WO2006086945A1 - Bearing arrangement in a gas turbine aircraft engine - Google Patents

Bearing arrangement in a gas turbine aircraft engine Download PDF

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Publication number
WO2006086945A1
WO2006086945A1 PCT/DE2006/000209 DE2006000209W WO2006086945A1 WO 2006086945 A1 WO2006086945 A1 WO 2006086945A1 DE 2006000209 W DE2006000209 W DE 2006000209W WO 2006086945 A1 WO2006086945 A1 WO 2006086945A1
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WO
WIPO (PCT)
Prior art keywords
bearing
stator
bearing ring
ring
actuators
Prior art date
Application number
PCT/DE2006/000209
Other languages
German (de)
French (fr)
Inventor
Alexander Böck
Carsten SCHÖNHOFF
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
Priority to US11/816,618 priority Critical patent/US20090226306A1/en
Priority to EP06705934A priority patent/EP1848877A1/en
Publication of WO2006086945A1 publication Critical patent/WO2006086945A1/en

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Classifications

    • 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
    • F16C23/00—Bearings for exclusively rotary movement adjustable for aligning or positioning
    • F16C23/06—Ball or roller bearings
    • F16C23/08—Ball or roller bearings self-adjusting
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F01D17/02—Arrangement of sensing elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/66—Mechanical actuators
    • 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
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines

Definitions

  • the invention relates to a bearing arrangement, in particular for a gas turbine aircraft engine, according to the preamble of claim 1.
  • rotors for example rotating blades
  • a stator for example a stationary housing and likewise fixed guide vanes.
  • Bearing arrangements for mounting the rotor relative to the stator have a stator or fixed bearing ring and a rotorseiti- gene or rotating bearing ring, wherein between the stator-side bearing ring and the rotor-side bearing ring rolling elements are positioned.
  • On the stator bearing ring usually hydraulic damping elements, so-called Squeezefilmdämpfer or Quetschöldämpfer arranged, which dampen the vibrations of the rotor.
  • Such crimping oil dampers allow a radial displacement of the bearings in the order of up to 0.2 mm.
  • gaps between the rotor and the stator must be minimized. These are, for example, gaps between a hub of the rotor and radially inner ends of fixed vanes, and gaps between radially outer ends of the blades and a fixed housing.
  • a positionally accurate mounting of the rotor relative to the stator is required.
  • forces or torques act on the bearing assemblies as a result of maneuvering loads.
  • the housing are essentially deformed, resulting in a worse splitting behavior.
  • Maneuver loads also ensure that undesirable bearing displacements occur on bearings damped with squeeze-film dampers.
  • the positionally accurate mounting of the rotor relative to the stator and thus an exact gap position between the stator and the rotor is made more difficult.
  • the present invention based on the problem to provide a novel bearing assembly.
  • This problem is solved by a bearing arrangement in the sense of claim 1.
  • the stator-side bearing ring on the one hand associated with transducers for determining the position of the stator bearing ring and on the other hand actuators for influencing the position of the stator bearing ring.
  • At least three measuring and adjusting members are assigned to the stator-side bearing ring, which are distributed uniformly over the circumference of the stator bearing ring, each of the measuring and control elements a transducer for determining the position of the stator bearing ring and an actuator for influencing the position of the stator bearing ring having.
  • the stator-side bearing ring is adjustable by means of the actuators of the measuring and actuators in two directions, each extending perpendicular to a rotational axis of the rotor-side bearing ring adjustable.
  • the sensors and actuators also assume the task of bearing damping or compensate for a residual imbalance of the rotor by "tracking" of the bearing about the axis of inertia of the rotor.
  • FIG. 1 shows a detail of a gas turbine aircraft engine in the region of a bearing arrangement according to the invention
  • FIG. 2 shows a detail of the bearing arrangement according to FIG. 1.
  • FIGS. 1 and 2. 1 shows a detail of a gas turbine aircraft engine in the region of a bearing arrangement 10 according to the invention.
  • the bearing arrangement 10 according to the invention comprises a stator-side, stationary bearing ring 11 and a rotor-side, rotating bearing ring 12.
  • the stator-side stationary bearing ring 11 is designed as a bearing outer ring and the rotor-side , rotating bearing ring 12 is formed as a bearing inner ring.
  • the rotor-side, rotating bearing inner ring 12 is connected via a flange 14 with a rotor disk 15 rotating blades and a likewise rotating seal carrier 16. 1, the connection of the rotor-side bearing inner ring 12 with the seal carrier 16 and the rotor disk 15 via a screw 17.
  • the stator-side, fixed bearing outer ring 11 is connected via a so-called circumferential securing 18 with a fixed housing part 19. About the circumference fuse 18, the relative position of the bearing assembly is fixed in the circumferential direction.
  • the stator-side, fixed bearing outer ring 11 a plurality of measuring and actuators 20 are assigned.
  • the stationary bearing outer ring 11 at least three measuring and control elements 20 are assigned, which are distributed uniformly over the circumference of the fixed bearing outer ring 11.
  • Each of the measuring and control elements 20 has a transducer, not shown, and an actuator 21. Using the transducers, the position of the fixed bearing outer ring 11 can be detected relative to a desired position.
  • the transducers transmit corresponding actual values of the position of the bearing outer ring 11 to a control or regulating device, not shown, wherein the control or regulating device with the provided actual values of the relative position between the fixed bearing outer ring 11 and the target position provided by the transducers Comparing setpoint values and, depending on this, generates control signals for the actuators 21.
  • the position of the stator bearing outer ring 11 and the entire bearing assembly 10 is adjustable based on the control signals generated by the control device or control device, in two directions, each perpendicular to a rotational axis of the rotor or Rotor-side bearing inner ring 12 extend.
  • the actuators 21 thus act in the radial direction on the stationary bearing ring 11, wherein the circumferential securing 18 allows a displacement of the bearing assembly 10 in the radial direction.
  • the actuators 21 of the measuring and actuating elements 20 engage in recesses 22 of the stator bearing outer ring 11.
  • the actuators 21 are in each case via a spherical bearing surface 23 with the bearing outer ring 11 in contact.
  • the actuators 21 are not positively connected to the housing 19 and the bearing outer ring 11, but this connection is established via a control of the actuators 21.
  • the point can be determined at the just contact still exists on the respective spherical bearing surface 23 to the bearing outer ring 11.
  • the spherical contact surfaces 23 are always held in contact with the bearing outer ring 11 via the control. It is also possible to determine and regulate the corresponding contact forces.
  • the actuators 21 are preferably designed in the sense of the present invention as piezoceramic actuators.
  • the bearings 21 may be formed as oil storage, air bearings or magnetic bearings.
  • the measuring and control elements 20 are connected via screw 24 with the stator-side housing part 19.
  • the bearing assembly With the bearing assembly according to the invention, it is possible in a particularly simple manner to compensate for shifts occurring during operation of the gas turbine aircraft engine bearing assembly with squeeze film damper by an active control.
  • the bearing assembly is about actuators in two directions, which are perpendicular to the axis of rotation of the rotor, adjustable.
  • the bearing assembly is compensated so as to maintain exactly gaps between the rotor and the stator. Oscillations or tumbling movements of the bearing arrangement that occur during operation can be compensated or damped with the bearing arrangement 10 according to the invention, as a result of which loads acting on an engine suspension can be reduced.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Support Of The Bearing (AREA)

Abstract

The invention relates to a bearing arrangement, especially for a gas turbine aircraft engine, said arrangement comprising a first bearing ring (11) which is fixed and on the stator side, and a second bearing ring (12) which is rotatable and on the rotor side. Rolling bodies (13) are arranged between the stator-side bearing ring (11) and the rotor-side bearing ring (12). Transducers for determining the position of the stator-side bearing ring (11), and actuators (21) for influencing the position of the stator-side bearing ring (11), are associated with the stator-side bearing ring (11).

Description

LAGERANORDNUWG IN EINEM GASTURBINENFLUGTRIEBWERK STORAGE PLANNING IN A GAS TURBINE FLIGHT TRUCTURE
Die Erfindung betrifft eine Lageranordnung, insbesondere für ein Gastur- binenflugtriebwerk, nach dem Oberbegriff des Anspruchs 1.The invention relates to a bearing arrangement, in particular for a gas turbine aircraft engine, according to the preamble of claim 1.
In Gasturbinenflugtriebwerken sind Rotoren, zum Beispiel rotierende Laufschaufeln, gegenüber einem Stator, zum Beispiel einem feststehenden Gehäuse sowie ebenfalls feststehenden Leitschaufeln, drehbar gelagert. Lageranordnungen zur Lagerung des Rotors gegenüber dem Stator verfügen über einen statorseitigen bzw. feststehenden Lagerring sowie einen rotorseiti- gen bzw. drehenden Lagerring, wobei zwischen dem statorseitigen Lagerring und dem rotorseitigen Lagerring Wälzkörper positioniert sind. An dem statorseitigen Lagerring sind üblicherweise hydraulische Dämpfungselemente, sogenannte Squeezefilmdämpfer bzw. Quetschöldämpfer, angeordnet, welche die Schwingungen des Rotors dämpfen. Solche Quetschöldämpfer lassen eine Radialverschiebung der Lager in einer Größenordung von bis zu 0,2 mm zu.In gas turbine aircraft engines, rotors, for example rotating blades, are rotatably mounted relative to a stator, for example a stationary housing and likewise fixed guide vanes. Bearing arrangements for mounting the rotor relative to the stator have a stator or fixed bearing ring and a rotorseiti- gene or rotating bearing ring, wherein between the stator-side bearing ring and the rotor-side bearing ring rolling elements are positioned. On the stator bearing ring usually hydraulic damping elements, so-called Squeezefilmdämpfer or Quetschöldämpfer arranged, which dampen the vibrations of the rotor. Such crimping oil dampers allow a radial displacement of the bearings in the order of up to 0.2 mm.
Zur Optimierung des Wirkungsgrads von Gasturbinenflugtriebwerken müssen Spalte zwischen dem Rotor und dem Stator minimiert werden. Hierbei handelt es sich zum Beispiel um Spalte zwischen einer Nabe des Rotors und radial innen liegenden Enden feststehender Leitschaufeln sowie um Spalte zwischen radial außenliegenden Enden der Laufschaufeln und einem feststehenden Gehäuse. Zur exakten Spalthaltung dieser Spalte und damit zur Optimierung des Wirkungsgrads des Gasturbinenflugtriebwerks ist unter anderem eine positionsgenaue Lagerung des Rotors gegenüber dem Stator erforderlich. Im Betrieb eines Gasturbinenflugtriebwerks wirken zum Beispiel infolge von Manöverlasten Kräfte bzw. Momente auf die Lageranordnungen. Durch Manöverlasten, Betriebskräfte und Betriebsmomente werden im wesentlichen die Gehäuse verformt, wodurch sich ein schlechteres Spaltverhalten ergibt. Manöverlasten sorgen weiterhin dafür, dass an mit Quetschfilm- dämpfern gedämpften Lagern unerwünschte Lagerverschiebungen auftreten. Die positionsgenaue Lagerung des Rotors gegenüber dem Stator und damit eine exakte Spalthaltung zwischen dem Stator und dem Rotor wird hierdurch erschwert .To optimize the efficiency of gas turbine aircraft engines, gaps between the rotor and the stator must be minimized. These are, for example, gaps between a hub of the rotor and radially inner ends of fixed vanes, and gaps between radially outer ends of the blades and a fixed housing. For exact cleavage of this column and thus to optimize the efficiency of the gas turbine aircraft engine, among other things, a positionally accurate mounting of the rotor relative to the stator is required. During operation of a gas turbine aircraft engine, for example, forces or torques act on the bearing assemblies as a result of maneuvering loads. By Manöverlasten, operating forces and operating torques, the housing are essentially deformed, resulting in a worse splitting behavior. Maneuver loads also ensure that undesirable bearing displacements occur on bearings damped with squeeze-film dampers. The positionally accurate mounting of the rotor relative to the stator and thus an exact gap position between the stator and the rotor is made more difficult.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde eine neuartige Lageranordnung zu schaffen. Dieses Problem wird durch eine Lageranordnung im Sinne des Patentanspruchs 1 gelöst. Erfindungsgemäß sind dem statorseitigen Lagerring einerseits Messwertaufnehmer zur Ermittlung der Position des statorseitigen Lagerrings und andererseits Aktuatoren zur Beeinflussung der Position des statorseitigen Lagerrings zugeordnet.On this basis, the present invention based on the problem to provide a novel bearing assembly. This problem is solved by a bearing arrangement in the sense of claim 1. According to the invention, the stator-side bearing ring on the one hand associated with transducers for determining the position of the stator bearing ring and on the other hand actuators for influencing the position of the stator bearing ring.
Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, dem statorseitigen bzw. feststehenden Lagerring mehrere Messwertaufnehmer sowie mehrere Aktuatoren zuzuordnen. Mit Hilfe der Messwertaufnehmer kann die Position des feststehenden Lagerrings erfasst werden, mit Hilfe des Aktuatoren ist eine Beeinflussung der Position des statorseitigen bzw. feststehenden Lagerrings möglich. Unerwünschte Verschiebung der Lager mit Quetschfilmdämpfern, die sich während des Betriebs zum Beispiel infolge von Manöverlasten ergeben, können so ausgeglichen bzw. kompensiert werden.For the purposes of the present invention, it is proposed to assign a plurality of transducers and a plurality of actuators to the stator-side or stationary bearing ring. With the help of the transducers, the position of the stationary bearing ring can be detected, with the help of the actuator influencing the position of the stator or fixed bearing ring is possible. Undesirable shift of the bearings with squeeze film dampers, which arise during operation, for example due to maneuvering, can be compensated or compensated.
Vorzugsweise sind dem statorseitigen Lagerring mindestens drei Mess- und Stellglieder zugeordnet, die über den Umfang des statorseitigen Lagerrings gleichmäßig verteilt sind, wobei jedes der Mess- und Stellglieder einen Messwertaufnehmer zur Ermittlung der Position des statorseitigen Lagerrings und einen Aktuator zur Beeinflussung der Position des statorseitigen Lagerrings aufweist. Der statorseitige Lagerring ist mit Hilfe der Aktuatoren der Mess- und Stellglieder in zwei Richtungen, die jeweils senkrecht zu einer Drehachse des rotorseitigen Lagerrings verlaufen, verstellbar.Preferably, at least three measuring and adjusting members are assigned to the stator-side bearing ring, which are distributed uniformly over the circumference of the stator bearing ring, each of the measuring and control elements a transducer for determining the position of the stator bearing ring and an actuator for influencing the position of the stator bearing ring having. The stator-side bearing ring is adjustable by means of the actuators of the measuring and actuators in two directions, each extending perpendicular to a rotational axis of the rotor-side bearing ring adjustable.
Die Sensoren und Aktuatoren übernehmen auch die Aufgabe der Lagerdämpfung bzw. kompensieren eine Restunwucht des Rotors durch „Nachführen" des Lagers um die Trägheitsachse des Rotors .The sensors and actuators also assume the task of bearing damping or compensate for a residual imbalance of the rotor by "tracking" of the bearing about the axis of inertia of the rotor.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ein Ausführungsbeispiel der Erfindung wird, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:Preferred embodiments of the invention will become apparent from the dependent claims and the description below. An embodiment of the invention will be described, without being limited thereto, with reference to the drawing. Showing:
Fig. 1 einen Ausschnitt aus einem Gasturbinenflugtriebwerk im Bereich einer erfindungsgemäßen Lageranordnung; und Fig. 2 ein Detail der Lageranordnung gemäß Fig. 1.1 shows a detail of a gas turbine aircraft engine in the region of a bearing arrangement according to the invention; and FIG. 2 shows a detail of the bearing arrangement according to FIG. 1.
Nachfolgend wird die Erfindung unter Bezugnahme auf Fig. 1 und 2 in größerem Detail beschrieben. Fig. 1 zeigt einen Ausschnitt aus einem Gasturbinenflugtriebwerk im Bereich einer erfindungsgemäßen Lageranordnung 10. Die erfindungsgemäße La- geranordnung 10 umfasst einen statorseitigen, feststehenden Lagerring 11 und einen rotorseitigen, sich drehenden Lagerring 12. Der statorseitige, feststehende Lagerring 11 ist als Lageraußenring und der rotorseitige, sich drehende Lagerring 12 als Lagerinnenring ausgebildet . Zwischen dem Lageraußenring 11 und dem Lagerinnenring 12 sind mehrere Wälzkörper 13 angeordnet .The invention will be described in more detail below with reference to FIGS. 1 and 2. 1 shows a detail of a gas turbine aircraft engine in the region of a bearing arrangement 10 according to the invention. The bearing arrangement 10 according to the invention comprises a stator-side, stationary bearing ring 11 and a rotor-side, rotating bearing ring 12. The stator-side stationary bearing ring 11 is designed as a bearing outer ring and the rotor-side , rotating bearing ring 12 is formed as a bearing inner ring. Between the bearing outer ring 11 and the bearing inner ring 12 a plurality of rolling elements 13 are arranged.
Wie Fig. 1 entnommen werden kann, ist der rotorseitige, sich drehende Lagerinnenring 12 über einen Flansch 14 mit einer Rotorscheibe 15 rotierender Laufschaufeln sowie einem ebenfalls rotierenden Dichtungsträger 16 verbunden. Gemäß Fig. 1 erfolgt die Verbindung des rotorseitigen Lagerinnenrings 12 mit dem Dichtungsträger 16 und der Rotorscheibe 15 über eine Schraubverbindung 17. Der statorseitige, feststehende Lageraußenring 11 ist über eine sogenannte Umfangssicherung 18 mit einem feststehenden Ge- häuseteil 19 verbunden. Über die Umfangssicherung 18 wird die Relativposition der Lageranordnung in Umfangsrichtung fixiert.1, the rotor-side, rotating bearing inner ring 12 is connected via a flange 14 with a rotor disk 15 rotating blades and a likewise rotating seal carrier 16. 1, the connection of the rotor-side bearing inner ring 12 with the seal carrier 16 and the rotor disk 15 via a screw 17. The stator-side, fixed bearing outer ring 11 is connected via a so-called circumferential securing 18 with a fixed housing part 19. About the circumference fuse 18, the relative position of the bearing assembly is fixed in the circumferential direction.
Im Sinne der hier vorliegenden Erfindung sind dem statorseitigen, feststehenden Lageraußenring 11 mehrere Mess- und Stellglieder 20 zugeordnet. Dabei sind dem feststehenden Lageraußenring 11 mindestens drei Mess- und Stellglieder 20 zugeordnet, die über den Umfang des feststehenden Lageraußenrings 11 gleichmäßig verteilt sind. Jedes der Mess- und Stellglieder 20 verfügt über einen nicht-dargestellten Messwertaufnehmer sowie einen Aktuator 21. Mit Hilfe der Messwertaufnehmer kann die Position des feststehenden Lageraußenrings 11 relativ zu einer Sollposition erfasst werden. Die Messwertaufnehmer übermitteln entsprechende Ist-Werte der Position des Lageraußenrings 11 an eine nicht-dargestellte Steuerungs- bzw. Regelungseinrichtung, wobei die Steuerungs- bzw. Regelungseinrichtung die von den Messwertaufnehmern bereitgestellten Ist-Werte der Relativposition zwischen dem feststehenden Lageraußenring 11 und der Sollposition mit vorgegebenen Soll-Werten vergleicht und abhängig hiervon Stellsignale für die Aktuatoren 21 erzeugt. Mit Hilfe der Aktuatoren 21 ist auf Basis der von der nicht-dargestellten Steuerungs- bzw. Regelungseinrichtung erzeugten Stellsignale die Position des statorseitigen Lageraußenrings 11 bzw. der gesamten Lageranordnung 10 verstellbar, und zwar in zwei Richtungen, die jeweils senkrecht zu einer Drehachse des Rotors bzw. rotorseitigen Lagerinnenrings 12 verlaufen. Die Aktuatoren 21 wirken demnach in radialer Richtung auf den feststehenden Lagerring 11, wobei die Umfangssicherung 18 eine Verschiebbarkeit der Lageranordnung 10 in radialer Richtung zulässt . Wie insbesondere Fig. 2 entnommen werden kann, greifen die Aktuatoren 21 der Mess- und Stellglieder 20 in Ausnehmungen 22 des statorseitigen Lageraußenrings 11 ein. Die Aktuatoren 21 stehen dabei über jeweils eine ballige Anlagefläche 23 mit dem Lageraußenring 11 in Kontakt.For the purposes of the present invention, the stator-side, fixed bearing outer ring 11 a plurality of measuring and actuators 20 are assigned. In this case, the stationary bearing outer ring 11 at least three measuring and control elements 20 are assigned, which are distributed uniformly over the circumference of the fixed bearing outer ring 11. Each of the measuring and control elements 20 has a transducer, not shown, and an actuator 21. Using the transducers, the position of the fixed bearing outer ring 11 can be detected relative to a desired position. The transducers transmit corresponding actual values of the position of the bearing outer ring 11 to a control or regulating device, not shown, wherein the control or regulating device with the provided actual values of the relative position between the fixed bearing outer ring 11 and the target position provided by the transducers Comparing setpoint values and, depending on this, generates control signals for the actuators 21. With the aid of the actuators 21, the position of the stator bearing outer ring 11 and the entire bearing assembly 10 is adjustable based on the control signals generated by the control device or control device, in two directions, each perpendicular to a rotational axis of the rotor or Rotor-side bearing inner ring 12 extend. The actuators 21 thus act in the radial direction on the stationary bearing ring 11, wherein the circumferential securing 18 allows a displacement of the bearing assembly 10 in the radial direction. As can be seen in particular from FIG. 2, the actuators 21 of the measuring and actuating elements 20 engage in recesses 22 of the stator bearing outer ring 11. The actuators 21 are in each case via a spherical bearing surface 23 with the bearing outer ring 11 in contact.
Die Aktuatoren 21 sind nicht formschlüssig mit dem Gehäuse 19 und dem Lageraußenring 11 verbunden, vielmehr wird diese Verbindung über eine Regelung der Aktuatoren 21 etabliert. Über einen Vergleich der Signale der Messwertaufnehmer bzw. Wegsensoren und der Steuerspannung des jeweiligen Aktuators 21 kann der Punkt ermittelt werden, an dem gerade noch Kontakt an der jeweiligen balligen Anlagefläche 23 zum Lageraußenring 11 besteht. Über einen Vergleich der Ist-Werte und Soll-Werte der Mess- und Stellglieder 20 werden über die Regelung die balligen Anlageflächen 23 stets in Kontakt zum Lageraußenring 11 gehalten. Es ist auch möglich, die entsprechenden Anpresskräfte zu ermitteln und zu regeln.The actuators 21 are not positively connected to the housing 19 and the bearing outer ring 11, but this connection is established via a control of the actuators 21. By comparing the signals of the transducers or displacement sensors and the control voltage of the respective actuator 21, the point can be determined at the just contact still exists on the respective spherical bearing surface 23 to the bearing outer ring 11. By comparing the actual values and desired values of the measuring and control elements 20, the spherical contact surfaces 23 are always held in contact with the bearing outer ring 11 via the control. It is also possible to determine and regulate the corresponding contact forces.
Die Aktuatoren 21 sind im Sinne der hier vorliegenden Erfindung vorzugsweise als piezokeramische Aktuatoren ausgebildet. Die Lager 21 können als Öllager, Luftlager oder auch Magnetlager ausgebildet sein. Die Mess- und Stellglieder 20 sind über Schraubverbindungen 24 mit dem statorseitigen Gehäuseteil 19 verbunden.The actuators 21 are preferably designed in the sense of the present invention as piezoceramic actuators. The bearings 21 may be formed as oil storage, air bearings or magnetic bearings. The measuring and control elements 20 are connected via screw 24 with the stator-side housing part 19.
Mit der erfindungsgemäßen Lageranordnung ist es auf besonders einfache Art und Weise möglich, während des Betriebs des Gasturbinenflugtriebwerks auftretende Verschiebungen der Lageranordnung mit Quetschfilmdämpfer durch eine aktive Regelung zu kompensieren. So ist die Lageranordnung ü- ber Aktuatoren in zwei Richtungen, die senkrecht zur Drehachse des Rotors verlaufen, verstellbar. Zusätzlich können insbesondere auf das Gasturbi- nenflugtriebwerk einwirkende Manöverlasten kompensiert werden, um so Spalte zwischen dem Rotor und dem Stator exakt einzuhalten. Sich während des Betriebs einstellende Schwingungen oder Taumelbewegungen der Lageranordnung können mit der erfindungsgemäßen Lageranordnung 10 kompensiert bzw. gedämpft werden, wodurch auf eine Triebwerksaufhängung wirkende Belastungen reduziert werden können. With the bearing assembly according to the invention, it is possible in a particularly simple manner to compensate for shifts occurring during operation of the gas turbine aircraft engine bearing assembly with squeeze film damper by an active control. Thus, the bearing assembly is about actuators in two directions, which are perpendicular to the axis of rotation of the rotor, adjustable. In addition, especially on the gas turbine nenflugtriebwerk acting maneuver loads can be compensated so as to maintain exactly gaps between the rotor and the stator. Oscillations or tumbling movements of the bearing arrangement that occur during operation can be compensated or damped with the bearing arrangement 10 according to the invention, as a result of which loads acting on an engine suspension can be reduced.

Claims

Patentansprüche claims
1. Lageranordnung, insbesondere für ein Gasturbinenflugtriebwerk, mit einem ersten, statorseitigen bzw. feststehenden Lagerring (11) und einem zweiten, rotorseitigen bzw. drehenden Lagerring (12) , wobei zwischen dem statorseitigen Lagerring (11) und dem rotorseitigen Lagerring (12) Wälzkörper (13) angeordnet sind, dadurch gekennzeichnet, dass dem statorseitigen Lagerring (11) einerseits Messwertaufnehmer zur Ermittlung der Position des statorseitigen Lagerrings (11) und andererseits Aktuatoren (21) zur Beeinflussung der Position des statorseitigen Lagerrings (11) zugeordnet sind.1. Bearing arrangement, in particular for a gas turbine aircraft engine, with a first, stator-side or fixed bearing ring (11) and a second rotor-side or rotating bearing ring (12), wherein between the stator-side bearing ring (11) and the rotor-side bearing ring (12) rolling elements (13) are arranged, characterized in that the stator bearing ring (11) on the one hand transducers for determining the position of the stator bearing ring (11) and on the other hand actuators (21) are assigned to influence the position of the stator bearing ring (11).
2. Lageranordnung nach Anspruch 1 , dadurch gekennzeichnet , dass dem statorseitigen Lagerring (11) kombinierte Mess- und Stellglieder (20) zugeordnet sind, wobei jedes Mess- und Stellglied (20) einen Messwertaufnehmer zur Ermittlung der Position des statorseitigen Lagerrings (11) und einen Aktuator (21) zur Beeinflussung der Position des statorseitigen Lagerrings (11) aufweist.2. Bearing arrangement according to claim 1, characterized in that the stator bearing ring (11) combined measuring and actuators (20) are assigned, each measuring and actuator (20) has a transducer for determining the position of the stator bearing ring (11) and an actuator (21) for influencing the position of the stator bearing ring (11).
3. Lageranordnung nach Anspruch 2 , dadurch gekennzeichnet, dass dem statorseitigen Lagerring (11) mindestens drei Mess- und Stellglieder (20) zugeordnet sind, die über den Umfang des statorseitigen Lagerrings (11) gleichmäßig verteilt sind.3. Bearing arrangement according to claim 2, characterized in that the stator bearing ring (11) at least three measuring and adjusting members (20) are associated, which are distributed uniformly over the circumference of the stator bearing ring (11).
4. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 3 , dadurch gekennzeichnet, dass die Messwertaufnehmer die Position des statorseitigen Lagerrings (11) relativ zu einer Sollposition erfassen.4. Bearing arrangement according to one or more of claims 1 to 3, characterized in that the transducers detect the position of the stator bearing ring (11) relative to a desired position.
5. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Aktuatoren (21) die Position des statorseitigen Lagerrings (11) relativ zu einer Sollposition beeinflussen. 5. Bearing arrangement according to one or more of claims 1 to 4, characterized in that the actuators (21) influence the position of the stator bearing ring (11) relative to a desired position.
6. Lageranordnung nach, einem oder mehreren der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der statorseitige Lagerring (11) mit Hilfe der Aktuatoren (21) der Mess- und Stellglieder (20) in zwei Richtungen, die jeweils senkrecht zu einer Drehachse des rotorseitigen Lagerrings (12) verlaufen, verstellbar ist.6. Bearing arrangement according to one or more of claims 1 to 5, characterized in that the stator bearing ring (11) by means of the actuators (21) of the measuring and actuating members (20) in two directions, each perpendicular to a rotation axis of Rotor-side bearing ring (12) extend, is adjustable.
7. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Aktuatoren (21) als piezokeramische Aktuatoren ausgebildet sind.7. Bearing arrangement according to one or more of claims 1 to 6, characterized in that the actuators (21) are designed as piezoceramic actuators.
8. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 7 , dadurch gekennzeichnet, dass die von den Messwertaufnehmern der Mess- und Stellglieder (20) ermittelten Istwerte der Position des statorseitigen Lagerrings (11) in einer Steuerungs- bzw. Regelungseinrichtung mit Sollwerten vergleichbar sind, wobei die Steuerungs- bzw. Regelungseinrichtung abhängig von dem Vergleich zwischen Sollwerten und Istwerten Stellsignale für die Aktuatoren (21) erzeugt.8. Bearing arrangement according to one or more of claims 1 to 7, characterized in that the measured values of the position of the stator-side bearing ring (11) determined by the transducers of the measuring and control elements (20) are comparable with reference values in a control or regulating device , wherein the control or regulating device generates control signals for the actuators (21) as a function of the comparison between desired values and actual values.
9. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der statorseitige Lagerring (11) als Lageraußenring und der ro- torseitige Lagerring (12) als Lagerinnenring ausgebildet ist.9. Bearing arrangement according to one or more of claims 1 to 8, characterized in that the stator bearing ring (11) is designed as a bearing outer ring and the rotor-side bearing ring (12) as a bearing inner ring.
10. Lageranordnung nach einem oder mehreren der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Aktuatoren (21) über jeweils eine ballige Anlagefläche (23) mit dem Lageraußenring (11) in Kontakt stehen, und dass über einen Vergleich der Ist-Werte und Soll-Werte der Mess- und Stellglieder (20) die balligen Anlageflächen (23) stets in Kontakt zum Lageraußenring (11) gehalten werden. 10. Bearing arrangement according to one or more of claims 1 to 9, characterized in that the actuators (21) via a respective spherical bearing surface (23) with the bearing outer ring (11) are in contact, and that a comparison of the actual values and Target values of the measuring and control elements (20) the spherical contact surfaces (23) are always kept in contact with the bearing outer ring (11).
PCT/DE2006/000209 2005-02-19 2006-02-08 Bearing arrangement in a gas turbine aircraft engine WO2006086945A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US11/816,618 US20090226306A1 (en) 2005-02-19 2006-02-08 Apparatus and method for adjusting a bearing array in a gas turbine aircraft engine
EP06705934A EP1848877A1 (en) 2005-02-19 2006-02-08 Bearing arrangement in a gas turbine aircraft engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005007776A DE102005007776A1 (en) 2005-02-19 2005-02-19 bearing arrangement
DE102005007776.5 2005-02-19

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WO2006086945A1 true WO2006086945A1 (en) 2006-08-24

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EP (1) EP1848877A1 (en)
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WO (1) WO2006086945A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100247015A1 (en) * 2009-03-25 2010-09-30 Rolls-Royce Plc Bearing arrangement
US8840114B2 (en) 2011-03-29 2014-09-23 Rolls-Royce Plc Assembly comprising a rotatable component
EP3670942A1 (en) * 2018-12-17 2020-06-24 Rolls-Royce plc Bearing assembly including active vibration control

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008008727A1 (en) 2008-02-12 2009-08-13 Schaeffler Kg Bearing, particularly rolling or sliding bearing, has position sensor to supply correspondingly similar signals to relative position of both bearing parts, and is comprised of potentiometer, which has resistance path and position finger
DE102008026081A1 (en) 2008-05-30 2009-12-31 Schaeffler Kg Storage device with position sensor
US9328626B2 (en) * 2012-08-21 2016-05-03 United Technologies Corporation Annular turbomachine seal and heat shield
US9845700B2 (en) * 2013-03-12 2017-12-19 Rolls-Royce North American Technologies Inc. Active seal system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4548546A (en) * 1981-11-05 1985-10-22 S.N.E.C.M.A. Adjustment system of centering a turbomachine wheel and mounted turbomachine by way of permitting the application of said system
DE3831928A1 (en) * 1988-09-20 1990-03-22 Friedrich Prof Dr Pfeiffer Device for stabilising axles or shafts
US5221146A (en) * 1991-04-16 1993-06-22 Nissan Motor Co., Ltd. Structure of bearing of geared shaft
EP1134443A2 (en) * 2000-03-15 2001-09-19 Umbra Cuscinetti S.p.A. A device for measuring and adjusting preloading on bearings
DE10304607A1 (en) * 2003-02-05 2004-08-19 Fag Kugelfischer Ag Detection of pre- or over-travel of bearings in a roller bearing by calculation of first and second signal periods of a strain gauge and comparison of a difference value with a threshold in order to detect pre- or over-travel
DE102004024851A1 (en) * 2004-05-19 2005-12-22 Fag Kugelfischer Ag & Co. Ohg Machine part storage arrangement for use in paper machine, has piezo components arranged in construction unit that one of section of unit is clamped by force less than or equal to zero between components, where components are actuators
WO2006015048A1 (en) * 2004-07-27 2006-02-09 The Timken Company Adaptive bearing system containing a piezoelectric actuator for controlling setting

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6491497B1 (en) * 2000-09-22 2002-12-10 General Electric Company Method and apparatus for supporting rotor assemblies during unbalances
KR100413061B1 (en) * 2001-01-19 2003-12-31 한국과학기술연구원 Smart foil journal bearing using piezoelectric actuators

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4548546A (en) * 1981-11-05 1985-10-22 S.N.E.C.M.A. Adjustment system of centering a turbomachine wheel and mounted turbomachine by way of permitting the application of said system
DE3831928A1 (en) * 1988-09-20 1990-03-22 Friedrich Prof Dr Pfeiffer Device for stabilising axles or shafts
US5221146A (en) * 1991-04-16 1993-06-22 Nissan Motor Co., Ltd. Structure of bearing of geared shaft
EP1134443A2 (en) * 2000-03-15 2001-09-19 Umbra Cuscinetti S.p.A. A device for measuring and adjusting preloading on bearings
DE10304607A1 (en) * 2003-02-05 2004-08-19 Fag Kugelfischer Ag Detection of pre- or over-travel of bearings in a roller bearing by calculation of first and second signal periods of a strain gauge and comparison of a difference value with a threshold in order to detect pre- or over-travel
DE102004024851A1 (en) * 2004-05-19 2005-12-22 Fag Kugelfischer Ag & Co. Ohg Machine part storage arrangement for use in paper machine, has piezo components arranged in construction unit that one of section of unit is clamped by force less than or equal to zero between components, where components are actuators
WO2006015048A1 (en) * 2004-07-27 2006-02-09 The Timken Company Adaptive bearing system containing a piezoelectric actuator for controlling setting

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100247015A1 (en) * 2009-03-25 2010-09-30 Rolls-Royce Plc Bearing arrangement
US8292509B2 (en) * 2009-03-25 2012-10-23 Rolls-Royce Plc Bearing arrangement
US8840114B2 (en) 2011-03-29 2014-09-23 Rolls-Royce Plc Assembly comprising a rotatable component
EP3670942A1 (en) * 2018-12-17 2020-06-24 Rolls-Royce plc Bearing assembly including active vibration control

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DE102005007776A1 (en) 2006-08-31
EP1848877A1 (en) 2007-10-31
US20090226306A1 (en) 2009-09-10

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