EP2129875B1 - Turbo engine with active clearance control - Google Patents

Turbo engine with active clearance control Download PDF

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Publication number
EP2129875B1
EP2129875B1 EP08706764A EP08706764A EP2129875B1 EP 2129875 B1 EP2129875 B1 EP 2129875B1 EP 08706764 A EP08706764 A EP 08706764A EP 08706764 A EP08706764 A EP 08706764A EP 2129875 B1 EP2129875 B1 EP 2129875B1
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EP
European Patent Office
Prior art keywords
adjusting device
gap
ring
jacket ring
rotor
Prior art date
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Not-in-force
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EP08706764A
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German (de)
French (fr)
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EP2129875A2 (en
Inventor
Joachim Wulf
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2129875A2 publication Critical patent/EP2129875A2/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.
  • a turbomachine with a stator and a rotor wherein the rotor blades and the stator identifies a housing and vanes.
  • the rotor-side Laufscbaufeln form at least one Laufscbaufellaranz, which is adjacent to a radially outer end of a radially inner housing wall of the housing, surrounded by the same and limited with the same a radial gap
  • the radially inner housing wall of the housing is also referred to as a shroud and serves in particular as a carrier for an inlet lining.
  • the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage.
  • the radially inner housing wall or the shroud segmented in the circumferential direction wherein preferably each segment is assigned a separate actuating device
  • the actuating devices are preferably designed as electromechanical actuators.
  • the arrangement of the electro-mechanical actuators, which act on the segments of the radially inner housing wall and the shroud takes a relatively large amount of space, which increases the overall dimensions of the turbomachine.
  • the document EP 1 655 455 A1 relates to a turbomachine having an adjustable vane support for radial clearance adjustment between a shroud formed by the vane carrier and the tips of blades rotating within the shroud.
  • the shroud ring is segmented and concentrically indicated by a trained as a coupling ring adjusting device.
  • a plurality of circumferentially ramped surfaces are arranged, which cooperate with cylindrical rollers on the coupling ring.
  • the present invention is based on the problem to provide an alternative adjustment of the shroud, which is reliable and has small radial dimensions.
  • a turbomachine according to claim 1. Thereafter, the outer ring is concentrically surrounded by a trained as a coupling ring adjusting device, wherein opposing surfaces of the shroud and the actuator are contoured frustoconical, and wherein between the shroud and the adjusting device in the radial direction and circumferentially with respect to the axial obliquely hired, cylindrical rolling elements are positioned, so that the adjusting device with respect to the shroud with simultaneous adjustment of the gap is rotatable.
  • the inventive concept of an Active Clearance Control on a turbomachine comes with a relatively small space, so that only slightly increases the overall size of a turbomachine. Due to the relatively simple structural design, the turbomachine is also susceptible to wear. Furthermore, only small adjustment forces are required to rotate the ring-like adjusting device relative to the jacket ring for adjusting the gap. Another advantage is that the assemblies involved are predominantly subjected to tension and compression, but are exposed to little or no bending stress.
  • the present invention relates to a turbomachine, in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
  • a turbomachine in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
  • Such turbomachines have at least one compressor, at least one combustion chamber and at least one turbine, wherein both in the region of the or each compressor and in the region of the or each turbine, a stator and a rotor is present.
  • the rotor of a compressor or a turbine comprises a plurality of rotating blades.
  • the stator of a compressor or a turbine comprises a housing and a plurality of stationary vanes.
  • the blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes, the vanes forming vane rings and the rotor blades forming rotor blades.
  • a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the direction of flow.
  • a gap is formed between a radially outer end of a blade ring and a radially inner housing wall of the housing, which is referred to as a shroud, which optimally optimizes the efficiency of the turbomachine must be small.
  • the present invention now relates to such details of a turbomachine, by means of which the gap between the radially outer end of a blade ring and the radially inner housing wall or the outer ring of a housing in the sense of an Active Clearance Control can be automatically influenced or changed.
  • the invention is preferably used in the region of a compressor of a turbomachine.
  • the invention is not limited to use in the area of the compressor, but the invention can also be used in the area of a turbine of a turbomachine.
  • Fig. 1 shows a highly schematic section of a turbomachine according to the invention according to a first aspect of the present invention.
  • Fig. 1 a radially inner housing wall or a shroud 10 of a stator of a compressor of a gas turbine, wherein the shroud 10 encloses a rotor blade, not shown. Between the shroud 10 and a radially outer end of the rotor blade ring, not shown, a likewise not shown gap is formed.
  • the shroud 10 is concentrically surrounded by a trained as a coupling ring adjusting device 11.
  • Fig. 1 are opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11 frustoconically contoured, being formed between the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 and thus formed between the outer ring 10 and actuator 11 as cylindrical rollers rolling elements 14, the relatively are employed obliquely to the axial direction of the shroud 10 in the radial direction and in the circumferential direction.
  • the adjusting device 11 can be rotated relative to the shroud 10. Since the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 are frustoconical contoured and the rolling elements 14 are employed obliquely relative to the axial direction of the shroud 10, this rotation of the actuating device 11 relative to the housing wall 10 in the direction of the arrow 15 continues in the sense of Arrow 16 a translational displacement of the adjusting device 11 relative to the shroud 10, due to which the diameter of the shroud 10 and thus the gap between the shroud 10 and the blade ring, not shown, can be adjusted simultaneously.
  • rolling elements 14 are preferably formed as so-called cage-guided rollers.
  • the gap of the gap reduced in size in relation to an initial dimension, in a second direction of rotation of the adjusting device 11, the gap dimension can be increased relative to the initial dimension.
  • These rolling elements 14 are inclined relative to the axial extension of the housing wall 10 and thus relative to the axial extension of the turbomachine in the circumferential direction and in the radial direction, wherein the opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11, between which the rolling elements 14 are arranged frustoconically contoured are.
  • the rotation of the actuating device 11 relative to the shroud 10 further causes an axial displacement of the adjusting device 11 relative to the shroud 10.
  • the actuating device 11 is screwed onto the shroud 10, so to speak.
  • the executed in a relatively thick wall thickness adjusting device 11 deforms the executed in a relatively thin wall thickness shroud 10 in the sense of elastic deformation, so adjusted by turning the actuator 11 relative to the shroud 10, the diameter of the shroud 10 and thus the gap between the shroud and the blade ring can be adjusted. It is also possible to manufacture the adjusting device 11 from a stiffer material than the shroud 10,
  • the inventive mechanism for providing an active clearance control on a turbomachine is characterized by a compact design with a low Height from. There are only small adjustment forces and no holding forces required. Components are mainly loaded on train and pressure, but are exposed to little or no bending load

Abstract

A turbine engine is disclosed. A blade ring is surrounded by a housing wall, the housing wall being configured as an outer ring, and delimits therewith a gap, the gap being adjustable by deformation of the outer ring. The outer ring is concentrically surrounded by an adjusting element, opposite faces of the outer ring and the adjusting element having the contour of a truncated cone, and rolling bodies being positioned between the outer ring and the adjusting element, the rolling bodies being put at an oblique angle in relation to the axial direction in the radial direction and in the peripheral direction, making it possible for the adjusting element to be rotated in relation to the outer ring while simultaneously adjusting the gap.

Description

Die Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, nach dem Oberbegriff des Anspruchs 1.The invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.

Aus der DE 10 2004 037 955 A1 ist eine Turbomaschine mit einem Stator und einem Rotor bekannt, wobei der Rotor Laufschaufeln und der Stator ein Gehäuse und Leitschaufeln ausweist. Die rotorseitigen Laufscbaufeln bilden mindestens einen Laufscbaufellaranz, der an einem radial außenliegenden Ende an eine radial innenliegende Gehäusewand des Gehäuses angrenzt, von derselben umgeben ist und mit derselben einen radialen Spalt begrenzt Die radial innenliegende Gehäusewand des Gehäuses wird auch als Mantelring bezeichnet und dient insbesondere als Träger für einen Einlaufbelag. Aus der DE 10 2004 037 955 A1 ist weiterhin bekannt, dass der Spalt zwischen dem Mantelring des Gehäuses und dem radial außenliegenden Ende des oder jedes Laufschaufelkranzes zur Bereitstellung eines sogenannten Active Clearance Control über Stelleinrichtungen in seinem Spaltmaß eingestellt bzw. angepasst werden kann, um so automatisch den Spalt zu beeinflussen und über alle Betriebsbedingungen eine optimale Spalthaltung zu gewährleisten. Dabei ist nach der DE 10 2004 037 955 A1 die radial innenliegende Gehäusewand bzw. der Mantelring in Umfangsrichtung segmentiert, wobei vorzugsweise jedem Segment eine separate Stelleinrichtung zugeordnet ist Die Stelleinrichtungen sind vorzugsweise als elektromechanische Aktuatoren ausgeführt. Die Anordnung der elektro-mechanischen Aktuatoren, die auf die Segmente der radial innenliegenden Gehäusewand bzw. des Mantelrings einwirken, nimmt relativ viel Bauraum in Anspruch, wodurch sich die Gesamtabmessungen der Turbomaschine vergrößern.From the DE 10 2004 037 955 A1 For example, a turbomachine with a stator and a rotor is known, wherein the rotor blades and the stator identifies a housing and vanes. The rotor-side Laufscbaufeln form at least one Laufscbaufellaranz, which is adjacent to a radially outer end of a radially inner housing wall of the housing, surrounded by the same and limited with the same a radial gap The radially inner housing wall of the housing is also referred to as a shroud and serves in particular as a carrier for an inlet lining. From the DE 10 2004 037 955 A1 It is also known that the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage. It is after the DE 10 2004 037 955 A1 the radially inner housing wall or the shroud segmented in the circumferential direction, wherein preferably each segment is assigned a separate actuating device The actuating devices are preferably designed as electromechanical actuators. The arrangement of the electro-mechanical actuators, which act on the segments of the radially inner housing wall and the shroud takes a relatively large amount of space, which increases the overall dimensions of the turbomachine.

Das Dokument EP 1 655 455 A1 betrifft eine Strömungsmaschine mit einem verstellbaren Leitschaufelträger zur Radialspalteinstellung zwischen einem vom dem Leitschaufelträger gebildeten Mantelring und den Spitzen von innerhalb des Mantelringes rotierenden Laufschaufeln. Der Mantelring ist segmentiert und von einer als Überwurfring ausgebildeten Stelleinrichtung konzentrisch angeben. An den Mantelringsegmenten sind jeweils mehrere in Umfangsrichtung rampenförmig verlaufende Flächen angeordnet, welche mit zylindrischen Rollen am Überwurfring zusammenwirken. Durch Verdrehen des Überwurfringes werden die Mantelringsegmente radial nach innen oder außen bewegt, wobei eine radiale Vorspannung nach innen über federelastische Elemente auf die Segmente einwirkt. Diese Art der Spalteinstellung ist mechanisch aufwändig und benötigt in Radialrichtung viel Raum.The document EP 1 655 455 A1 relates to a turbomachine having an adjustable vane support for radial clearance adjustment between a shroud formed by the vane carrier and the tips of blades rotating within the shroud. The shroud ring is segmented and concentrically indicated by a trained as a coupling ring adjusting device. At the shroud segments in each case a plurality of circumferentially ramped surfaces are arranged, which cooperate with cylindrical rollers on the coupling ring. By rotating the coupling ring, the shroud segments are moved radially inwardly or outwardly, with a radial Preload acts inward on the segments via elastic elements. This type of gap adjustment is mechanically complex and requires a lot of space in the radial direction.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine alternative Stellmöglichkeit des Mantelrings zu schaffen, die zuverlässig ist und geringe radiale Abmessungen aufweist.On this basis, the present invention is based on the problem to provide an alternative adjustment of the shroud, which is reliable and has small radial dimensions.

Dieses Problem wird durch eine Turbomaschine gemäß Anspruch 1 gelöst. Hiernach ist der Mantelring von einer als Überwurfring ausgebildeten Stelleinrichtung konzentrisch umgeben, wobei sich gegenüberliegende Flächen des Mantelrings und der Stelleinrichtung kegelstumpfförmig konturiert sind, und wobei zwischen dem Mantelring und der Stelleinrichtung in Radialrichtung und in Umfangsrichtung gegenüber der Axialrichtung schräg angestellte, zylindrische Wälzkörper positioniert sind, sodass die Stelleinrichtung gegenüber dem Mantelring unter gleichzeitiger Einstellung des Spalts verdrehbar ist.This problem is solved by a turbomachine according to claim 1. Thereafter, the outer ring is concentrically surrounded by a trained as a coupling ring adjusting device, wherein opposing surfaces of the shroud and the actuator are contoured frustoconical, and wherein between the shroud and the adjusting device in the radial direction and circumferentially with respect to the axial obliquely hired, cylindrical rolling elements are positioned, so that the adjusting device with respect to the shroud with simultaneous adjustment of the gap is rotatable.

Das erfindungsgemäße Konzept eines Active Clearance Control an einer Turbomaschine kommt mit relativ geringem Bauraum aus, so dass sich die Gesamtabmessung einer Turbomaschine nur geringfügig vergrößert. Bedingt durch den relativ einfachen konstruktiven Aufbau ist die Turbomaschine darüber hinaus auch verschleißunanfällig. Ferner werden nur geringe Verstellkräfte benötigt, um die ringartige Stelleinrichtung gegenüber dem Mantelring zur Einstellung des Spalts zu verdrehen. Ein weiterer Vorteil liegt darin, dass die beteiligten Baugruppen vorwiegend auf Zug und Druck beansprucht werden, jedoch keiner oder nur einer geringen Biegebeanspruchung ausgesetzt sind.The inventive concept of an Active Clearance Control on a turbomachine comes with a relatively small space, so that only slightly increases the overall size of a turbomachine. Due to the relatively simple structural design, the turbomachine is also susceptible to wear. Furthermore, only small adjustment forces are required to rotate the ring-like adjusting device relative to the jacket ring for adjusting the gap. Another advantage is that the assemblies involved are predominantly subjected to tension and compression, but are exposed to little or no bending stress.

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:

Fig. 1
ein stark schematisiertes Detail einer erfindungsgemäßen Turbomaschine
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
a highly schematic detail of a turbomachine according to the invention

Die hier vorliegende Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, wie z.B. ein Gasturbinenflugtriebwerk. Derartige Turbomaschinen verfügen über mindestens einen Verdichter, mindestens eine Brennkammer sowie mindestens eine Turbine, wobei sowohl im Bereich des oder jeden Verdichters als auch im Bereich der oder jeder Turbine ein Stator sowie ein Rotor vorhanden ist.The present invention relates to a turbomachine, in particular a gas turbine, such as e.g. a gas turbine aircraft engine. Such turbomachines have at least one compressor, at least one combustion chamber and at least one turbine, wherein both in the region of the or each compressor and in the region of the or each turbine, a stator and a rotor is present.

Der Rotor eines Verdichters bzw. einer Turbine umfasst mehrere rotierende Laufschaufeln. Der Stator eines Verdichters bzw. einer Turbine umfasst ein Gehäuse sowie mehrere feststehende Leitschaufeln. Die dem Rotor zugeordneten Laufschaufeln rotieren gegenüber dem feststehenden Gehäuse und den feststehenden Leitschaufeln des Stators, wobei die Leitschaufeln Leitschaufelkränze und die Laufschaufeln Laufschaufelkränze bilden. Zwischen zwei in Durchströmungsrichtung hintereinander angeordneten Leitschaufelkränzen ist dabei jeweils ein Laufschaufelkranz positioniert.The rotor of a compressor or a turbine comprises a plurality of rotating blades. The stator of a compressor or a turbine comprises a housing and a plurality of stationary vanes. The blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes, the vanes forming vane rings and the rotor blades forming rotor blades. In each case, a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the direction of flow.

Sowohl im Bereich des oder jedes Verdichters sowie im Bereich der oder jeder Turbine einer Turbomaschine ist zwischen einem radial außenliegenden Ende eines Laufschaufelkranzes und einer radial innenliegenden Gehäusewand des Gehäuses, die als Mantelring bezeichnet wird, ein Spalt ausgebildet, der zur Optimierung des Wirkungsgrads der Turbomaschine möglichst klein ausfallen muss.Both in the region of or each compressor and in the region of the or each turbine of a turbomachine, a gap is formed between a radially outer end of a blade ring and a radially inner housing wall of the housing, which is referred to as a shroud, which optimally optimizes the efficiency of the turbomachine must be small.

Die hier vorliegende Erfindung betrifft nun solche Details einer Turbomaschine, mit Hilfe derer der Spalt zwischen dem radial außenliegenden Ende eines Laufschaufelkranzes und der radial innenliegenden Gehäusewand bzw. dem Mantelring eines Gehäuses im Sinne eines Active Clearance Control automatisch beeinflusst bzw. verändert werden kann.The present invention now relates to such details of a turbomachine, by means of which the gap between the radially outer end of a blade ring and the radially inner housing wall or the outer ring of a housing in the sense of an Active Clearance Control can be automatically influenced or changed.

An dieser Stelle sei darauf hingewiesen, dass die Erfindung vorzugsweise im Bereich eines Verdichters einer Turbomaschine zum Einsatz kommt. Die Erfindung ist jedoch nicht auf die Verwendung im Bereich des Verdichters beschränkt, vielmehr kann die Erfindung auch im Bereich einer Turbine einer Turbomaschine zum Einsatz kommen.It should be noted at this point that the invention is preferably used in the region of a compressor of a turbomachine. However, the invention is not limited to use in the area of the compressor, but the invention can also be used in the area of a turbine of a turbomachine.

Fig. 1 zeigt einen stark schematisierten Ausschnitt aus einer erfindungsgemäßen Turbomaschine nach einem ersten Aspekt der hier vorliegenden Erfindung. Fig. 1 shows a highly schematic section of a turbomachine according to the invention according to a first aspect of the present invention.

So zeigt Fig. 1 eine radial innenliegenden Gehäusewand bzw. einen Mantelring 10 eines Stators eines Verdichters einer Gasturbine, wobei der Mantelring 10 einen nicht-dargestellten Laufschaufelkranz umschließt. Zwischen dem Mantelring 10 und einem radial außenliegenden Ende des nicht-dargestellten Laufschaufelkranzes ist ein ebenfalls nichtdargestellter Spalt ausgebildet.So shows Fig. 1 a radially inner housing wall or a shroud 10 of a stator of a compressor of a gas turbine, wherein the shroud 10 encloses a rotor blade, not shown. Between the shroud 10 and a radially outer end of the rotor blade ring, not shown, a likewise not shown gap is formed.

Der Mantelring 10 ist konzentrisch von einer als Überwurfring ausgebildeten Stelleinrichtung 11 umgeben. Gemäß Fig. 1 sind sich gegenüberliegende Flächen 12, 13 von Mantelring 10 und Stelleinrichtung 11 kegelstumpfförmig konturiert, wobei zwischen den sich gegenüberliegenden Flächen 12 und 13 von Mantelring 10 und Stelleinrichtung 11 und damit zwischen Mantelring 10 und Stelleinrichtung 11 als zylindrische Laufrollen ausgebildete Wälzkörper 14 angeordnet sind, die relativ zur Axialrichtung des Mantelrings 10 in Radialrichtung und in Umfangsrichtung schräg angestellt sind.The shroud 10 is concentrically surrounded by a trained as a coupling ring adjusting device 11. According to Fig. 1 are opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11 frustoconically contoured, being formed between the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 and thus formed between the outer ring 10 and actuator 11 as cylindrical rollers rolling elements 14, the relatively are employed obliquely to the axial direction of the shroud 10 in the radial direction and in the circumferential direction.

Bedingt dadurch, dass zwischen dem Mantelring 10 und der Stelleinrichtung 11, welche den Mantelring 10 konzentrisch umgibt, die Wälzkörper 14 angeordnet sind, kann die Stelleinrichtung 11 gegenüber dem Mantelring 10 verdreht werden. Da die sich gegenüberliegenden Flächen 12 und 13 von Mantelring 10 und Stelleinrichtung 11 kegelstumpfförmig konturiert sind und die Wälzkörper 14 relativ zur Axialrichtung des Mantelrings 10 schräg angestellt sind, bewirkt diese Verdrehung der Stelleinrichtung 11 relativ zur Gehäusewand 10 im Sinne des Pfeils 15 weiterhin im Sinne des Pfeils 16 eine translatorische Verschiebung der Stelleinrichtung 11 relativ zum Mantelring 10, aufgrund derer gleichzeitig der Durchmesser des Mantelrings 10 und damit der Spalt zwischen dem Mantelring 10 und dem nicht-dargestellten Laufschaufelkranz eingestellt werden kann.Due to the fact that between the shroud 10 and the adjusting device 11, which surrounds the shroud 10 concentrically, the rolling elements 14 are arranged, the adjusting device 11 can be rotated relative to the shroud 10. Since the opposing surfaces 12 and 13 of the outer ring 10 and adjusting device 11 are frustoconical contoured and the rolling elements 14 are employed obliquely relative to the axial direction of the shroud 10, this rotation of the actuating device 11 relative to the housing wall 10 in the direction of the arrow 15 continues in the sense of Arrow 16 a translational displacement of the adjusting device 11 relative to the shroud 10, due to which the diameter of the shroud 10 and thus the gap between the shroud 10 and the blade ring, not shown, can be adjusted simultaneously.

Es sei darauf hingewiesen, dass die Wälzkörper 14 vorzugsweise als sogenannte käfiggeführte Laufrollen ausgebildet sind.It should be noted that the rolling elements 14 are preferably formed as so-called cage-guided rollers.

Ausgehend von einer Ausgangsstellung der Stelleinrichtung 11 relativ zum Mantelring 10 ist in einer ersten Drehrichtung der ringartigen Stelleinrichtung 11 das Spaltmaß des Spalts bezogen auf ein Ausgangsmaß verkleinerbar, in einer zweiten Drehrichtung der Stelleinrichtung 11 ist das Spaltmaß gegenüber dem Ausgangsmaß vergrößerbar.Starting from a starting position of the adjusting device 11 relative to the shroud 10 is in a first direction of rotation of the ring-type adjusting device 11, the gap of the gap reduced in size in relation to an initial dimension, in a second direction of rotation of the adjusting device 11, the gap dimension can be increased relative to the initial dimension.

Bei der Verdrehung der ringartigen Stelleinrichtung 11 gegenüber dem Mantelring 10 wird der Mantelring 10 zur Einstellung des Spaltmaßes elastisch verformt.When rotating the ring-like adjusting device 11 relative to the shroud 10 of the shroud 10 is elastically deformed to adjust the gap.

Gemäß der hier vorliegenden Erfindung wird demnach zur Anpassung des Spalts zwischen dem Mantelring 10 und einem radial außenliegenden Ende eines Laufschaufelkranzes, der von dem Mantelring 10 umgeben ist, ein Mechanismus vorgeschlagen, der im Wesentlichen aus zwei konzentrischen Ringen besteht, nämlich einem ersten Ring, der von dem Mantelring 10 gebildet ist, und einem zweiten Ring, der von der Stelleinrichtung 11 gebildet ist. Zwischen diesen beiden Ringen, also zwischen dem Mantelring 10 und der Stelleinrichtung 11, sind vorzugsweise als Laufrollen ausgebildete Wälzkörper 14 angeordnet, die ein Verdrehen der Stelleinrichtung 11 relativ zum Mantelring 10 zulassen. Diese Wälzkörper 14 sind relativ zur Axialerstreckung der Gehäusewand 10 und damit relativ zur Axialerstreckung der Turbomaschine in Umfangsrichtung und in Radialrichtung schräg gestellt, wobei die sich gegenüberliegenden Flächen 12, 13 von Mantelring 10 und Stelleinrichtung 11, zwischen denen die Wälzkörper 14 angeordnet sind, kegelstumpfförmig konturiert sind.According to the present invention, therefore, to adapt the gap between the shroud 10 and a radially outer end of a blade ring, which is surrounded by the shroud 10, proposed a mechanism consisting essentially of two concentric rings, namely a first ring, the is formed by the shroud 10, and a second ring, which is formed by the adjusting device 11. Between these two rings, ie between the shroud 10 and the adjusting device 11, rolling elements 14 designed as rollers are preferably arranged, which allow the adjusting device 11 to rotate relative to the shroud 10. These rolling elements 14 are inclined relative to the axial extension of the housing wall 10 and thus relative to the axial extension of the turbomachine in the circumferential direction and in the radial direction, wherein the opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11, between which the rolling elements 14 are arranged frustoconically contoured are.

Hierdurch bewirkt die Verdrehung der Stelleinrichtung 11 relativ zum Mantelrings 10 weiterhin eine Axialverschiebung der Verstelleinrichtung 11 relativ zum Mantelring 10. Die Stelleinrichtung 11 wird sozusagen auf den Mantelring 10 aufgeschraubt. Hierbei verformt die in einer relativ dicken Wandstärke ausgeführte Stelleinrichtung 11 den in einer relativ dünnen Wandstarke ausgeführten Mantelring 10 im Sinne einer elastischen Verformung, so dass durch Verdrehen der Stelleinrichtung 11 relativ zum Mantelring 10 der Durchmesser des Mantelrings 10 angepasst und damit der Spalt zwischen dem Mantelring und dem Laufschaufelkranz eingestellt werden kann. Es ist auch möglich, die Stelleinrichtung 11 aus einem steiferen Werkstoff als den Mantelring 10 zu fertigen,As a result, the rotation of the actuating device 11 relative to the shroud 10 further causes an axial displacement of the adjusting device 11 relative to the shroud 10. The actuating device 11 is screwed onto the shroud 10, so to speak. Here, the executed in a relatively thick wall thickness adjusting device 11 deforms the executed in a relatively thin wall thickness shroud 10 in the sense of elastic deformation, so adjusted by turning the actuator 11 relative to the shroud 10, the diameter of the shroud 10 and thus the gap between the shroud and the blade ring can be adjusted. It is also possible to manufacture the adjusting device 11 from a stiffer material than the shroud 10,

Der erfindungsgemäße Mechanismus zur Bereitstellung einer Active Clearance Control an einer Turbomaschine zeichnet sich durch einen kompakten Aufbau mit einer geringen Bauhöhe aus. Es sind nur geringe Verstellkräfte und keine Haltekräfte erforderlich. Bauteile werden vorwiegend auf Zug und Druck belastet, sind jedoch keiner oder nur einer geringen Biegebelastung ausgesetztThe inventive mechanism for providing an active clearance control on a turbomachine is characterized by a compact design with a low Height from. There are only small adjustment forces and no holding forces required. Components are mainly loaded on train and pressure, but are exposed to little or no bending load

Claims (5)

  1. A turbo-engine having a stator and a rotor, wherein the rotor has rotor blades and the stator has a housing and guide blades, wherein the rotor blades on the rotor side form at least one rotor-blade ring which at a radially external end of the same adjoins a radially internal housing wall of the housing formed as a jacket ring, is surrounded by the same and delimits a gap with the same, and wherein the gap between the jacket ring of the housing and the radially external end of the or each rotor-blade ring can be set by deformation of the jacket ring, wherein the jacket ring (10) is concentrically surrounded by an adjusting device (11) that is formed as a retaining ring,
    characterised in that
    opposing faces (12, 13) of the jacket ring (10) and of the adjusting device (11) have the contours of a truncated cone, and in that positioned between the jacket ring (10) and the adjusting device (11) in the radial direction and in the circumferential direction there are cylindrical rolling bodies (14) that are set obliquely in relation to the axial direction so that the adjusting device (11) can be rotated in relation to the jacket ring (10) with simultaneous setting of the gap.
  2. A turbo-engine according to claim 1,
    characterised in that
    upon rotation of the adjusting device (11), which is formed as a retaining ring, in relation to the jacket ring (10) the adjusting device can be adjusted in relation to the jacket ring (10) in the axial direction with simultaneous elastic deformation of the jacket ring (10) in order to set the gap.
  3. A turbo-engine according to claim 1 or 2,
    characterised in that
    in a first direction of rotation of the adjusting device (11) a gap clearance of the gap can be diminished relative to an initial dimension that is defined by an initial position of the adjusting device (11), and in that in a second direction of rotation of the adjusting device (11) a gap clearance of the gap can be enlarged relative to an initial dimension that is defined by an initial position of the adjusting device (11).
  4. A turbo-engine according to one or more of claims 1 to 3,
    characterised in that
    the adjusting device (11) is constructed with relatively thick walls, and the jacket ring (10) is constructed with relatively thin walls.
  5. A turbo-engine according to one or more of claims 1 to 4,
    characterised in that
    the adjusting device (11) is made from a material that is stiffer than that of the jacket ring (10).
EP08706764A 2007-01-20 2008-01-16 Turbo engine with active clearance control Not-in-force EP2129875B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007003028A DE102007003028A1 (en) 2007-01-20 2007-01-20 turbomachinery
PCT/DE2008/000067 WO2008086782A2 (en) 2007-01-20 2008-01-16 Turbo engine

Publications (2)

Publication Number Publication Date
EP2129875A2 EP2129875A2 (en) 2009-12-09
EP2129875B1 true EP2129875B1 (en) 2011-03-09

Family

ID=39530809

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Application Number Title Priority Date Filing Date
EP08706764A Not-in-force EP2129875B1 (en) 2007-01-20 2008-01-16 Turbo engine with active clearance control

Country Status (7)

Country Link
US (1) US8376691B2 (en)
EP (1) EP2129875B1 (en)
AT (1) ATE501340T1 (en)
CA (1) CA2676012A1 (en)
DE (2) DE102007003028A1 (en)
ES (1) ES2358165T3 (en)
WO (1) WO2008086782A2 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070162152A1 (en) * 2005-03-31 2007-07-12 Massachusetts Institute Of Technology Artificial joints using agonist-antagonist actuators
DE102008042582A1 (en) 2008-10-02 2010-04-08 Bundesdruckerei Gmbh Method for storing data for managing digital identity of user, involves writing data from provider computer system to token via connection to store data in token, and providing connections with connection-oriented protocol
DE102008042262B4 (en) 2008-09-22 2010-05-27 Bundesdruckerei Gmbh Method for storing data, computer program product, ID token and computer system
EP2233701A1 (en) * 2009-03-26 2010-09-29 Siemens Aktiengesellschaft Axial turbomachine with axially displaceable vane carrier
US9784117B2 (en) 2015-06-04 2017-10-10 United Technologies Corporation Turbine engine tip clearance control system with rocker arms
US9752450B2 (en) * 2015-06-04 2017-09-05 United Technologies Corporation Turbine engine tip clearance control system with later translatable slide block

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
GB2416194B (en) * 2004-07-15 2006-08-16 Rolls Royce Plc A spacer arrangement
DE102004037955A1 (en) 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine
EP1655455A1 (en) 2004-11-05 2006-05-10 Siemens Aktiengesellschaft Turbomachine having a guide vane support with adjustable radial clearance

Also Published As

Publication number Publication date
DE102007003028A1 (en) 2008-07-24
WO2008086782A2 (en) 2008-07-24
US20100054921A1 (en) 2010-03-04
CA2676012A1 (en) 2008-07-24
US8376691B2 (en) 2013-02-19
DE502008002810D1 (en) 2011-04-21
EP2129875A2 (en) 2009-12-09
WO2008086782A3 (en) 2009-11-19
ES2358165T3 (en) 2011-05-06
ATE501340T1 (en) 2011-03-15

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