electrical energy.
  • the rotor 20 of the generator 19 is preferably driven by a gas flow of a non-illustrated fan or fan module of the gas turbine.
  • the generator 19 is positioned downstream of the fan or fan module, wherein a generator module exhibiting the generator module at the downstream end of the fan module is detachably connected to the fan module.
  • the generator 19 or the rotor 20 of the generator 19 is preferably driven by a bypass gas flow of the fan or fan module and thus generates electrical energy from this bypass gas flow.
  • Trained as a free-running generator turbine rotor 20 of the generator 19 has a plurality of rotating blades 22, wherein the blades 22 are connected at a radially inner end via a platform 23 with an outer bearing ring 26 of a bearing 27.
  • the radially inner ends of the blades 22 and the platform 23 are assigned pole pieces 24.
  • the rotor 20 of the generator 19 encloses together with the pole pieces 24 radially outwardly of the stator 21 of the generator 19.
  • the stator 21 includes windings and magnetic circuits to ultimately electrical energy from the movement or rotation of the rotor 20 of the generator 19th to create.
  • the electrical energy generated in the stator 21 of the generator 19 is at least partially supplied to the stator 18 of the torque motor and used there for movement or to drive the adjusting ring 17 designed as a rotor of the torque motor.
  • stator 21 of the generator 19 and the stator 18 of the torque motor are mounted on a common bracket 28.
  • the stator 21 of the generator 19 encloses the stator 18 of the torque motor concentrically and forms a unit with this. Accordingly, the stator 18 of the torque motor surrounds the rotor of the torque motor; the stator 21 of the generator 19 encloses the stator 18 of the torque motor and thus also the rotor of the torque motor; the rotor 20 of the generator 19 encloses the stator 21 of the generator 19 and thus also the stator 18 and the rotor of the torque motor.
  • the rotor of the torque motor is the adjusting ring 17.
  • the stator 18 of the torque motor in turn comprises windings and the adjusting ring 17 are associated with magnetic elements 25. Over the circumference of the adjusting ring 17, a plurality of such magnetic elements 25 are positioned distributed, wherein the distance between two adjacent magnetic elements 25 is dimensioned such that between them the guiding levers 16 leading to the guide vanes 12 are fastened.
  • Fig. 1 only one vane ring with adjustable vanes 12 is shown.
  • the guide vanes of several vane rings can be adjusted as described above.
  • the adjustable guide vanes of each vane ring are adjustable via a respective adjusting ring, wherein preferably each adjusting ring of each vane ring is associated with a rotor of a torque motor.
  • the inventive device for adjusting vanes eliminates the need for the prior art hydraulic piston for adjusting the adjusting ring.
  • the invention it is possible to use the electrical energy generated by a generator for the electrical adjustment of the guide vanes with only a small additional weight for the gas turbine.
  • a particularly fast adjustment of the guide vanes is possible since conventional electromotive drives with gearboxes are dispensed with.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Description

Die Erfindung betrifft eine Vorrichtung zum Verstellen von Leitschaufeln gemäß dem Oberbegriff des Patentanspruchs 1.The invention relates to a device for adjusting guide vanes according to the preamble of patent claim 1.

Gasturbinen, insbesondere Flugtriebwerke, bestehen aus mehreren Baugruppen, so zum Beispiel aus einem Lüfter (Fan), einer Brennkammer, vorzugsweise mehreren Verdichtern sowie mehreren Turbinen. In einer Turbine sowie in einem Verdichter der Gasturbine sind mehrere feststehende Leitschaufeln sowie mehrere rotierende Laufschaufeln angeordnet. Die Leitschaufeln sind gegenüber einem Gehäuse der Gasturbine feststehend ausgebildet. Die Laufschaufeln sind mindestens einem Rotor zugeordnet und rotieren gegenüber den feststehenden Leitschaufeln sowie dem feststehenden Gehäuse. Verfügt die Turbine bzw. der Verdichter über mehrere Stufen, so sind in axialer Richtung bzw. in Strömungsrichtung hintereinander abwechselnd Leitschaufeln und Laufschaufeln angeordnet, wobei an einer axialen Position, d.h. entlang des Umfangs des Rotors bzw. des Gehäuses, ebenfalls mehrere Laufschaufeln bzw. Leitschaufeln angeordnet sind, die sogenannte Leitschaufelkränze oder Laufschaufelkränze bilden.Gas turbines, in particular aircraft engines, consist of several assemblies, such as a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines. In a turbine and in a compressor of the gas turbine, a plurality of stationary vanes and a plurality of rotating blades are arranged. The guide vanes are stationary with respect to a housing of the gas turbine. The blades are associated with at least one rotor and rotate with respect to the fixed vanes and the fixed housing. If the turbine or the compressor has a plurality of stages, guide vanes and rotor blades are alternately arranged one behind the other in the axial direction or in the direction of flow, wherein at an axial position, i.e. at an axial position, ie. along the circumference of the rotor or the housing, also a plurality of blades or vanes are arranged which form so-called vane rings or blade rings.

Die feststehenden Leitschaufeln eines Verdichters bzw. einer Turbine können um eine Achse verstellbar bzw. schwenkbar ausgebildet sein. So offenbart zum Beispiel die DE 39 13 102 C1 eine Vorrichtung zur Verstellung von Leitschaufeln, bei der Leitschaufeln eines Leitschaufelkranzes außerhalb eines Gehäuses der Gasturbine über Stellhebel mit einem Stellring schwenkbar verbunden sind, wobei der oder jeder Stellhebel mit einem ersten Ende an dem Stellring und mit einem dem ersten Ende gegenüberliegenden zweiten Ende an einem Ende eines Schafts der jeweiligen Leitschaufel angreift. Nach dem Stand der Technik erfolgt die Verstellung der Leitschaufeln über hydraulische Mittel, vorzugsweise über Hydraulikkolben.The fixed guide vanes of a compressor or a turbine can be designed to be adjustable or pivotable about an axis. For example, the DE 39 13 102 C1 an apparatus for adjusting vanes, wherein the vanes of a vane ring outside a housing of the gas turbine are pivotally connected via adjusting levers with a collar, wherein the or each adjusting lever having a first end to the collar and with a first end opposite the second end at one end a shaft of the respective vane attacks. According to the prior art, the adjustment of the guide vanes via hydraulic means, preferably via hydraulic piston.

Die GB 1 499 531 offenbart zusätzlich eine Verstellung der Leitochaafelm mit einem elektromotor.The GB 1 499 531 additionally discloses an adjustment of Leitochaafelm with an electric motor.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Vorrichtung zum Verstellen von Leitschaufeln zu schaffen.On this basis, the present invention based on the problem to provide a novel device for adjusting vanes.

Dieses Problem wird dadurch gelöst, dass die eingangs genannte Vorrichtung zum Verstellen von Leitschaufeln durch die Merkmale des kennzeichnenden Teils des Patentanspruchs 1 weitergebildet ist. Erfindungsgemäß ist dem Stellring ein Läufer eines Torquemotors zugeordnet, wobei ein Ständer des Torquemotors den Läufer des Torquemotors konzentrisch umschließt. Vorzugsweise ist der Stellring als Läufer des Torquemotors ausgebildet.This problem is solved in that the above-mentioned device for adjusting vanes is further developed by the features of the characterizing part of patent claim 1. According to the invention, a rotor of a torque motor is associated with the adjusting ring, wherein a stator of the torque motor concentrically surrounds the rotor of the torque motor. Preferably, the adjusting ring is designed as a rotor of the torque motor.

Nach einer vorteilhaften Weiterbildung der Erfindung wird die zum Betreiben des Torquemotors benötigte, elektrische Energie von einem Generator der Gasturbine bereitgestellt, wobei der Generator einen Ständer und einen Läufer aufweist, und wobei der Läufer des Generators als freilaufende Generatorturbine ausgebildet ist, die angetrieben von einer Gasströmung relativ zu dem Ständer des Generators rotiert und so aus der Bewegungsenergie der Gasströmung elektrische Energie erzeugt.According to an advantageous development of the invention, the electrical energy required for operating the torque motor is provided by a generator of the gas turbine, the generator comprising a stator and a rotor, and wherein the rotor of the generator is designed as a free-running generator turbine, which is driven by a gas flow rotates relative to the stator of the generator and thus generates electrical energy from the kinetic energy of the gas flow.

Vorzugsweise sind der Ständer des Torquemotors und der Ständer des Generators an einer gemeinsamen Halterung gelagert, wobei der Ständer des Generators den Ständer des Torquemotors konzentrisch umschließt, die beide aus einem Blechschnitt gefertigt sind. Demnach umschließt der Ständer des Torquemotors den Läufer des Torquemotors, der Ständer des Generators umschließt den Ständer des Torquemotors und damit auch den Läufer des Torquemotors, und der Läufer des Generators umschließt den Ständer des Generators und damit auch den Ständer sowie den Läufer des Torquemotors.Preferably, the stator of the torque motor and the stator of the generator are mounted on a common support, wherein the stator of the generator concentrically surrounds the stator of the torque motor, which are both made of a sheet metal section. Accordingly, the stator of the torque motor surrounds the rotor of the torque motor, the stator of the generator encloses the stator of the torque motor and thus the rotor of the torque motor, and the rotor of the generator encloses the stator of the generator and thus the stator and the rotor of the torque motor.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den abhängigen Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
einen schematisierten Querschnitt durch eine erfindungsgemäße Gasturbine im Bereich eines Hochdruckverdichters.
Preferred embodiments of the invention will become apparent from the dependent subclaims and the following description. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a schematic cross section through a gas turbine according to the invention in the region of a high-pressure compressor.

Nachfolgend wird die hier vorliegende Erfindung unter Bezugnahme auf die Fig. 1 in größerem Detail beschrieben.Hereinafter, the present invention will be described with reference to FIGS Fig. 1 described in more detail.

Fig. 1 zeigt einen ausschnittsweisen Querschnitt durch einen Hochdruckverdichter 10 einer Gasturbine, nämlich eines Flugtriebwerks. So zeigt Fig. 1 einen Strömungskanal 11 des Hochdruckverdichters 10, wobei in dem Strömungskanal 11 in axialer Richtung bzw. in Durchströmungsrichtung desselben hintereinander feststehende Leitschaufeln 12 sowie rotierende Laufschaufeln 13 positioniert sind. An einer axialen Position und über den Umfang des Hochdruckverdichters 10 verteilt angeordnete Leitschaufeln 12 bilden Leitschaufelkränze, an einer axialen Position angeordnete Laufschaufeln 13 bilden Laufschaufelkränze. In Fig. 1 ist lediglich ein Leitschaufelkranz bestehend aus Leitschaufeln 12 und ein Laufschaufelkranz bestehend aus Laufschaufeln 13 gezeigt. Es ist selbstverständlich, dass in Durchströmungsrichtung des Hochdruckverdichters 11 mehrere derartige Leitschaufelkränze sowie Laufschaufelkränze wechselweise hintereinander angeordnet sein können. Fig. 1 shows a partial cross section through a high-pressure compressor 10 of a gas turbine, namely an aircraft engine. So shows Fig. 1 a flow channel 11 of the high pressure compressor 10, wherein in the flow channel 11 in the axial direction or in the flow direction of the same successively fixed guide vanes 12 and rotating blades 13 are positioned. At an axial position and distributed over the circumference of the high pressure compressor 10 arranged vanes 12 form vane rings, arranged at an axial position blades 13 form blade rings. In Fig. 1 only one vane ring consisting of vanes 12 and a blade ring consisting of blades 13 is shown. It is understood that in the direction of flow of the high pressure compressor 11 more such vane rings and blade rings can be arranged alternately one behind the other.

Der Strömungskanal 11 des Hochdruckverdichters wird von einem Gehäuse 14 begrenzt. Die feststehenden Leitschaufeln 12 verfügen an einem radial außenliegenden Ende über einen Schaft 15, mit welchem dieselben das Gehäuse 14 durchdringen. An dem Schaft 15 einer jeden verstellbaren Leitschaufel 12 greift ein Stellhebel 16 an, wobei der Stellhebel 16 ferner mit einem Stellring 17 verbunden ist. Alle Stellhebel 16 der Leitschaufeln 12 eines Leitschaufelkranzes sind mit demselben Stellring 17 verbunden. Über Verdrehen des Stellrings 17 können demnach alle Leitschaufeln 12 eines Leitschaufelkranzes gemeinsam verstellt bzw. verschwenkt werden.The flow channel 11 of the high pressure compressor is limited by a housing 14. The fixed vanes 12 have at a radially outer end via a shaft 15 with which they penetrate the housing 14. On the shaft 15 of each adjustable guide vane 12 engages an adjusting lever 16, wherein the adjusting lever 16 is further connected to a collar 17. All levers 16 of the guide vanes 12 of a vane ring are connected to the same adjusting ring 17. Accordingly, all the guide vanes 12 of a vane ring can be adjusted or pivoted together by turning the adjusting ring 17.

Im Sinne der hier vorliegenden Erfindung ist dem Stellring 17 ein Läufer eines Torquemotors zugeordnet, wobei der Stellring 17 vorzugsweise als Läufer des Torquemotors ausgebildet ist. Ein Ständer 18 des Torquemotors umschließt den als Läufer des Torquemotors ausgebildeten Stellring 17 konzentrisch, nämlich radial außen.For the purposes of the present invention, the adjusting ring 17 is associated with a rotor of a torque motor, wherein the adjusting ring 17 is preferably designed as a rotor of the torque motor. A stator 18 of the torque motor surrounds the trained as a rotor of the torque motor collar 17 concentric, namely radially outward.

Die zum Betreiben des Torquemotors benötigte elektrische Energie wird von einem Generator 19 der Gasturbine bereitgestellt. Der Generator 19 der Gasturbine verfügt ebenso wie der Torquemotor über einen Läufer 20 sowie einen Ständer 21. Der Läufer 20 des Generators 19 ist als eine freilaufende Generatorturbine ausgebildet, die angetrieben von einer Gasströmung relativ zum Ständer 21 des Generators 19 rotiert und so aus der Bewegungsenergie der Gasströmung elektrische Energie erzeugt. Der Läufer 20 des Generators 19 wird dabei vorzugsweise von einer Gasströmung eines nicht-dargestellten Fans bzw. Fanmoduls der Gasturbine angetrieben. Hierzu ist der Generator 19 stromabwärts des Fans bzw. Fanmoduls positioniert, wobei ein den Generator aufweisendes Generatormodul am stromabwärts liegenden Ende des Fanmoduls lösbar mit dem Fanmodul verbunden ist. Der Generator 19 bzw. der Läufer 20 des Generators 19 wird vorzugsweise von einer Bypass-Gasströmung des Fans bzw. Fanmoduls angetrieben und erzeugt demnach aus dieser Bypass-Gasströmung elektrische Energie.The electrical energy required to operate the torque motor is provided by a generator 19 of the gas turbine. The generator 19 of the gas turbine has as well as the torque motor via a rotor 20 and a stator 21. The rotor 20 of the generator 19 is formed as a free-running generator turbine, which rotates driven by a gas flow relative to the stator 21 of the generator 19 and so from the kinetic energy the gas flow generates electrical energy. The rotor 20 of the generator 19 is preferably driven by a gas flow of a non-illustrated fan or fan module of the gas turbine. For this purpose, the generator 19 is positioned downstream of the fan or fan module, wherein a generator module exhibiting the generator module at the downstream end of the fan module is detachably connected to the fan module. The generator 19 or the rotor 20 of the generator 19 is preferably driven by a bypass gas flow of the fan or fan module and thus generates electrical energy from this bypass gas flow.

Der als freilaufende Generatorturbine ausgebildete Läufer 20 des Generators 19 verfügt über mehrere rotierende Schaufeln 22, wobei die Schaufeln 22 an einem radial innenliegenden Ende über eine Plattform 23 mit einem äußeren Lagerring 26 eines Lagers 27 verbunden sind. Den radial innenliegenden Enden der Schaufeln 22 bzw. der Plattform 23 sind Polstücke 24 zugeordnet. Wie Fig. 1 entnommen werden kann, umschließt der Läufer 20 des Generators 19 zusammen mit den Polstücken 24 radial außen den Ständer 21 des Generators 19. Der Ständer 21 umfasst Wicklungen sowie magnetische Schaltkreise, um letztendlich elektrische Energie aus der Bewegung bzw. Rotation des Läufers 20 des Generators 19 zu erzeugen. Die im Ständer 21 des Generators 19 erzeugte elektrische Energie wird zumindest teilweise dem Ständer 18 des Torquemotors zugeführt und dort zur Bewegung bzw. zum Antrieb des als Läufer des Torquemotors ausgebildeten Stellrings 17 verwendet.Trained as a free-running generator turbine rotor 20 of the generator 19 has a plurality of rotating blades 22, wherein the blades 22 are connected at a radially inner end via a platform 23 with an outer bearing ring 26 of a bearing 27. The radially inner ends of the blades 22 and the platform 23 are assigned pole pieces 24. As Fig. 1 can be removed, the rotor 20 of the generator 19 encloses together with the pole pieces 24 radially outwardly of the stator 21 of the generator 19. The stator 21 includes windings and magnetic circuits to ultimately electrical energy from the movement or rotation of the rotor 20 of the generator 19th to create. The electrical energy generated in the stator 21 of the generator 19 is at least partially supplied to the stator 18 of the torque motor and used there for movement or to drive the adjusting ring 17 designed as a rotor of the torque motor.

Wie Fig. 1 entnommen werden kann, sind der Ständer 21 des Generators 19 und der Ständer 18 des Torquemotors an einer gemeinsamen Halterung 28 gelagert. Der Ständer 21 des Generators 19 umschließt dabei den Ständer 18 des Torquemotors konzentrisch und bildet mit diesem eine Einheit. Demnach umschließt der Ständer 18 des Torquemotors den Läufer des Torquemotors; der Ständer 21 des Generators 19 umschließt den Ständer 18 des Torquemotors und damit auch den Läufer des Torquemotors; der Läufer 20 des Generators 19 umschließt den Ständer 21 des Generators 19 und damit auch den Ständer 18 sowie den Läufer des Torquemotors. Bei dem Läufer des Torquemotors handelt es sich um den Stellring 17.As Fig. 1 can be removed, the stator 21 of the generator 19 and the stator 18 of the torque motor are mounted on a common bracket 28. The stator 21 of the generator 19 encloses the stator 18 of the torque motor concentrically and forms a unit with this. Accordingly, the stator 18 of the torque motor surrounds the rotor of the torque motor; the stator 21 of the generator 19 encloses the stator 18 of the torque motor and thus also the rotor of the torque motor; the rotor 20 of the generator 19 encloses the stator 21 of the generator 19 and thus also the stator 18 and the rotor of the torque motor. The rotor of the torque motor is the adjusting ring 17.

Der Ständer 18 des Torquemotors umfasst wiederum Wicklungen und dem Stellring 17 sind magnetische Elemente 25 zugeordnet. Über den Umfang des Stellrings 17 sind mehrere derartige magnetische Elemente 25 verteilt positioniert, wobei der Abstand zwischen zwei benachbarten magnetischen Elementen 25 derart bemessen ist, dass zwischen denselben die zu den Leitschaufeln 12 führenden Stellhebel 16 befestigbar sind.The stator 18 of the torque motor in turn comprises windings and the adjusting ring 17 are associated with magnetic elements 25. Over the circumference of the adjusting ring 17, a plurality of such magnetic elements 25 are positioned distributed, wherein the distance between two adjacent magnetic elements 25 is dimensioned such that between them the guiding levers 16 leading to the guide vanes 12 are fastened.

In Fig. 1 ist lediglich ein Leitschaufelkranz mit verstellbaren Leitschaufeln 12 gezeigt. Im Sinne der hier vorliegenden Erfindung können auch die Leitschaufeln mehrerer Leitschaufelkränze wie oben beschrieben verstellt werden. Hierbei sind dann die verstellbaren Leitschaufeln eines jeden Leitschaufelkranzes über jeweils einen Stellring verstellbar, wobei vorzugsweise jedem Stellring jedes Leitschaufelkranzes ein Läufer eines Torquemotors zugeordnet ist.In Fig. 1 only one vane ring with adjustable vanes 12 is shown. For the purposes of the present invention, the guide vanes of several vane rings can be adjusted as described above. Here then the adjustable guide vanes of each vane ring are adjustable via a respective adjusting ring, wherein preferably each adjusting ring of each vane ring is associated with a rotor of a torque motor.

Mit der hier vorliegenden Erfindung wird ein völlig neues Konzept zur Verstellung von Leitschaufeln an einer Gasturbine vorgeschlagen. Die erfindungsgemäße Vorrichtung zum Verstellen von Leitschaufeln eliminiert die nach dem Stand der Technik benötigen Hydraulikkolben zum Verstellen des Stellrings. Mit der Erfindung ist es möglich, die von einem Generator erzeugte elektrische Energie zur elektrischen Verstellung der Leitschaufeln zu verwenden und zwar mit nur geringem zusätzlichen Gewicht für die Gasturbine. Mithilfe der erfindungsgemäßen Vorrichtung ist ein besonders schnelles Verstellen der Leitschaufeln möglich, da auf konventionelle elektromotorische Antriebe mit Getriebe verzichtet wird.With the present invention, a completely new concept for adjusting guide vanes on a gas turbine is proposed. The inventive device for adjusting vanes eliminates the need for the prior art hydraulic piston for adjusting the adjusting ring. With the invention it is possible to use the electrical energy generated by a generator for the electrical adjustment of the guide vanes with only a small additional weight for the gas turbine. With the aid of the device according to the invention, a particularly fast adjustment of the guide vanes is possible since conventional electromotive drives with gearboxes are dispensed with.

Claims (9)

  1. A device for adjusting guide vanes of a gas turbine, in which guide vanes (12) are pivotably connected by way of a respective adjusting lever (16) to an adjusting ring (17), wherein the or each adjusting lever (16) acts with a first end on the adjusting ring (17) and with a second end lying opposite the first end on an end of a shaft (15) of the respective guide vane (12),
    characterised in that
    a rotor of a torque motor is associated with the adjusting ring (17), wherein a stator (18) of the torque motor concentrically surrounds the rotor of the torque motor.
  2. A device according to claim 1,
    characterised in that
    the adjusting ring (17) is formed as the rotor of the torque motor, wherein a stator (18) of the torque motor concentrically surrounds the adjusting ring (17) and thus the rotor of the torque motor.
  3. A device according to claim 1 or 2,
    characterised in that
    the electric energy required to operate the torque motor is provided by a generator (19) of the gas turbine, wherein the generator (19) has a stator (21) and a rotor (20), and wherein the rotor (20) of the generator (19) is formed as a free-wheeling generator turbine which, driven by a gas stream, rotates relative to the stator (21) of the generator (19) and thus generates electric energy from the kinetic energy of the gas stream.
  4. A device according to claim 3,
    characterised in that
    the generator (19) is positioned downstream of a fan module in such a way that the rotor (20) of the generator (19) that is formed as a free-wheeling generator turbine is driven by a gas stream of the fan module.
  5. A device according to claim 4,
    characterised in that
    the generator (19) is integrated into a generator module, wherein the generator module is connected to the fan module at the downstream end of the fan module, and wherein the generator (19) generates electric energy from a bypass gas stream of the fan module.
  6. A device according to one or more of claims 2 to 5,
    characterised in that
    the rotor (20) of the generator (19) that is formed as a free-wheeling generator turbine has a plurality of rotating blades (22) with pole pieces (24) associated with the blades (22), wherein the pole pieces are associated with radially internal ends of the rotating blades (22) of the rotor (20) that is formed as a free-wheeling generator turbine, wherein the rotor (20) radially surrounds the stator (18) of the generator (19) on the outside.
  7. A device according to one or more of claims 1 to 6,
    characterised in that
    the stator (18) of the torque motor and the stator (21) of the generator (19) are mounted on a common holding support (28), wherein the stator (21) of the generator (19) concentrically surrounds the stator (18) of the torque motor.
  8. A device according to one or more of claims 1 to 7,
    characterised in that
    the rotor of the torque motor has a plurality of magnetic elements (25) distributed over its circumference.
  9. A device according to claim 8,
    characterised in that
    the distance between the magnetic elements (25) is dimensioned in such a way that an adjusting lever (16) leading to an adjustable guide vane (12) can be secured between two adjacent magnetic elements (25).
EP05706718A 2004-01-31 2005-01-28 Device for the adjustment of guide blades Not-in-force EP1709300B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004004976A DE102004004976A1 (en) 2004-01-31 2004-01-31 Device for adjusting vanes
PCT/DE2005/000130 WO2005073520A1 (en) 2004-01-31 2005-01-28 Device for the adjustment of guide blades

Publications (2)

Publication Number Publication Date
EP1709300A1 EP1709300A1 (en) 2006-10-11
EP1709300B1 true EP1709300B1 (en) 2012-09-12

Family

ID=34801394

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Application Number Title Priority Date Filing Date
EP05706718A Not-in-force EP1709300B1 (en) 2004-01-31 2005-01-28 Device for the adjustment of guide blades

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US (1) US7850422B2 (en)
EP (1) EP1709300B1 (en)
DE (1) DE102004004976A1 (en)
WO (1) WO2005073520A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006025831B4 (en) * 2006-06-02 2013-10-31 Rovema Gmbh Device for welding plastic for packaging purposes (torque motor)
FR2915523A1 (en) * 2007-04-27 2008-10-31 Snecma Sa DEVICE FOR GENERATING ELECTRIC ENERGY IN A DOUBLE-BODY GAS TURBINE ENGINE
DE102018210085A1 (en) * 2018-06-21 2019-12-24 Continental Automotive Gmbh Compressor with directly driven variable iris and charging device
US20240229673A9 (en) * 2022-10-21 2024-07-11 Rolls-Royce North American Technologies Inc. Variable stator vane assembly with magnetic actuation rotor for gas turbine engines

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Publication number Priority date Publication date Assignee Title
NL182289B (en) 1953-10-09 Alusuisse CERAMIC FOAM FILTER AND PROCEDURE FOR MANUFACTURE THEREOF.
US2823700A (en) * 1954-11-19 1958-02-18 Westinghouse Electric Corp Fluid flow control apparatus
US3449914A (en) * 1967-12-21 1969-06-17 United Aircraft Corp Variable flow turbofan engine
GB1499531A (en) * 1976-05-24 1978-02-01 Secr Defence Apparatus for varying the incidence of turbomachinery stator blades
US4718819A (en) * 1983-02-25 1988-01-12 Teledyne Industries, Inc. Variable geometry device for turbine compressor outlet
JPS60169442A (en) * 1984-02-10 1985-09-02 Mitsubishi Chem Ind Ltd Production of cinnamic acid ester
DE3913102C1 (en) 1989-04-21 1990-05-31 Mtu Muenchen Gmbh
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GB2372157B (en) * 2001-02-09 2005-07-06 Rolls Royce Plc A gas turbine with an electrical machine
US6873085B2 (en) * 2001-05-16 2005-03-29 G & G Technology, Inc. Brushless motor

Also Published As

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US20070280821A1 (en) 2007-12-06
US7850422B2 (en) 2010-12-14
WO2005073520A1 (en) 2005-08-11
DE102004004976A1 (en) 2005-08-18
EP1709300A1 (en) 2006-10-11

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