EP1249577A1 - Gas turbine with axially movable shroud elements - Google Patents

Gas turbine with axially movable shroud elements Download PDF

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Publication number
EP1249577A1
EP1249577A1 EP01109198A EP01109198A EP1249577A1 EP 1249577 A1 EP1249577 A1 EP 1249577A1 EP 01109198 A EP01109198 A EP 01109198A EP 01109198 A EP01109198 A EP 01109198A EP 1249577 A1 EP1249577 A1 EP 1249577A1
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EP
European Patent Office
Prior art keywords
gas turbine
turbine according
guide part
rib
guide
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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
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EP01109198A
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German (de)
French (fr)
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EP1249577B1 (en
Inventor
Christian Dr. Scholz
Peter Tiemann
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Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP01109198A priority Critical patent/EP1249577B1/en
Priority to ES01109198T priority patent/ES2286054T3/en
Priority to DE50112597T priority patent/DE50112597D1/en
Priority to JP2002106196A priority patent/JP4283488B2/en
Priority to US10/120,808 priority patent/US6676372B2/en
Priority to CNB02119078XA priority patent/CN100400797C/en
Publication of EP1249577A1 publication Critical patent/EP1249577A1/en
Application granted granted Critical
Publication of EP1249577B1 publication Critical patent/EP1249577B1/en
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    • 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

Definitions

  • the invention relates to a gas turbine with a guide and with a blade ring in a gas channel and with a Housing and axially secured against rotation against each other sliding funnel-shaped guide parts as a carrier of rings forming an outer jacket of the gas channel.
  • Gas turbines are often not only in their starting phase, but also subject to changing loads even in continuous operation. This has especially with regard to that of individual components assume a transient temperature Operation as a result. To avoid damage to the turbine the individual components are therefore usually clamped in such a way that they are unhindered thermally induced dimensional changes can execute.
  • Turbine losses due to cross currents over their blade tips to minimize as much as possible are the smallest possible radial gap between the blade tips and these opposite guide surfaces. Because both the blades and their rotor as well as guide blades and their carriers as well as an all-connecting housing expand differently in time with each load change and / or shrink, there is an optimal radial Gap over the blade tips only for very few of any number of stationary operating states. The These gas turbines are therefore often operated with a not optimized gap width and therefore with a not optimized efficiency.
  • the invention is based on the object of a gas turbine system to develop further in such a way that with her over Variety of operating conditions an optimal blade tip gap is given, so that a basic requirement for Achieving good efficiency is guaranteed.
  • This task is the one specified for a gas turbine kind solved according to the invention, in which at least one of the funnel-shaped guide parts controlled axially by a motor is movable. Appropriately serve as a motor Variety of hydraulic on the circumference of the guide part Press. However, every other type of drive is Content of this invention.
  • the particular advantage of this arrangement lies in the possibility of the blade tip gap actively set by moving the guide part axially. at the limitation of the active adjustability to axial movements is advantageous due to the funnel-shaped shape given the conicity of the guide part, because due to this taper, any axial displacement will result the same also a change in the substantially radial looking at blade tip gap.
  • An embodiment of the invention is based on a drawing explained in more detail. The only figure of this drawing shows a longitudinal section through a turbine between a propellant and exit.
  • Blade rings 2 with a plurality of blades 3 wedged.
  • One by vane rings 4 with a variety gas flow 6 guided by guide vanes 5 expands through a Gas channel 7 and drives the blades 3.
  • the gas channel 7 has an annular cross section and is at its pressure side end with a hot gas chamber 8 connected from which compressed and heated gas Arrow direction is driven to a gas outlet opening 9.
  • a radially inner boundary of the gas channel 7 is from Hubs 10 of the rotor blades wedged on the turbine shaft 1 2 and carried by the inner ends of the guide vanes 5, non-rotating hubs 11 of the guide vane rings 4 educated. Joints between the hubs 10 and the hubs 11 are sealed by labyrinth seals.
  • a radially outer boundary of the gas channel 7 has one funnel-shaped, conical shape and is defined by rings 12 and 13 educated.
  • the rings 12 and 13 are funnel-shaped Guide parts 14 and 15 worn, the rings 12 the free
  • the ends of the blades 3 lie opposite one another and the rings 13 hold the outer ends of the guide vanes 5 and thus the wear 4 of these vane ring formed. Gaps between the rings 12 and 13 are separated by suitable Sealed sealing rings not shown.
  • the guide parts 14 and 15 are thick-walled, very rigid and on in cross section preferably rectangular blocks 16 axially slidably mounted.
  • the blocks 16 are in a housing 17th anchored and each of the guide parts 14 and 15 engages his both ends in a wreath from a variety of blocks 16, so that tilting for the guide parts 14 and 15 as well is excluded, like radial movements.
  • the housing 17 is as stiff as the guide parts 14 and 15 and carries on the inside, apart from the blocks 16 per guide part 14 or 15 a rigid rib 18.
  • This rigid rib 18 is in each case provided axially between the rings of blocks 16, which are assigned to the same guide part 14 or 15.
  • the rigid one Rib 18 is particularly practical in the axial direction not deformable.
  • Each of the guide parts 14 and 15 carries one radially outward protruding, comparatively thin-walled stop rib 19, which on the hot gas chamber 8 side of the associated rigid rib 18 with one of its free end supported bead 20 supports.
  • a reinforcement 21 is arranged, which is also the rigid Rib 18 is facing, but shorter in the axial direction than the bead is 20.
  • the guide parts 14 and 15 are in the gas outlet opening 9 facing area radially outwards through a cross section preferably comprises trapezoidal stiffening rib 22, the one radially oriented, the associated rigid Rib 18 has opposite stop surface 23. Between the rigid ribs 18 and their opposite Stop surface 23 are even on the circumference of the associated guide part 14 or 15 distributes a large number arranged by hydraulic presses. Piston 24 of these presses are based directly on the rigid rib 18 and Associated cylinders 25 of the presses lie on the stop surface 23 of the stiffening rib 22. An annular space between the Housing 17 and the guide parts 14 and 15 is membrane-like Partitions 26 divided into chambers.
  • the arrangement according to the invention now enables a targeted, active adjustment of just the width of this gap. To this For this purpose, this width is measured by sensors, not shown. If you want to reduce the gap width then by the motor represented by the presses Guide part 14 and / or 15 in the direction of the gas outlet opening 9 moved.
  • the stop rib 19 resiliently clamped so that they are in the opposite direction required movement the guide member 14 or 15 carrying them pushes back towards the hot gas chamber 8.
  • This task is achieved by the same guiding part 14 or 15 associated presses together have an axial force something 10 times that of gas flow 6 due to operational reasons exerted on the relevant guide member 14 or 15 axial force equivalent. Both axial forces act in the direction the gas outlet opening 9 and add up.
  • Deformation energy is used when adjusting a guide part 14 or 15 in the direction of the gas outlet opening 9 saved and serves in an opposite movement to generate a restoring force.
  • This restoring force is in any position of the associated guide part 14 or 15 larger than that due to the operation of the gas stream 6 on this applied axial force.
  • the restoring force is preferably about 2 to 3 times as large as the operational axial force.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

The turbine has axially displaceable casing parts (14, 15) to compensate for thermal expansion, which form the outside of a funnel-shaped gas channel (7). At least one of these casing parts is driven by a motor for its axial displacement, thus altering the width of the blade tip gap as a result of the funnel-shaped design of the casing parts.

Description

Die Erfindung betrifft eine Gasturbine mit einem Leit- und mit einem Laufschaufelkranz in einem Gaskanal und mit einem Gehäuse sowie darin gegen Rotation gesicherten axial gegeneinander verschiebbaren trichterförmigen Leitteilen als Träger von einen äußeren Mantel des Gaskanals bildenden Ringen.The invention relates to a gas turbine with a guide and with a blade ring in a gas channel and with a Housing and axially secured against rotation against each other sliding funnel-shaped guide parts as a carrier of rings forming an outer jacket of the gas channel.

Gasturbinen werden häufig nicht nur in ihrer Startphase, sondern auch im Dauerbetrieb mit wechselnden Lasten beaufschlagt. Das hat insbesondere auch hinsichtlich der von den einzelnen Bauteilen angenommen Temperaturen einen instationären Betrieb zur Folge. Zur Vermeidung von Schäden an der Turbine sind daher die einzelnen Bauteile üblicherweise so eingespannt, daß sie thermisch bedingte Maßänderungen ungehindert ausführen können.Gas turbines are often not only in their starting phase, but also subject to changing loads even in continuous operation. This has especially with regard to that of individual components assume a transient temperature Operation as a result. To avoid damage to the turbine the individual components are therefore usually clamped in such a way that they are unhindered thermally induced dimensional changes can execute.

Um Turbinenverluste durch Querströmungen über ihren Laufschaufelspitzen weitgehend zu minimieren, sind kleinstmögliche radiale Spalte zwischen den Laufschaufelspitzen und diesen gegenüberliegenden Leitflächen einzuhalten. Da sich sowohl die Laufschaufeln und ihr Rotor als auch Leitschaufeln und ihre Träger ebenso wie ein alles verbindendes Gehäuse zeitlich gesehen bei jeder Laständerung unterschiedlich ausdehnen und/oder schrumpfen, stellt sich ein optimaler radialer Spalt über den Laufschaufelspitzen nur für sehr wenige von beliebig vielen stationären Betriebszuständen ein. Der Betrieb dieser Gasturbinen erfolgt daher häufig mit einer nicht optimierten Spaltweite und demzufolge mit einem nicht optimierten Wirkungsgrad.Turbine losses due to cross currents over their blade tips to minimize as much as possible are the smallest possible radial gap between the blade tips and these opposite guide surfaces. Because both the blades and their rotor as well as guide blades and their carriers as well as an all-connecting housing expand differently in time with each load change and / or shrink, there is an optimal radial Gap over the blade tips only for very few of any number of stationary operating states. The These gas turbines are therefore often operated with a not optimized gap width and therefore with a not optimized efficiency.

Durch die US-PS 4,177,004 ist eine Turbinengestaltung bekannt, bei der die Laufschaufelspitzen selbst Werkstoff von einer ihnen gegenüberliegenden Leitfläche abtragen, so daß für diese Anordnung bei dem Betriebszustand, bei dem die größte Annäherung der Laufschaufelspitzen an die Leitflächen erfolgt, der Laufschaufelspitzenspalt nahezu verschwindet. Bei jedem anderen Betriebszustand ist jedoch auch bei dieser bekannten Anordnung der Laufschaufelspitzenspalt wieder größer und damit weniger günstig.A turbine design is known from US Pat. No. 4,177,004, where the blade tips themselves are made of remove a guide surface opposite them so that for this arrangement in the operating state in which the greatest approach of the blade tips to the guide surfaces occurs, the blade tip gap almost disappears. In any other operating state, however, this is also the case known arrangement of the blade tip gap again larger and therefore less cheap.

Bei anderen bisher bekannten Anordnungen ist es zwar gelungen, durch die Auswahl geeigneter Werkstoffpaarungen die thermisch bedingten Relativbewegungen der Bauteile für viele Betriebszustände gering zu halten, aber auch dort gilt, daß nur jeweils bei einem bestimmten stationären Zustand ein optimaler Laufschaufelspitzenspalt herrscht. Bei jedem anderen Zustand treten wiederum weniger günstige Verhältnisse ein.With other arrangements known to date, it has been possible to through the selection of suitable material combinations thermally induced relative movements of the components for many To keep operating conditions low, but also applies there that only an optimal one at a certain steady state Blade tip gap prevails. With everyone else In turn, conditions are less favorable.

Der Erfindung liegt nun die Aufgabe zugrunde, eine Gasturbinenanlage so weiter zu entwickeln, daß bei ihr über eine Vielzahl von Betriebszuständen ein optimaler Laufschaufelspitzenspalt gegeben ist, so daß eine Grundvoraussetzung zur Erzielung eines guten Wirkungsgrades gewährleistet ist.The invention is based on the object of a gas turbine system to develop further in such a way that with her over Variety of operating conditions an optimal blade tip gap is given, so that a basic requirement for Achieving good efficiency is guaranteed.

Diese Aufgabe ist für eine Gasturbine der eingangs angegebenen Art erfindungsgemäß gelöst, in dem mindestens eines der trichterförmigen Leitteile durch einen Motor gesteuert axial verschiebbar ist. Zweckmäßig dienen dabei als Motor eine Vielzahl von auf den Umfang des Leitteiles verteilte hydraulische Pressen. Jedoch auch jede andere Art von Antrieben ist Inhalt dieser Erfindung. Der besondere Vorteil dieser Anordnung liegt in der Möglichkeit den Laufschaufelspitzenspalt durch axiale Bewegung des Leitteils aktiv einzustellen. Bei der Beschränkung der aktiven Einstellbarkeit auf axiale Bewegungen wird vorteilhaft die durch die trichterförmige Gestalt des Leitteils gegebene Konizität desselben ausgenutzt, denn infolge dieser Konizität bewirkt jede axiale Verschiebung desselben auch eine Veränderung des im wesentlichen radial zu betrachtenden Laufschaufelspitzenspalts. This task is the one specified for a gas turbine Kind solved according to the invention, in which at least one of the funnel-shaped guide parts controlled axially by a motor is movable. Appropriately serve as a motor Variety of hydraulic on the circumference of the guide part Press. However, every other type of drive is Content of this invention. The particular advantage of this arrangement lies in the possibility of the blade tip gap actively set by moving the guide part axially. at the limitation of the active adjustability to axial movements is advantageous due to the funnel-shaped shape given the conicity of the guide part, because due to this taper, any axial displacement will result the same also a change in the substantially radial looking at blade tip gap.

Weitere zweckmäßige und vorteilhafte Ausführungen der erfindungsgemäßen Anordnung sind in den Ansprüchen 3 bis 12 angegeben.Further expedient and advantageous embodiments of the invention Arrangement are given in claims 3 to 12.

Ein Ausführungsbeispiel der Erfindung ist anhand einer Zeichnung näher erläutert. Die einzige Fig. dieser Zeichnung zeigt einen Längsschnitt durch eine Turbine zwischen einem Treibgasein- und -austritt.An embodiment of the invention is based on a drawing explained in more detail. The only figure of this drawing shows a longitudinal section through a turbine between a propellant and exit.

Auf einer nicht näher dargestellten Turbinenwelle 1 sind Laufschaufelkränze 2 mit einer Vielzahl von Laufschaufeln 3 verkeilt. Ein durch Leitschaufelkränze 4 mit einer Vielzahl von Leitschaufeln 5 geführter Gasstrom 6 expandiert durch einen Gaskanal 7 und treibt dabei die Laufschaufeln 3.Are on a turbine shaft 1, not shown Blade rings 2 with a plurality of blades 3 wedged. One by vane rings 4 with a variety gas flow 6 guided by guide vanes 5 expands through a Gas channel 7 and drives the blades 3.

Der Gaskanal 7 hat einen kreisringförmigen Querschnitt und ist an seinem druckseitigen Ende mit einer Heißgaskammer 8 verbunden, aus der komprimiertes und aufgeheiztes Gas in Pfeilrichtung zu einer Gasaustrittsöffnung 9 getrieben wird. Eine radial innenliegende Begrenzung des Gaskanals 7 wird von auf der Turbinenwelle 1 verkeilten Naben 10 der Laufschaufelkränze 2 und von den inneren Enden der Leitschaufeln 5 getragenen, nicht rotierenden Naben 11 der Leitschaufelkränze 4 gebildet. Fugen zwischen den Naben 10 und den Naben 11 sind durch Labyrinthdichtungen verschlossen.The gas channel 7 has an annular cross section and is at its pressure side end with a hot gas chamber 8 connected from which compressed and heated gas Arrow direction is driven to a gas outlet opening 9. A radially inner boundary of the gas channel 7 is from Hubs 10 of the rotor blades wedged on the turbine shaft 1 2 and carried by the inner ends of the guide vanes 5, non-rotating hubs 11 of the guide vane rings 4 educated. Joints between the hubs 10 and the hubs 11 are sealed by labyrinth seals.

Eine radial außenliegende Begrenzung des Gaskanals 7 hat eine trichterförmige, konische Form und wird durch Ringe 12 und 13 gebildet. Die Ringe 12 und 13 werden von trichterförmigen Leitteilen 14 und 15 getragen, wobei die Ringe 12 den freien Enden der Laufschaufeln 3 gegenüberliegen und die Ringe 13 die äußeren Enden der Leitschaufeln 5 halten und damit den von diesen gebildeten Leitschaufelkranz 4 insgesamt tragen. Spalten zwischen den Ringen 12 und 13 sind durch geeignete, nicht dargestellte Dichtringe verschlossen. A radially outer boundary of the gas channel 7 has one funnel-shaped, conical shape and is defined by rings 12 and 13 educated. The rings 12 and 13 are funnel-shaped Guide parts 14 and 15 worn, the rings 12 the free The ends of the blades 3 lie opposite one another and the rings 13 hold the outer ends of the guide vanes 5 and thus the wear 4 of these vane ring formed. Gaps between the rings 12 and 13 are separated by suitable Sealed sealing rings not shown.

Die Leitteile 14 und 15 sind dickwandig, sehr steif und auf im Querschnitt vorzugsweise rechteckigen Klötzen 16 axial verschiebbar gelagert. Die Klötze 16 sind in einem Gehäuse 17 verankert und jedes der Leitteile 14 und 15 greift an seinen beiden Enden in je einen Kranz aus einer Vielzahl von Klötzen 16, so daß ein Verkanten für die Leitteile 14 und 15 ebenso ausgeschlossen ist, wie radiale Bewegungen.The guide parts 14 and 15 are thick-walled, very rigid and on in cross section preferably rectangular blocks 16 axially slidably mounted. The blocks 16 are in a housing 17th anchored and each of the guide parts 14 and 15 engages his both ends in a wreath from a variety of blocks 16, so that tilting for the guide parts 14 and 15 as well is excluded, like radial movements.

Das Gehäuse 17 ist, bedingt durch seine Form und seine Wandstärke, ebenso steif wie die Leitteile 14 und 15 und trägt auf seiner Innenseite außer den Klötzen 16 je Leitteil 14 bzw. 15 eine starre Rippe 18. Diese starre Rippe 18 ist jeweils axial zwischen den Kränzen von Klötzen 16 vorgesehen, die demselben Leitteil 14 bzw. 15 zugeordnet sind. Die starre Rippe 18 ist insbesondere auch in axialer Richtung praktisch nicht verformbar.Due to its shape and wall thickness, the housing 17 is as stiff as the guide parts 14 and 15 and carries on the inside, apart from the blocks 16 per guide part 14 or 15 a rigid rib 18. This rigid rib 18 is in each case provided axially between the rings of blocks 16, which are assigned to the same guide part 14 or 15. The rigid one Rib 18 is particularly practical in the axial direction not deformable.

Jedes der Leitteile 14 und 15 trägt eine radial nach außen vorstehende, vergleichsweise dünnwandige Anschlagrippe 19, die sich auf der der Heißgaskammer 8 zugekehrten Seite der zugehörigen starren Rippe 18 mit einem von ihrem freien Ende getragenen Wulst 20 abstützt. Am Fuß der Anschlagrippe 19 ist eine Verstärkung 21 angeordnet, die zwar ebenfalls der starren Rippe 18 zugekehrt ist, aber in axialer Richtung kürzer als der Wulst 20 ist.Each of the guide parts 14 and 15 carries one radially outward protruding, comparatively thin-walled stop rib 19, which on the hot gas chamber 8 side of the associated rigid rib 18 with one of its free end supported bead 20 supports. At the foot of the stop rib 19 is a reinforcement 21 is arranged, which is also the rigid Rib 18 is facing, but shorter in the axial direction than the bead is 20.

Die Leitteile 14 und 15 sind in ihrem der Gasaustrittsöffnung 9 zugekehrten Bereich radial nach außen durch eine im Querschnitt vorzugsweise trapezförmige Versteifungsrippe 22 umfasst, die eine radial ausgerichtete, der zugeordneten starren Rippe 18 gegenüberliegende Anschlagfläche 23 aufweist. Zwischen den starren Rippen 18 und der ihr jeweils gegenüberliegenden Anschlagsfläche 23 sind gleichmäßig auf den Umfang des zugehörigen Leitteils 14 oder 15 verteilt eine Vielzahl von hydraulischen Pressen angeordnet. Kolben 24 dieser Pressen stützen sich unmittelbar an der starren Rippe 18 ab und zugehörige Zylinder 25 der Pressen liegen auf der Anschlagsfläche 23 der Versteifungsrippe 22. Ein Ringraum zwischen dem Gehäuse 17 und den Leitteilen 14 und 15 ist durch membranartige Zwischenwände 26 in Kammern unterteilt.The guide parts 14 and 15 are in the gas outlet opening 9 facing area radially outwards through a cross section preferably comprises trapezoidal stiffening rib 22, the one radially oriented, the associated rigid Rib 18 has opposite stop surface 23. Between the rigid ribs 18 and their opposite Stop surface 23 are even on the circumference of the associated guide part 14 or 15 distributes a large number arranged by hydraulic presses. Piston 24 of these presses are based directly on the rigid rib 18 and Associated cylinders 25 of the presses lie on the stop surface 23 of the stiffening rib 22. An annular space between the Housing 17 and the guide parts 14 and 15 is membrane-like Partitions 26 divided into chambers.

Alle demselben Leitteil 14 bzw. 15 zugeordneten Pressen bilden zusammen jeweils einen Linearmotor, der das von ihm beaufschlagte Leitteil 14 oder 15 gegenüber dem Gehäuse 17 axial in Richtung auf die Gasaustrittsöffnung 9 verschiebt. Bei dieser Verschiebung liegt die Anschlagrippe 19 mit ihrem Wulst 20 an der starren Rippe 18 und wird elastisch verformt. Die von den trichterförmigen Leitteilen 14 und 15 getragenen Ringe 12 liegen angenähert auf einem Kegelmantel und verändern bei axialer Verschiebung die Weite des Laufschaufelspitzenspaltes. Um ein Anstreifen eines Ringes 12 an den Spitzen der Laufschaufeln 3 auszuschließen, ist der axial mögliche Weg der Leitteile 14 bzw. 15 begrenzt. Als Endanschlag dient zu diesem Zweck die Verstärkung 21 als Anschlag an der starren Rippe 18.Form all presses assigned to the same guide part 14 or 15 each together a linear motor that applied to it Guide part 14 or 15 opposite the housing 17th axially in the direction of the gas outlet opening 9. During this shift, the stop rib 19 lies with her Bead 20 on the rigid rib 18 and is elastically deformed. Those carried by the funnel-shaped guide parts 14 and 15 Rings 12 lie approximately on a cone jacket and change with axial displacement, the width of the blade tip gap. To rub a ring 12 on the tips to exclude the blades 3 is the axially possible Path of the guide parts 14 and 15 limited. Serves as an end stop for this purpose the reinforcement 21 as a stop on the rigid Rib 18.

Beim Anfahren der Gasturbine herrscht, ebenso wie bei jeder Laständerung an praktisch allen mit Bezugszeichen versehenen Teilen ein thermisch instabiler Zustand. Dabei sind die Änderungsgeschwindigkeiten an den einzelnen Teilen sehr unterschiedlich, so daß dementsprechend unterschiedliche Wärmedehnungen und -schrumpfungen an diesen Teilen auftreten. Diese unterschiedlichen Temperaturänderungen führen demzufolge zu Relativbewegungen der Teile gegeneinander, wobei insbesondere Veränderungen der Weite des Spaltes zwischen den Ringen 12 und den diesen gegenüberliegenden Spitzen der Laufschaufeln 3 einen nicht unwesentlichen Einfluss auf den Wirkungsgrad der Turbine haben.When starting the gas turbine, as with everyone Load change on practically all those with reference numerals Share a thermally unstable condition. Here are the rates of change very different on the individual parts, so that different thermal expansions and shrinkage occur on these parts. This consequently different temperature changes lead to Relative movements of the parts against each other, in particular Changes in the width of the gap between the rings 12 and the tips of the rotor blades 3 opposite these a not insignificant influence on the efficiency of the Have turbine.

Die erfindungsgemäße Anordnung ermöglicht nun eine gezielte, aktive Einstellung gerade der Weite dieses Spaltes. Zu diesem Zweck wird diese Weite durch nicht dargestellte Sensoren gemessen. Bei erwünschter Verkleinerung der Spaltweite wird dann durch den von den Pressen dargestellten Motor das betreffende Leitteil 14 und/oder 15 in Richtung der Gasaustrittsöffnung 9 verschoben. Dabei wird die Anschlagrippe 19 federnd verspannt, so daß sie bei einer in der Gegenrichtung erforderlichen Bewegung das sie tragende Leitteil 14 oder 15 in Richtung auf die Heißgaskammer 8 zurückschiebt. Zur Erfüllung dieser Aufgabe erreichen die jeweils demselben Leitteil 14 oder 15 zugeordneten Pressen zusammen eine Axialkraft, die etwas dem 10-fachen einer betriebsbedingt von dem Gasstrom 6 auf das betreffende Leitteil 14 oder 15 ausgeübten Axialkraft entspricht. Dabei wirken beide Axialkräfte in Richtung auf die Gasaustrittsöffnung 9 und addieren sich.The arrangement according to the invention now enables a targeted, active adjustment of just the width of this gap. To this For this purpose, this width is measured by sensors, not shown. If you want to reduce the gap width then by the motor represented by the presses Guide part 14 and / or 15 in the direction of the gas outlet opening 9 moved. The stop rib 19 resiliently clamped so that they are in the opposite direction required movement the guide member 14 or 15 carrying them pushes back towards the hot gas chamber 8. To fulfillment This task is achieved by the same guiding part 14 or 15 associated presses together have an axial force something 10 times that of gas flow 6 due to operational reasons exerted on the relevant guide member 14 or 15 axial force equivalent. Both axial forces act in the direction the gas outlet opening 9 and add up.

Die bei ihrer Verformung von der Anschlagrippe 19 aufgenommene Verformungsenergie wird bei der Verstellung eines Leitteils 14 oder 15 in Richtung auf die Gasaustrittsöffnung 9 gespeichert und dient bei einer entgegengesetzten Bewegung zur Erzeugung einer Rückstellkraft. Diese Rückstellkraft ist in jeder Stellung des zugehörigen Leitteils 14 oder 15 größer, als die betriebsbedingt vom Gasstrom 6 auf dieses ausgeübte Axialkraft. Vorzugsweise ist die Rückstellkraft etwa 2 bis 3 mal so groß, wie die betriebsbedingte Axialkraft. Dadurch ist jedes der Leitteile 14 und 15 in jeder Stellung spielfrei an der starren Rippe 18 festgespannt.The one received by the stop rib 19 during its deformation Deformation energy is used when adjusting a guide part 14 or 15 in the direction of the gas outlet opening 9 saved and serves in an opposite movement to generate a restoring force. This restoring force is in any position of the associated guide part 14 or 15 larger than that due to the operation of the gas stream 6 on this applied axial force. The restoring force is preferably about 2 to 3 times as large as the operational axial force. As a result, each of the guide members 14 and 15 is in each Position clamped free of play on the rigid rib 18.

Claims (12)

Gasturbine mit einem Leit- (4) und mit einem Laufschaufelkranz (2) in einem Gaskanal (7) und mit einem Gehäuse (17) sowie darin gegen Rotation gesicherten axial gegeneinander verschiebbaren, trichterförmigen Leitteilen (14/15) als Träger von einen äußeren Mantel des Gaskanals (7) bildenden Ringen (12/13)
dadurch gekennzeichnet , daß mindestens eines der trichterförmigen Leitteile (14/15) durch einen Motor gesteuert axial verschiebbar ist.Gas turbine with a guide ring (4) and with a rotor blade ring (2) in a gas channel (7) and with a housing (17) as well as funnel-shaped guide parts (14/15) which are axially displaceable against rotation and act as carriers of an outer jacket of the gas channel (7) forming rings (12/13)
characterized in that at least one of the funnel-shaped guide parts (14/15) is axially displaceable controlled by a motor. Gasturbine nach Anspruch 1
dadurch gekennzeichnet, daß als Motor mehrere auf den Umfang des Leitteiles (14/15) verteilte hydraulische oder pneumatische Pressen dienen.Gas turbine according to claim 1
characterized in that several hydraulic or pneumatic presses distributed over the circumference of the guide part (14/15) serve as the motor. Gasturbine nach Anspruch 1 oder 2
dadurch gekennzeichnet, daß sich Kolben (24) der Pressen mit ihrem freien Ende an einer gehäusefesten, starren Rippe (18) abstützen.Gas turbine according to claim 1 or 2
characterized in that the free end of the piston (24) of the press is supported on a rigid rib (18) fixed to the housing. Gasturbine nach einem der Ansprüche 1 bis 3
dadurch gekennzeichnet, daß auf den Kolben (24) der Pressen gleitende Zylinder (25) von dem Leitteil (14/15) getragen sind.Gas turbine according to one of claims 1 to 3
characterized in that cylinders (25) sliding on the pistons (24) of the presses are carried by the guide part (14/15). Gasturbine nach einem der Ansprüche 1 bis 4
dadurch gekennzeichnet, daß das Leitteil (14/15) außer den Gaskanal (7) begrenzenden Ringen (12/13) mindestens einen Leitschaufelkranz (4) trägt.Gas turbine according to one of claims 1 to 4
characterized in that the guide part (14/15) carries at least one guide vane ring (4) in addition to the rings (12/13) delimiting the gas channel (7). Gasturbine nach einem der Ansprüche 1 bis 5
dadurch gekennzeichnet, daß sich eine flanschartig vom Leitteil (14/15) radial nach außen vorstehende Anschlagrippe (19) mit ihrem freien Ende an der steifen gehäusefesten Rippe (18) abstützt und durch die Pressen elastisch verformbar ist.Gas turbine according to one of claims 1 to 5
characterized in that a stop rib (19) projecting radially outward from the guide part (14/15) is supported with its free end on the rigid housing-fixed rib (18) and is elastically deformable by the presses. Gasturbine nach einem der Ansprüche 1 bis 6
dadurch gekennzeichnet, daß eine von den denselben Leitteil (14/15) beaufschlagenden Pressen gemeinsam erzeugbare Kraft mindestens um den Faktor 10 größer ist, als eine betriebsbedingt auf die Anschlagrippe (19) wirkende Axialkraft.Gas turbine according to one of claims 1 to 6
characterized in that a force which can be generated jointly by the presses acting on the same guide part (14/15) is greater by at least a factor of 10 than an axial force acting on the stop rib (19) due to operation. Gasturbine nach einem der Ansprüche 1 bis 7
dadurch gekennzeichnet, daß eine Rückstellkraft der elastisch verformten Anschlagrippe (19) größer ist, als die betriebsbedingt auf die Anschlagrippe (19) wirkende Axialkraft.Gas turbine according to one of claims 1 to 7
characterized in that a restoring force of the elastically deformed stop rib (19) is greater than the axial force acting on the stop rib (19) due to operation. Gasturbine nach einem der Ansprüche 1 bis 8
dadurch gekennzeichnet, daß die Rückstellkraft durch Verschieben des trichterförmigen Leitteils (14/15) einen Laufschaufelspitzenspalt vergrößert.Gas turbine according to one of claims 1 to 8
characterized in that the restoring force increases a blade tip gap by moving the funnel-shaped guide part (14/15). Gasturbine nach einem der Ansprüche 1 bis 9
dadurch gekennzeichnet, daß die flanschartige, elastisch verformbare Anschlagrippe (19) an ihrer Wurzel einen Endanschlag (Verstärkung 21) aufweist, der die elastische Verformung begrenzt.Gas turbine according to one of claims 1 to 9
characterized in that the flange-like, elastically deformable stop rib (19) has an end stop (reinforcement 21) at its root, which limits the elastic deformation. Gasturbine nach einem der Ansprüche 1 bis 10
dadurch gekennzeichnet, daß das Leitteil (14/15) sowohl axial vor, als auch axial hinter der Anschlagrippe (19) und der gehäusefesten Rippe (18) durch mehrere, über den Umfang des Leitteils (14) verteilte Axialführungen (Klotz 16) gegen Verkanten gesichert ist.Gas turbine according to one of claims 1 to 10
characterized in that the guide part (14/15) both axially in front of and axially behind the stop rib (19) and the fixed rib (18) by several axial guides (block 16) distributed over the circumference of the guide part (14) against tilting is secured. Gasturbine nach einem der Ansprüche 1 bis 11
dadurch gekennzeichnet, daß die Axialführungen (Klotz 16) vom Gehäuse (17) getragen sind.Gas turbine according to one of claims 1 to 11
characterized in that the axial guides (block 16) are carried by the housing (17).
EP01109198A 2001-04-12 2001-04-12 Gas turbine with axially movable shroud elements Expired - Lifetime EP1249577B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP01109198A EP1249577B1 (en) 2001-04-12 2001-04-12 Gas turbine with axially movable shroud elements
ES01109198T ES2286054T3 (en) 2001-04-12 2001-04-12 GAS TURBINE WITH AXIALLY DISPLACABLE HOUSING PIECES.
DE50112597T DE50112597D1 (en) 2001-04-12 2001-04-12 Gas turbine with axially movable housing parts
JP2002106196A JP4283488B2 (en) 2001-04-12 2002-04-09 gas turbine
US10/120,808 US6676372B2 (en) 2001-04-12 2002-04-11 Gas turbine with axially mutually displaceable guide parts
CNB02119078XA CN100400797C (en) 2001-04-12 2002-04-12 Combustion turbine with axial relative movel guide unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01109198A EP1249577B1 (en) 2001-04-12 2001-04-12 Gas turbine with axially movable shroud elements

Publications (2)

Publication Number Publication Date
EP1249577A1 true EP1249577A1 (en) 2002-10-16
EP1249577B1 EP1249577B1 (en) 2007-06-06

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ID=8177137

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01109198A Expired - Lifetime EP1249577B1 (en) 2001-04-12 2001-04-12 Gas turbine with axially movable shroud elements

Country Status (6)

Country Link
US (1) US6676372B2 (en)
EP (1) EP1249577B1 (en)
JP (1) JP4283488B2 (en)
CN (1) CN100400797C (en)
DE (1) DE50112597D1 (en)
ES (1) ES2286054T3 (en)

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EP1900907A2 (en) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Turbine blade tip gap reduction system for a turbine engine
EP1965035A1 (en) 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation of the axial gap between adjustable grills and the contour ring for hot gas expanders
WO2009074355A1 (en) * 2007-12-10 2009-06-18 Siemens Aktiengesellschaft Axial turbo machine having reduced gap leakage
WO2010108876A1 (en) 2009-03-26 2010-09-30 Siemens Aktiengesellschaft Axial turbomachine having an axially displaceable guide-blade carrier
DE102009023062A1 (en) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Gap control system, turbomachine and method for adjusting a running gap between a rotor and a casing of a turbomachine
DE102009037620A1 (en) * 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh flow machine
EP2339122A1 (en) * 2009-12-23 2011-06-29 Siemens Aktiengesellschaft Turbine with adjustable volume inlet chamber
DE102010045851A1 (en) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Turbo-machine e.g. turbine stage of gas turbine of aircraft engine, has housing control unit for displacement of housing portions against each other and/or bearing control unit for displacement of housing and rotor shaft against each other
EP3078815A1 (en) * 2015-04-09 2016-10-12 United Technologies Corporation Active clearance control for axial rotor systems

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EP1746256A1 (en) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Reduction of gap loss in turbomachines
DE102005048982A1 (en) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Apparatus and method for axially displacing a turbine rotor
US7909566B1 (en) 2006-04-20 2011-03-22 Florida Turbine Technologies, Inc. Rotor thrust balance activated tip clearance control system
US7549835B2 (en) * 2006-07-07 2009-06-23 Siemens Energy, Inc. Leakage flow control and seal wear minimization system for a turbine engine
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US8277177B2 (en) 2009-01-19 2012-10-02 Siemens Energy, Inc. Fluidic rim seal system for turbine engines
US20100196139A1 (en) * 2009-02-02 2010-08-05 Beeck Alexander R Leakage flow minimization system for a turbine engine
US8177476B2 (en) * 2009-03-25 2012-05-15 General Electric Company Method and apparatus for clearance control
US8177483B2 (en) * 2009-05-22 2012-05-15 General Electric Company Active casing alignment control system and method
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US9109608B2 (en) * 2011-12-15 2015-08-18 Siemens Energy, Inc. Compressor airfoil tip clearance optimization system
US9488062B2 (en) 2012-05-10 2016-11-08 General Electric Company Inner turbine shell axial movement
DE102012213016A1 (en) * 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Method for minimizing the gap between a rotor and a housing
CN105579669B (en) * 2013-09-27 2017-07-07 西门子股份公司 For the inner housing hub of gas turbine
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CN104389645A (en) * 2014-11-15 2015-03-04 哈尔滨广瀚燃气轮机有限公司 Sealing structure for novel turbine motor high-temperature thermal expansion compensation stator
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EP1520958A3 (en) * 2003-09-30 2012-10-17 General Electric Company Method and apparatus for turbomachine active clearance control
EP1520958A2 (en) * 2003-09-30 2005-04-06 General Electric Company Method and apparatus for turbomachine active clearance control
EP1900907A2 (en) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Turbine blade tip gap reduction system for a turbine engine
EP1900907A3 (en) * 2006-09-08 2009-12-16 Siemens Energy, Inc. Turbine blade tip gap reduction system for a turbine engine
EP1965035A1 (en) 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation of the axial gap between adjustable grills and the contour ring for hot gas expanders
CN101255804B (en) * 2007-03-02 2016-03-30 西门子公司 Fluid machine, especially hot gas expansion machine
WO2009074355A1 (en) * 2007-12-10 2009-06-18 Siemens Aktiengesellschaft Axial turbo machine having reduced gap leakage
WO2010108876A1 (en) 2009-03-26 2010-09-30 Siemens Aktiengesellschaft Axial turbomachine having an axially displaceable guide-blade carrier
DE102009023062A1 (en) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Gap control system, turbomachine and method for adjusting a running gap between a rotor and a casing of a turbomachine
US9068471B2 (en) 2009-05-28 2015-06-30 Mtu Aero Engines Gmbh Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine
DE102009037620A1 (en) * 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh flow machine
EP2339122A1 (en) * 2009-12-23 2011-06-29 Siemens Aktiengesellschaft Turbine with adjustable volume inlet chamber
DE102010045851A1 (en) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Turbo-machine e.g. turbine stage of gas turbine of aircraft engine, has housing control unit for displacement of housing portions against each other and/or bearing control unit for displacement of housing and rotor shaft against each other
EP3078815A1 (en) * 2015-04-09 2016-10-12 United Technologies Corporation Active clearance control for axial rotor systems
US10323536B2 (en) 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems

Also Published As

Publication number Publication date
CN1381670A (en) 2002-11-27
ES2286054T3 (en) 2007-12-01
US6676372B2 (en) 2004-01-13
JP2002327603A (en) 2002-11-15
CN100400797C (en) 2008-07-09
JP4283488B2 (en) 2009-06-24
US20020164246A1 (en) 2002-11-07
DE50112597D1 (en) 2007-07-19
EP1249577B1 (en) 2007-06-06

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