EP2379847A1 - Method for mounting an integral inner ring of a turbocompressor stator - Google Patents

Method for mounting an integral inner ring of a turbocompressor stator

Info

Publication number
EP2379847A1
EP2379847A1 EP10702397A EP10702397A EP2379847A1 EP 2379847 A1 EP2379847 A1 EP 2379847A1 EP 10702397 A EP10702397 A EP 10702397A EP 10702397 A EP10702397 A EP 10702397A EP 2379847 A1 EP2379847 A1 EP 2379847A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
radius
ring
outer radius
vane
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.)
Granted
Application number
EP10702397A
Other languages
German (de)
French (fr)
Other versions
EP2379847B1 (en
Inventor
Frank Stiehler
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 EP2379847A1 publication Critical patent/EP2379847A1/en
Application granted granted Critical
Publication of EP2379847B1 publication Critical patent/EP2379847B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the invention relates to a method for mounting an integral inner ring of a turbocompressor stator to a vane ring.
  • the vanes are mounted on a rotatable ring.
  • the inner ring is provided with openings (bearing countersinks) into which bearing bushes for the inner pins of the guide vanes can be inserted. Only when the guide vanes are inserted in the compressor housing, the installation (assembly) of the inner ring takes place.
  • assembly has hitherto been possible only in segments.
  • the inner ring is divided circumferentially into individual segments with a center angle ⁇ 180 °, and the segments with the openings are individually “threaded" into the inner lugs of the vanes, as far as the gaps between the segments allow. In practice, therefore, the segments typically have a midpoint angle not greater than 30 °.
  • Such a segmented inner ring is shown, for example, in EP 1 508 672 A1.
  • a method for mounting a segmented inner ring without axial division is known from DE 10 2006 024 085 Al. The method described therein makes use of the fact that the openings in the segments of the inner ring are significantly larger in diameter than the inner cones of the guide vanes, so that the latter can be temporarily positioned eccentrically and obliquely in the openings.
  • segmented inner rings have fundamental disadvantages compared to one-piece, closed (integral) inner rings.
  • the segmentation leads to greater wear and a significantly shorter service life.
  • the segmentation leads to an undesirable cluster swing.
  • the inventive method for mounting an integral inner ring of a turbocompressor stator to a vane ring comprises the following steps:
  • the invention is based on the recognition that an integral inner ring can be designed so deformable that the inner ring can be biased with a suitable geometric design of its openings and the inner pins of the vanes so that the Verforrmingshunt of the inner ring during its relaxation for threading the inner ring in the Guide vane ring can be used.
  • the die ensures that no overstretching of the inner ring occurs because it limits the bend to a defined radius.
  • Figure 1 is a plan view of a die and a part of an inner ring before its pre-bending
  • Figure 2 is a schematic partial view of a vane ring with one side attached inner ring
  • Figure 3 is a larger schematic partial view of the vane ring with partially threaded inner ring.
  • FIG. 4 shows the geometric model on which the method according to the invention is based.
  • an integral, that is undivided, one-piece inner ring 10 is provided with an outer radius R which is constant over the circumference.
  • a one-piece inner ring is to be understood here also a one-piece part ring with a center angle> 180 °.
  • the outer radius R of the inner ring 10 corresponds to an inner radius S of the Leitschaufelkranzes 12, to which the inner ring 10 is to be mounted.
  • the vane ring 12 is the entirety or, as described in the following assembly process, a part of the inner ring 10 to be held vanes 14, which are already pre-assembled in the tubular housing or in a housing part of the compressor.
  • the vane ring 12 is in the latter case a partial ring (preferably with a midpoint angle ⁇ 180 °) of circumferentially juxtaposed vanes 14.
  • the vanes 14 have inner pins 16 which are to be stored in associated openings 18 (bearing depressions) of the inner ring 10.
  • the inner ring 10 is pre-bent by the inner ring 10 constant to an outer radius r is biased, which is smaller than the outer radius R of the inner ring 10 in the untensioned state.
  • the bias is applied over the entire circumference of the inner ring 10 or over a certain part, preferably over a part whose arc length of the arc length of the preassembled vane ring 12 corresponds (based on the radii R and S).
  • the inner ring 10 is brought into contact with the die 20 at an inner contact point A for this purpose.
  • the inner ring 10 is fixed with a clamping 22 with adjustable drawbar.
  • two further adjustable clamping units 24 are provided with which at two points of pull, which are preferably diametrically opposed to each other (center angle distance ⁇ 180 °), the inner ring 10 is bent onto the die 20.
  • the clamping units 24 may - according to the example shown in Figure 1 - train bearing forming pins 26 and / or claws on which a tensile force is applied.
  • the clamping direction S is adjusted during pretensioning so that the inner ring 10 does not buckle, but applies uniformly to the die 20.
  • the clamping units 22 and 24 are then fixed, so that the inner ring 10 remains in its prestressed state.
  • Figures 2 and 3 show schematically how subsequently the inner ring 10 is threaded by relaxing on its original outer radius R in the vane part ring.
  • the biased inner ring 10 is attached to one end 28 of the vane ring 12 and unrolled in the vane ring 12 by the adjustable clamping units 22 and 24 are relieved (release of the fixation).
  • the openings 18 of the inner ring 10 are moved without tilting or jamming over the inner pins 16 of the guide vanes 14. This is possible in the particular relaxation restoring deformation of the inner ring 10 to its original outer radius R alone due to the play of the openings 18.
  • FIG. 3 shows how, at the tangential contact point P, the outer radius of the inner ring without transition from the smaller radius r (pretensioned) changes directly to the original radius R (relaxed).
  • the disassembly of the inner ring 10 from the vane ring 12 is also possible by tilting or jamming by reversing the described assembly process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a method for mounting an integral inner ring (10) of a turbocompressor stator to a guide vane ring (12). The method comprises the following steps: making the guide vane ring (12) having an inner radius S available; making the inner ring (10) having an outer radius R available, said outer radius equaling the inner radius S; pretensioning the inner ring (10) to an outer radius r which is smaller than the outer radius R of the untensioned inner ring (10); and relaxing the inner ring (10) to the outer radius R.

Description

Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators Method for mounting an integral inner ring of a turbocompressor stator
Die Erfindung betrifft ein Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators an einen Leitschaufelkranz.The invention relates to a method for mounting an integral inner ring of a turbocompressor stator to a vane ring.
Bei Turboverdichtern für Gasturbinen, die einen beschaufelten Stator aufweisen, werden die Leitschaufeln auf einem drehfesten rnnenring gelagert. Der Innenring ist mit Öffnungen (Lagersenkungen) versehen, in die Lagerbuchsen für die Innenzapfen der Leitschaufeln einsetzbar sind. Erst wenn die Leitschaufeln im Verdichtergehäuse eingesetzt sind, erfolgt die Installation (Montage) des Innenrings. Bei Innenringen ohne axiale Teilung ist die Montage bislang nur segmentweise möglich. Der rnnenring ist in Umfangsrichtung in einzelne Segmente mit einem Mittelpunktswinkel < 180° unterteilt, und die Segmente mit den Öffnungen werden einzeln in die Innenzapfen der Leitschaufeln "eingefädelt", soweit die Spalte zwischen den Segmenten dies zulassen. In der Praxis weisen die Segmente daher in der Regel einen Mittelpunkts winkel auf, der nicht größer als 30° ist.In turbocompressors for gas turbines, which have a bladed stator, the vanes are mounted on a rotatable ring. The inner ring is provided with openings (bearing countersinks) into which bearing bushes for the inner pins of the guide vanes can be inserted. Only when the guide vanes are inserted in the compressor housing, the installation (assembly) of the inner ring takes place. In the case of inner rings without axial division, assembly has hitherto been possible only in segments. The inner ring is divided circumferentially into individual segments with a center angle <180 °, and the segments with the openings are individually "threaded" into the inner lugs of the vanes, as far as the gaps between the segments allow. In practice, therefore, the segments typically have a midpoint angle not greater than 30 °.
Ein solcher segmentierter Innenring ist beispielsweise in der EP 1 508 672 Al gezeigt. Ein Verfahren zur Montage eines segmentierten Innenrings ohne axiale Teilung ist aus der DE 10 2006 024 085 Al bekannt. Bei dem darin beschriebenen Verfahren wird ausgenutzt, dass die Öffnungen in den Segmenten des rnnenrings im Durchmesser deutlich größer sind als die Innenzapfen der Leitschaufeln, so dass letztere zeitweilig exzentrisch und schräg in den Öffnungen positioniert sein können.Such a segmented inner ring is shown, for example, in EP 1 508 672 A1. A method for mounting a segmented inner ring without axial division is known from DE 10 2006 024 085 Al. The method described therein makes use of the fact that the openings in the segments of the inner ring are significantly larger in diameter than the inner cones of the guide vanes, so that the latter can be temporarily positioned eccentrically and obliquely in the openings.
Segmentierte Innenringe haben jedoch im Vergleich zu einteiligen, geschlossenen (integralen) Innenringen grundsätzliche Nachteile. So führt die Segmentierung zu einem größeren Verschleiß und einer erheblich verkürzten Lebensdauer. Außerdem führt die Segmentierung zu einem unerwünschten Clusterschwingen.However, segmented inner rings have fundamental disadvantages compared to one-piece, closed (integral) inner rings. The segmentation leads to greater wear and a significantly shorter service life. In addition, the segmentation leads to an undesirable cluster swing.
Bislang ist aber kein Verfahren bekannt, mit dem ein integraler Innenring ohne axiale Teilung in zufriedenstellender Weise montiert werden kann. Aufgabe der Erfindung ist es, diesen Mangel zu beheben und ein Verfahren anzugeben, das eine einfache Montage und ggf. Demontage eines Leitschaufeln tragenden Innenrings zu ermöglichen. Gelöst wird diese Aufgabe durch ein Verfahren mit den Merkmalen des Anspruchs 1. Vorteilhafte und zweckmäßige Ausgestaltungen des erfindungsgemäßen Verfahrens ergeben sich aus den Unteransprüchen.So far, however, no method is known with which an integral inner ring without axial division can be mounted in a satisfactory manner. The object of the invention is to remedy this deficiency and to provide a method that allow easy assembly and possibly disassembly of a guide vanes bearing inner ring. This object is achieved by a method having the features of claim 1. Advantageous and expedient embodiments of the method according to the invention will become apparent from the dependent claims.
Das erfindungsgemäße Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators an einen Leitschaufelkranz weist folgende Schritte auf:The inventive method for mounting an integral inner ring of a turbocompressor stator to a vane ring comprises the following steps:
- Bereitstellen des Leitschaufelkranzes mit einem inneren Radius S;- Providing the vane ring with an inner radius S;
— Bereitstellen des Innenrings mit einem äußeren Radius R, der dem inneren Radius S entspricht;- Providing the inner ring with an outer radius R corresponding to the inner radius S;
— Vorspannen des Innenrings auf einen äußeren Radius r, der kleiner ist als der äußere Radius R des ungespannten Innenrings; und- biasing the inner ring to an outer radius r, which is smaller than the outer radius R of the unstressed inner ring; and
- Entspannen des Innenrings auf den äußeren Radius R.- Relaxing of the inner ring on the outer radius R.
Die Erfindung beruht auf der Erkenntnis, dass ein integraler Innenring so verformbar gestaltet werden kann, dass der Innenring bei geeigneter geometrischer Auslegung seiner Öffnungen und der Innenzapfen der Leitschaufeln so vorgespannt werden kann, dass die Verforrmingsbewegung des Innenrings bei dessen Entspannung zum Einfädeln des Innenrings in den Leitschaufelkranz genutzt werden kann.The invention is based on the recognition that an integral inner ring can be designed so deformable that the inner ring can be biased with a suitable geometric design of its openings and the inner pins of the vanes so that the Verforrmingsbewegung of the inner ring during its relaxation for threading the inner ring in the Guide vane ring can be used.
Besonders vorteilhaft ist beim Vorspannen des Innenrings die Verwendung einer Matrize mit einem Radius, deren Außenradius kleiner ist als der äußere Radius R des ungespannten Innenrings abzüglich dessen radialer Dicke. Die Matrize stellt sicher, dass keine Überdehnung des Innenrings auftritt, da sie die Biegung auf einen definierten Radius begrenzt.Particularly advantageous when biasing the inner ring, the use of a die with a radius whose outer radius is smaller than the outer radius R of the unstressed inner ring minus its radial thickness. The die ensures that no overstretching of the inner ring occurs because it limits the bend to a defined radius.
Weitere Merkmale und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung und aus den beigefügten Zeichnungen, auf die Bezug genommen wird. In den Zeichnungen zeigen:Further features and advantages of the invention will become apparent from the following description and from the accompanying drawings, to which reference is made. In the drawings show:
Figur 1 eine Draufsicht auf eine Matrize und eines Teils eines Innenrings vor dessen Vorbiegung; Figur 2 eine schematische Teilansicht eines Leitschaufelkranzes mit einseitig angesetztem Innenring;Figure 1 is a plan view of a die and a part of an inner ring before its pre-bending; Figure 2 is a schematic partial view of a vane ring with one side attached inner ring;
Figur 3 eine größere schematische Teilansicht des Leitschaufelkranzes mit teilweise eingefädeltem Innenring; undFigure 3 is a larger schematic partial view of the vane ring with partially threaded inner ring; and
Figur 4 das geometrische Modell, das dem erfindungsgemäßen Verfahren zugrunde liegt.FIG. 4 shows the geometric model on which the method according to the invention is based.
Das erfindungsgemäße Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators an einen Leitschaufelkranz wird im Folgenden anhand der Figuren 1 bis 4 näher erläutert.The inventive method for mounting an integral inner ring of a turbocompressor to a vane ring is explained in more detail below with reference to Figures 1 to 4.
Zunächst wird ein integraler, also ungeteilter, einstückiger Innenring 10 mit einem über den Umfang konstanten äußeren Radius R bereitgestellt. Unter einem einstückigen Innenring soll hier auch ein einstückiger Teilring mit einem Mittelpunktswinkel > 180° verstanden werden. Der äußere Radius R des Innenrings 10 entspricht einem inneren Radius S des Leitschaufelkranzes 12, an den der Innenring 10 montiert werden soll.First, an integral, that is undivided, one-piece inner ring 10 is provided with an outer radius R which is constant over the circumference. Under a one-piece inner ring is to be understood here also a one-piece part ring with a center angle> 180 °. The outer radius R of the inner ring 10 corresponds to an inner radius S of the Leitschaufelkranzes 12, to which the inner ring 10 is to be mounted.
Der Leitschaufelkranz 12 ist die Gesamtheit oder, wie im folgenden Montageverfahren beschrieben, ein Teil der vom Innenring 10 zu haltenden Leitschaufeln 14, die im rohrförmigen Gehäuse bzw. in einem Gehäuseteil des Verdichters bereits vormontiert sind. Der Leitschaufelkranz 12 ist in letzterem Fall ein Teilring (vorzugsweise mit einem Mittelpunktswinkel ~ 180°) von in Umfangsrichtung nebeneinander angeordneten Leitschaufeln 14. Die Leitschaufeln 14 weisen Innenzapfen 16 auf, die in zugeordneten Öffnungen 18 (Lagersenkungen) des Innenrings 10 gelagert werden sollen.The vane ring 12 is the entirety or, as described in the following assembly process, a part of the inner ring 10 to be held vanes 14, which are already pre-assembled in the tubular housing or in a housing part of the compressor. The vane ring 12 is in the latter case a partial ring (preferably with a midpoint angle ~ 180 °) of circumferentially juxtaposed vanes 14. The vanes 14 have inner pins 16 which are to be stored in associated openings 18 (bearing depressions) of the inner ring 10.
Unter dem äußeren Radius R des Innenrings 10 und dem inneren Radius S des Leitschaufelkranzes 12 sind von der axialen Mittelachse des Verdichtergehäuses gemessene Radien zu verstehen, die im montierten Zustand des Innenrings 10 zusammenfallen. Konkret sind dies der halbe Außendurchmesser des Innenrings 10 und ein Radius im Bereich der Innenzapfen 16 der Leitschaufeln 14. (Der Einfachheit halber sind in den Zeichnungen - mit Ausnahme der Figur 4 - nicht die Radien selbst, sondern die zugehörigen Bogenlinien mit R, S (und später mit r) bezeichnet). Mittels einer Matrize 20 in Form einer Scheibe oder eines Scheibenrings oder eines entsprechenden Segments mit einem Außenradius, der kleiner ist als der äußere Radius R des Innenrings 10 abzüglich dessen radialer Dicke, wird der Innenring 10 vorgebogen, indem der Innenring 10 konstant auf einen äußeren Radius r vorgespannt wird, der kleiner ist als der äußere Radius R des Innenrings 10 im ungespannten Zustand. Die Vorspannung erfolgt über den gesamten Umfang des Innenrings 10 oder über einen bestimmten Teil, vorzugsweise über einen Teil, dessen Bogenlänge der Bogenlänge des vormontierten Leitschaufelkranzes 12 entspricht (bezogen auf die Radien R bzw. S).Under the outer radius R of the inner ring 10 and the inner radius S of the vane ring 12 are to be understood by the axial center axis of the compressor housing measured radii, which coincide in the assembled state of the inner ring 10. Concretely, these are half the outer diameter of the inner ring 10 and a radius in the region of the inner pins 16 of the guide vanes 14. (For simplicity, in the drawings - with the exception of Figure 4 - not the radii themselves, but the associated arc lines with R, S ( and later designated r)). By means of a die 20 in the form of a disc or a disc ring or a corresponding segment with an outer radius which is smaller than the outer radius R of the inner ring 10 minus its radial thickness, the inner ring 10 is pre-bent by the inner ring 10 constant to an outer radius r is biased, which is smaller than the outer radius R of the inner ring 10 in the untensioned state. The bias is applied over the entire circumference of the inner ring 10 or over a certain part, preferably over a part whose arc length of the arc length of the preassembled vane ring 12 corresponds (based on the radii R and S).
Wie in Figur 1 gezeigt wird der Innenring 10 hierzu an einem inneren Anlagepunkt A in Anlage mit der Matrize 20 gebracht. Dort wird der Innenring 10 mit einer Verklammerung 22 mit verstellbarem Zuggestänge fixiert. Neben dieser Verklammerung 22 sind zwei weitere verstellbare Spanneinheiten 24 vorgesehen, mit denen an zwei Zugpunkten, die einander vorzugsweise diametral gegenüberliegen (Mittelpunktswinkelabstand ~ 180°), der Innenring 10 auf die Matrize 20 gebogen wird. Die Spanneinheiten 24 können - gemäß dem in Figur 1 dargestellten Beispiel - Zuglager bildende Stifte 26 und/oder Krallen aufweisen, auf die eine Zugkraft aufgebracht wird. Die Spannrichtung S wird beim Vorspannen so eingestellt, dass sich der Innenring 10 nicht ausbeult, sondern gleichmäßig an die Matrize 20 anlegt. Die Spanneinheiten 22 und 24 werden anschließend fixiert, sodass der Innenring 10 in seinem vorgespannten Zustand verbleibt.As shown in FIG. 1, the inner ring 10 is brought into contact with the die 20 at an inner contact point A for this purpose. There, the inner ring 10 is fixed with a clamping 22 with adjustable drawbar. In addition to this clamping 22, two further adjustable clamping units 24 are provided with which at two points of pull, which are preferably diametrically opposed to each other (center angle distance ~ 180 °), the inner ring 10 is bent onto the die 20. The clamping units 24 may - according to the example shown in Figure 1 - train bearing forming pins 26 and / or claws on which a tensile force is applied. The clamping direction S is adjusted during pretensioning so that the inner ring 10 does not buckle, but applies uniformly to the die 20. The clamping units 22 and 24 are then fixed, so that the inner ring 10 remains in its prestressed state.
Die Figuren 2 und 3 zeigen schematisch, wie anschließend der Innenring 10 durch Entspannen auf seinen ursprünglichen Außenradius R in den Leitschaufel -Teilring eingefädelt wird. Der vorgespannte Innenring 10 wird an einem Ende 28 des Leitschaufelkranzes 12 angesetzt und im Leitschaufelkranz 12 abgerollt, indem die verstellbaren Spanneinheiten 22 und 24 entlastet werden (Lösen der Fixierung). Dabei werden die Öffnungen 18 des Innenrings 10 ohne Verkanten oder Verklemmen über die Innenzapfen 16 der Leitschaufeln 14 bewegt. Dies ist bei der besonderen Entspannungsrückverformung des Innenrings 10 auf seinen ursprünglichen Außenradius R alleine aufgrund des Spiels der Öffnungen 18 möglich.Figures 2 and 3 show schematically how subsequently the inner ring 10 is threaded by relaxing on its original outer radius R in the vane part ring. The biased inner ring 10 is attached to one end 28 of the vane ring 12 and unrolled in the vane ring 12 by the adjustable clamping units 22 and 24 are relieved (release of the fixation). In this case, the openings 18 of the inner ring 10 are moved without tilting or jamming over the inner pins 16 of the guide vanes 14. This is possible in the particular relaxation restoring deformation of the inner ring 10 to its original outer radius R alone due to the play of the openings 18.
In Figur 3 ist gezeigt, wie am tangentialen Berührungspunkt P der Außenradius des Innenrings ohne Übergang vom kleineren Radius r (vorgespannt) unmittelbar auf den ursprünglichen Radius R (entspannt) wechselt. Während also das Abrollen des Innenrings 10 im Leitschaufelkranz 12 kontinuierlich erfolgt, vollführt der Radius des Innenrings 10 am mitlaufenden tangentialen Berührungspunkt P einen Krümmungssprung von r auf R. Die Betriebsendlage des Innenrings 10, in der die Innenzapfen 16 und die Öffnungen 18 fluchten, wird somit alleine unter Ausnutzung des Lagersenkungsspiels und der Abweichung zwischen der gespannten und der entspannten Innenringgeometrie erreicht.FIG. 3 shows how, at the tangential contact point P, the outer radius of the inner ring without transition from the smaller radius r (pretensioned) changes directly to the original radius R (relaxed). Thus, while the rolling of the inner ring 10 in the vane ring 12 takes place continuously, the radius of the inner ring 10 performs a curvature jump from r to R at the tangential tangential point of contact P. The operating end position of the inner ring 10, in which the inner pin 16 and the openings 18 are aligned, is thus achieved solely by taking advantage of the bearing clearance and the deviation between the tensioned and the relaxed inner ring geometry.
Die kinematische Beschreibung des Abrollvorgangs geht aus der Modellbetrachtung gemäß Figur 4 hervor. Daraus ergibt sich, dass das Abrollen des Innenrings 10 im Leitschaufelkranz eine Hypozykloidenbewegung darstellt, entsprechend dem Abrollen eines Planetenrads in einem Zahnkranz. Die Bewegungsbahn eins festen Punktes des Innenrings 10 entspricht demnach einer Zykloide, die auf einem Innenkreis mit dem Radius R-r (bezogen auf die Mittelachse des Innenrings 10 bzw. des Leitschaufelkranzes 12) erzeugt wurde.The kinematic description of the rolling process is evident from the model view according to FIG. It follows that the rolling of the inner ring 10 in the vane ring is a Hypozykloidenbewegung, according to the rolling of a planetary gear in a ring gear. The trajectory of a fixed point of the inner ring 10 thus corresponds to a cycloid which has been generated on an inner circle with the radius R-r (with respect to the central axis of the inner ring 10 and the Leitschaufelkranzes 12).
Die Demontage des Innenrings 10 vom Leitschaufelkranz 12 ist durch Umkehrung des beschriebenen Montagevorgangs ebenfalls ohne Verkanten oder Verklemmen möglich. The disassembly of the inner ring 10 from the vane ring 12 is also possible by tilting or jamming by reversing the described assembly process.

Claims

P atentansprüche Patent claims
1. Verfahren zur Montage eines integralen Innenrings (10) eines Turboverdichterstators an einen Leitschaufelkranz (12), mit folgenden Schritten:A method of assembling an integral inner ring (10) of a turbocompressor stator to a vane ring (12), comprising the steps of:
- Bereitstellen des Leitschaufelkranzes (12) mit einem inneren Radius S;- Providing the vane ring (12) with an inner radius S;
- Bereitstellen des Innenrings (10) mit einem äußeren Radius R, der dem inneren Radius S entspricht;- Providing the inner ring (10) with an outer radius R corresponding to the inner radius S;
- Vorspannen des Innenrings (10) auf einen über den Umfang des Innenrings (10) konstanten äußeren Radius r, der kleiner ist als der äußere Radius R des ungespannten Innenrings (10); und- biasing the inner ring (10) to an over the circumference of the inner ring (10) constant outer radius r, which is smaller than the outer radius R of the unstressed inner ring (10); and
Abrollen des Innenrings (10) im Leitschaufelkranz (12) durch Entspannen des Innenrings (10) auf den äußeren Radius R.Rolling the inner ring (10) in the vane ring (12) by relaxing the inner ring (10) on the outer radius R.
2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass beim Entspannen des Innenrings (10) an einem tangentialen Berührungspunkt P der Außenradius des Innenrings (10) einen Krümmungssprung vom Radius r unmittelbar auf den Radius R vollführt.2. The method according to claim 1, characterized in that when relaxing the inner ring (10) at a tangential point of contact P, the outer radius of the inner ring (10) performs a curvature of the radius r directly on the radius R.
3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass zum Vorspannen des Innenrings (10) eine Matrize (20) mit einem Radius verwendet wird, deren Außenradius kleiner ist als der äußere Radius R des ungespannten Innenrings (10) abzüglich dessen radialer Dicke.3. The method according to claim 1 or 2, characterized in that for biasing the inner ring (10) has a die (20) is used with a radius whose outer radius is smaller than the outer radius R of the unstressed inner ring (10) minus its radial thickness ,
4. Verfahren nach Anspruch 3, dadurch gekennzeichnet, dass der Innenring (10) an einem inneren Anlagepunkt A in Anlage mit der Matrize (20) gebracht und dort mit einer Verklammerung (22) fixiert wird.4. The method according to claim 3, characterized in that the inner ring (10) brought at an inner bearing point A in contact with the die (20) and fixed there with a clamping (22).
5. Verfahren nach Anspruch 3 oder 4, dadurch gekennzeichnet, dass die Vorspannung des Innenrings (10) mit Hilfe wenigstens zweier Spanneinheiten (24) aufgebracht wird, die an einander vorzugsweise diametral gegenüberliegenden Zugpunkten am Innenring (10) angreifen.5. The method according to claim 3 or 4, characterized in that the bias of the inner ring (10) by means of at least two clamping units (24) is applied, the attack on preferably diametrically opposite points of pull on the inner ring (10).
6. Verfahren nach Anspruch 5, dadurch gekennzeichnet, dass die Spannrichtung der auf die Zugpunkte aufgebrachten Zugkräfte so eingestellt wird, dass sich der Innenring (10) nicht ausbeult und gleichmäßig an die Matrize (20) anlegt.6. The method according to claim 5, characterized in that the clamping direction of the tensile forces applied to the traction points is adjusted so that the inner ring (10) does not bulge and evenly applied to the die (20).
7. Verfahren nach Anspruch 5 oder 6, dadurch gekennzeichnet, dass zum Entspannen des Innenrings (10) die Spanneinheiten (24) und ggf. ein an die Verklammerung (22) gekoppeltes Zuggestänge entlastet werden.7. The method according to claim 5 or 6, characterized in that for relaxing the inner ring (10), the clamping units (24) and possibly a to the clamping (22) coupled drawbar are relieved.
8. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der äußere Radius R der halbe Außendurchmesser des Innenrings (10) und der innere Radius S ein von der axialen Mittelachse eines Gehäuses gemessener Radius im Bereich der Innenzapfen (16) der Leitschaufeln (14) ist.8. The method according to any one of the preceding claims, characterized in that the outer radius R of half the outer diameter of the inner ring (10) and the inner radius S a measured from the axial center axis of a housing radius in the region of the inner pins (16) of the guide vanes (14 ).
9. Verfahren nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Leitschaufelkranz (12) ein Teilring ist, der einen Teil von in einem Gehäuse oder Gehäuseteil vormontierten Leitschaufeln (14) mit Innenzapfen (16) umfasst.9. The method according to any one of the preceding claims, characterized in that the guide vane ring (12) is a partial ring which comprises a part of pre-assembled in a housing or housing part vanes (14) with inner pin (16).
10. Verfahren nach Anspruch 9, dadurch gekennzeichnet, dass der Leitschaufelkranz (12) einen Mittelpunktswinkel von etwa 180° hat.10. The method according to claim 9, characterized in that the vane ring (12) has a center angle of about 180 °.
11. Verfahren nach Anspruch 9 oder 10, dadurch gekennzeichnet, dass der Innenring (10) über eine Bogenlänge bezogen auf dessen Radius R vorgespannt wird, die der Bogenlänge des Leitschaufelkranzes (12) bezogen auf dessen Radius S entspricht.11. The method according to claim 9 or 10, characterized in that the inner ring (10) is biased over an arc length relative to the radius R, which corresponds to the arc length of the guide vane ring (12) based on the radius S.
12. Verfahren nach einem der Ansprüche 9 bis 11, dadurch gekennzeichnet, dass der Innenring (10) beim Entspannen an einem Ende (28) des Leitschaufelkranzes (12) angesetzt und im Leitschaufelkranz (12) so abgerollt wird, dass die Bewegungsbahn eins festen Punktes des Innenrings (10) einer Zykloide entspricht.12. The method according to any one of claims 9 to 11, characterized in that the inner ring (10) when relaxing at one end (28) of the vane ring (12) and set in the vane ring (12) is unrolled so that the trajectory of a fixed point of the inner ring (10) corresponds to a cycloid.
13. Verfahren nach Anspruch 12, dadurch gekennzeichnet, dass, die Zykloide auf einem Innenkreis mit dem Radius R-r erzeugt wird. 13. The method according to claim 12, characterized in that the cycloid is generated on an inner circle with the radius R-r.
EP10702397.0A 2009-01-16 2010-01-14 Method for mounting an integral inner shroud of a turbocompressor stator Active EP2379847B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009004934.7A DE102009004934B4 (en) 2009-01-16 2009-01-16 Method for assembling an integral inner ring of a turbo compressor stator
PCT/DE2010/000023 WO2010081468A1 (en) 2009-01-16 2010-01-14 Method for mounting an integral inner ring of a turbocompressor stator

Publications (2)

Publication Number Publication Date
EP2379847A1 true EP2379847A1 (en) 2011-10-26
EP2379847B1 EP2379847B1 (en) 2013-06-12

Family

ID=41796410

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10702397.0A Active EP2379847B1 (en) 2009-01-16 2010-01-14 Method for mounting an integral inner shroud of a turbocompressor stator

Country Status (5)

Country Link
US (1) US8943689B2 (en)
EP (1) EP2379847B1 (en)
CA (1) CA2746134C (en)
DE (1) DE102009004934B4 (en)
WO (1) WO2010081468A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520769A1 (en) 2011-05-02 2012-11-07 MTU Aero Engines GmbH Inner ring for forming a guide vane assembly, guide vane assembly and fluid flow engine
EP2725202A1 (en) 2012-10-25 2014-04-30 MTU Aero Engines GmbH Inner ring seal support arrangement for an adjustable stator blade assembly of a turbomachine
EP2884054A1 (en) 2013-12-10 2015-06-17 MTU Aero Engines GmbH Variable guide vane with cone frustum in a bearing arrangement
DE102014205986B4 (en) 2014-03-31 2021-03-18 MTU Aero Engines AG Guide vane ring and turbomachine
AU2020258963A1 (en) * 2019-04-16 2021-07-29 Atlas Copco (Wuxi) Compressor Co., Ltd. Guide device for directing gas through
FR3122668B1 (en) * 2021-05-04 2023-05-26 Safran Aircraft Engines Method for mounting an abradable element comprising a honeycomb structure in an annular groove of a turbomachine member

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE669777A (en)
DE892046C (en) * 1953-08-20 Maschinenfabrik Augsburg-Nürnlberg A. G., Augsburg Diffuser for centrifugal machines with axial flow
DE969599C (en) * 1943-05-27 1958-06-19 Holzwarth Gasturbinen G M B H Cooled nozzle body for centrifugal machines, especially exhaust gas turbines
DE807572C (en) * 1947-11-19 1951-07-02 Cem Comp Electro Mec Guide vane arrangement for steam and gas turbines
FR1145011A (en) * 1955-04-05 1957-10-21 Maschf Augsburg Nuernberg Ag Guide vane device for machines with axial flow rotor, in particular steam and gas turbines
NL243359A (en) * 1958-11-07
DE1096921B (en) * 1959-08-18 1961-01-12 Licentia Gmbh Multi-stage axial steam or gas turbine in a pot housing
US3156970A (en) * 1961-07-14 1964-11-17 Gen Motors Corp Torque converter elements and methods of making the same
US3132842A (en) 1962-04-13 1964-05-12 Gen Electric Turbine bucket supporting structure
DE1172900B (en) * 1962-04-17 1964-06-25 Gasturbinenbau Veb Method for assembling a multistage axial flow machine
FR1373359A (en) * 1962-10-19 1964-09-25 Ass Elect Ind Intermediate stage diaphragms for turbines and axial compressors
US3300180A (en) * 1964-11-17 1967-01-24 Worthington Corp Segmented diaphragm assembly
DE2152365C3 (en) 1971-02-03 1973-12-06 Carrier Corp., Syracuse, N.Y. (V.St.A.) Device for supporting the inner ends of rotatably mounted guide vanes of an axial flow machine
US3969805A (en) 1974-12-23 1976-07-20 The Trane Company Method of constructing an axial flow fan
US5086560A (en) * 1990-01-24 1992-02-11 Glazier Stephen C Method of assembling prestressed frictionless bearings
EP1508672A1 (en) 2003-08-21 2005-02-23 Siemens Aktiengesellschaft Segmented fastening ring for a turbine
FR2870309B1 (en) * 2004-05-17 2006-07-07 Snecma Moteurs Sa METHOD FOR ASSEMBLING MONOBLOCS AUBAGE DISCS AND DEVICE FOR DAMPING THE VIBRATION OF THE BLADES OF SAID DISCS
DE102006024085B4 (en) 2006-05-23 2020-04-16 MTU Aero Engines AG Turbo compressor in axial design

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010081468A1 *

Also Published As

Publication number Publication date
WO2010081468A1 (en) 2010-07-22
CA2746134A1 (en) 2010-07-22
DE102009004934A1 (en) 2010-08-19
DE102009004934B4 (en) 2021-08-26
US20110265328A1 (en) 2011-11-03
US8943689B2 (en) 2015-02-03
EP2379847B1 (en) 2013-06-12
CA2746134C (en) 2017-01-03

Similar Documents

Publication Publication Date Title
EP2379847B1 (en) Method for mounting an integral inner shroud of a turbocompressor stator
DE102010006670A1 (en) Hot riveting connection and method for its production
DE102017206246A1 (en) Bearing arrangement for mounting a rotor blade of a wind turbine
EP1387102A1 (en) Press-on shaft-hub connection
DE102016219919A1 (en) Elastic gear of a wave gear
WO2020176918A1 (en) Plain bearing arrangement
DE102015110246A1 (en) Rolling bearing assembly and blade bearing for a wind turbine
DE102008051041B4 (en) Turbocharger with fastening elements for fastening turbine bearing rings of a variable turbine geometry VTG
DE102007019881A1 (en) Rolling bearing and bearing arrangement with roller bearings
EP1847691A2 (en) Roller element for a pivotable machine part
EP2601422A2 (en) Assembly for sealing a rotational connection
DE102010042181A1 (en) Variable turbine and / or compressor geometry
DE102011079274A1 (en) Steering pinion for a steering system and method for its production
EP2499384B1 (en) Ball-joint as well as method for securing a sealing boot on a ball-joint
EP3561292B1 (en) Fixing bolts for the manufacture of a wind turbine rotor blade flange connection, system, method, flange inserter, rotor blade and wind turbine
DE102007053878A1 (en) Rolled roller
DE102012019963A1 (en) Exhaust gas turbocharger for combustion engine, has bearing that is detachably mounted on housing and fixed to guide bush consisting of guide material, and composite bearing bush consisting of material different from guide material
WO2012041466A1 (en) Elastic joint body having a collar bushing arrangement to protect loops
DE102011118655A1 (en) Joint for a cardan shaft
WO2012000699A1 (en) Ball screw
EP2382397B1 (en) Multipart screw element, screw connection, and method for producing a multipart screw element
DE102014225417A1 (en) Articulated planetary shaft
EP3983689B1 (en) Pivot cradle bearing and method for producing a pivot cradle bearing
DE102018003437A1 (en) Wind energy plant and method for assembling a wind energy plant
DE102020204447B4 (en) Process for producing a component for a wind turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20110504

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 616764

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130615

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010003639

Country of ref document: DE

Effective date: 20130808

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130913

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130923

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130912

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: MTU AERO ENGINES AG

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20130612

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130912

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20131114 AND 20131120

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131014

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131012

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

26N No opposition filed

Effective date: 20140313

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010003639

Country of ref document: DE

Effective date: 20140313

BERE Be: lapsed

Owner name: MTU AERO ENGINES G.M.B.H.

Effective date: 20140131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140114

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140114

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 616764

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20100114

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130612

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240119

Year of fee payment: 15

Ref country code: GB

Payment date: 20240124

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240123

Year of fee payment: 15