EP1249577B1 - Gas turbine with axially movable shroud elements - Google Patents
Gas turbine with axially movable shroud elements Download PDFInfo
- Publication number
- EP1249577B1 EP1249577B1 EP01109198A EP01109198A EP1249577B1 EP 1249577 B1 EP1249577 B1 EP 1249577B1 EP 01109198 A EP01109198 A EP 01109198A EP 01109198 A EP01109198 A EP 01109198A EP 1249577 B1 EP1249577 B1 EP 1249577B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine according
- guide part
- rib
- presses
- 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.)
- Expired - Lifetime
Links
Images
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
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 secured therein against rotation axially mutually displaceable funnel-shaped guiding parts as a carrier of an outer shell of the gas channel forming rings.
- Gas turbines are often subjected to changing loads not only in their starting phase, but also in continuous operation. This results in unsteady operation, especially with regard to the temperatures assumed by the individual components. To avoid damage to the turbine, therefore, the individual components are usually clamped so that they can perform thermally induced dimensional changes unhindered.
- the outer channel wall is partially formed by a guide ring, which is opposite to the blade tips of blades and slidable for radial clearance adjustment of a drive in the axial direction.
- the guide ring concentrically enclosing the blade ring is arranged in an annular recess of the housing of the gas turbine, wherein the space structure surrounding the recess is rigidly fixed to adjacent housing parts.
- a multi-part stator blade carrier which is composed of radially movable segments, which are axially fixed by approaches.
- To move the segments slidable segment carrier are provided in the outer conical wall of the annular space parallel to the wall.
- the sliding surfaces of the segment carrier and their guides are each formed like a sawtooth and inclined relative to the displacement direction.
- a displacement of the segment carrier causes a radial movement of the segments, which is used to adjust the radial gaps of all turbine stages.
- the invention is based on the object to develop a gas turbine plant so that in her over a variety of operating conditions, an optimal blade tip gap is given, so that a basic requirement for achieving a good efficiency is guaranteed.
- a gas turbine of the type specified in which at least one of the funnel-shaped guide parts controlled by a motor is axially displaceable.
- a motor Suitably serve as a motor a plurality of distributed over the circumference of the guide part hydraulic presses.
- any other type of drives is content of this invention.
- the particular advantage of this arrangement is the possibility to actively set the blade tip gap by axial movement of the guide.
- the conicity of the funnel-shaped design of the guide member is advantageously utilized, because as a result of this conicity, any axial displacement thereof also causes a change in the blade tip gap to be considered substantially radially.
- rotor blade rings 2 are keyed with a plurality of blades 3.
- a gas flow 6 guided through vane rings 4 with a multiplicity of vanes 5 expands through a gas duct 7, thereby driving the rotor blades 3.
- the gas channel 7 has an annular cross-section and is connected at its pressure-side end with a hot gas chamber 8, is driven from the compressed and heated gas in the arrow direction to a gas outlet opening 9.
- a radially inner boundary of the gas channel 7 is formed by hubs 10 of the blade rings 2 keyed on the turbine shaft 1 and non-rotating hubs 11 of the guide blade rings 4 carried by the inner ends of the guide blades 5. Joints between the hubs 10 and the hubs 11 are closed by labyrinth seals.
- a radially outer boundary of the gas channel 7 has a funnel-shaped conical shape and is formed by rings 12 and 13.
- the rings 12 and 13 are supported by funnel-shaped guideways 14 and 15, the rings 12 facing the free ends of the blades 3, and the rings 13 holding the outer ends of the vanes 5 and thus supporting the vane ring 4 formed by them as a whole. Gaps between the rings 12 and 13 are closed by suitable sealing rings, not shown.
- the guide parts 14 and 15 are thick-walled, very stiff and mounted axially slidably on cross-sectionally preferably rectangular blocks 16.
- the blocks 16 are anchored in a housing 17 and each of the guide parts 14 and 15 engages at its two ends in each case a wreath of a plurality of blocks 16, so that tilting for the guide parts 14 and 15 is also excluded, such as radial movements.
- the housing 17 is, due to its shape and its wall thickness, as stiff as the conducting parts 14 and 15 and carries on its inside except the blocks 16 per guide member 14 and 15, a rigid rib 18.
- This rigid rib 18 is axially between the Wreaths of blocks 16 provided, which are associated with the same guide member 14 and 15, respectively.
- the rigid rib 18 is in particular practically not deformable in the axial direction.
- Each of the guide parts 14 and 15 carries a radially outwardly projecting, relatively thin-walled stop rib 19, which is supported on the hot gas chamber 8 facing side of the associated rigid rib 18 with a bead 20 carried by its free end.
- a reinforcement 21 is arranged, which is indeed also the rigid rib 18 faces, but shorter in the axial direction than the bead 20.
- the guide parts 14 and 15 are in their gas outlet opening 9 facing portion radially outwardly by a preferably trapezoidal in cross section stiffening rib 22 includes a radially oriented, the associated rigid rib 18 opposite abutment surface 23 has. Between the rigid ribs 18 and their respective opposite stop surface 23 are distributed uniformly on the circumference of the associated guide member 14 or 15 a plurality of hydraulic presses. Pistons 24 of these presses are supported 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 divided by membrane-like partitions 26 into chambers.
- the inventive arrangement now allows a targeted, active setting just the width of this gap. For this purpose, this width is measured by sensors, not shown. With a desired reduction of the gap width is then through the engine shown by the presses concerned Guiding 14 and / or 15 shifted in the direction of the gas outlet opening 9.
- the stopper rib 19 is resiliently clamped, so that it pushes back in a direction required in the opposite direction of the movement carrying them guide member 14 or 15 in the direction of the hot gas chamber 8.
- each of the same guide member 14 or 15 associated presses together reach an axial force which corresponds to something the 10 times an operationally exerted by the gas flow 6 to the relevant guide member 14 or 15 axial force. Both axial forces act in the direction of the gas outlet opening 9 and add up.
- the deformation energy absorbed by the stop rib 19 during its deformation is stored in the adjustment of a guide part 14 or 15 in the direction of the gas outlet opening 9 and serves in an opposite movement to generate a restoring force.
- This restoring force is greater in each position of the associated guide member 14 or 15, as the operationally from the gas flow 6 to this exerted axial force.
- the restoring force is about 2 to 3 times as large as the operational axial force.
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 secured therein against rotation axially mutually displaceable funnel-shaped guiding parts as a carrier of an outer shell of the gas channel forming rings.
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 subjected to changing loads not only in their starting phase, but also in continuous operation. This results in unsteady operation, especially with regard to the temperatures assumed by the individual components. To avoid damage to the turbine, therefore, the individual components are usually clamped so that they can perform thermally induced dimensional changes unhindered.
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.To minimize turbine losses due to cross flows over their blade tips, the smallest possible radial gaps between the blade tips and these opposing vanes must be maintained. Since both the blades and their rotor and vanes and their supports, as well as an all-connecting housing, expand and / or shrink differently in time with each load change, an optimum radial gap across the blade tips will only result in very few of any number of stationary operating conditions one. The operation of these gas turbines is therefore often with a non-optimized gap width and consequently with a non-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.By US-PS 4,177,004 a turbine design is known in which the blade tips themselves remove material from a guide surface opposite them, so that for this arrangement in the operating state in which the the approach of the blade tips to the fins is approached, the blade tip gap almost disappears. In any other operating state, however, the blade tip gap is again larger and thus less favorable even with this known arrangement.
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.In other previously known arrangements, it has indeed been possible by selecting suitable material pairings to keep the thermally induced relative movements of the components low for many operating conditions, but also there is that only at a certain stationary state, an optimal blade tip gap prevails. In any other condition, less favorable conditions occur again.
Außerdem ist aus der US 5,203,673 eine Gasturbine mit einem konischen Gaskanal bekannt, dessen äußere Kanalwand teilweise von einem Führungsring gebildet wird, welcher den Schaufelspitzen von Laufschaufeln gegenüberliegt und zur Radialspalteinstellung von einem Antrieb in Axialrichtung verschiebbar ist. Der den Laufschaufelring konzentrisch umgreifende Führungsring ist in einer ringförmigen Ausnehmung des Gehäuses der Gasturbine angeordnet, wobei die die Ausnehmung umgebende Raumstruktur starr an benachbarten Gehäuseteilen fixiert ist.Moreover, from US 5,203,673 a gas turbine with a conical gas channel is known, the outer channel wall is partially formed by a guide ring, which is opposite to the blade tips of blades and slidable for radial clearance adjustment of a drive in the axial direction. The guide ring concentrically enclosing the blade ring is arranged in an annular recess of the housing of the gas turbine, wherein the space structure surrounding the recess is rigidly fixed to adjacent housing parts.
Weiter ist aus der DE 1 426 818 ein mehrteiliger Leitschaufelträger bekannt, der sich aus radial bewegbaren Segmenten zusammensetzt, welche durch Ansätze axial festgelegt sind. Zur Bewegung der Segmente sind in der äußeren konischen Wand des Ringraums parallel zur Wand verschiebbare Segmentträger vorgesehen. Die Gleitflächen der Segmentträger und deren Führungen sind jeweils sägezahnartig und gegenüber der verschieberichtung geneigt ausgebildet. Hierdurch bedingt eine Verschiebung der Segmentträger eine Radialbewegung der Segmente, was zur Einstellung der Radialspalte aller Turbinenstufen genutzt wird.Further, from DE 1 426 818 a multi-part stator blade carrier is known, which is composed of radially movable segments, which are axially fixed by approaches. To move the segments slidable segment carrier are provided in the outer conical wall of the annular space parallel to the wall. The sliding surfaces of the segment carrier and their guides are each formed like a sawtooth and inclined relative to the displacement direction. As a result, a displacement of the segment carrier causes a radial movement of the segments, which is used to adjust the radial gaps of all turbine stages.
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 to develop a gas turbine plant so that in her over a variety of operating conditions, an optimal blade tip gap is given, so that a basic requirement for achieving a 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 object is achieved according to the invention for a gas turbine of the type specified, in which at least one of the funnel-shaped guide parts controlled by a motor is axially displaceable. Suitably serve as a motor a plurality of distributed over the circumference of the guide part hydraulic presses. However, any other type of drives is content of this invention. The particular advantage of this arrangement is the possibility to actively set the blade tip gap by axial movement of the guide. In the limitation of the active adjustability to axial movements, the conicity of the funnel-shaped design of the guide member is advantageously utilized, because as a result of this conicity, any axial displacement thereof also causes a change in the blade tip gap to be considered substantially radially.
Weitere zweckmäßige und vorteilhafte Ausführungen der erfindungsgemäßen Anordnung sind in den Ansprüchen 3 bis 12 angegeben.Further expedient and advantageous embodiments of the arrangement according to the invention are specified in
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 explained in more detail with reference to a drawing. The only Fig. This drawing shows a longitudinal section through a turbine between a Treibgasein- 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.On a turbine shaft 1, not shown,
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 connected at its pressure-side end with a
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 a funnel-shaped conical shape and is formed by
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
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.The
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
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
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.All of the
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 prevails, as with any load change to virtually all parts provided with reference numerals a thermally unstable state. The rates of change at the individual parts are very different, so that accordingly different thermal expansion and shrinkage occur at these parts. These different temperature changes thus lead to relative movements of the parts against each other, in particular, changes in the width of the gap between the
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 inventive arrangement now allows a targeted, active setting just the width of this gap. For this purpose, this width is measured by sensors, not shown. With a desired reduction of the gap width is then through the engine shown by the presses concerned
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 deformation energy absorbed by the
Claims (12)
- Gas turbine having a ring of stator blades (4) and a ring of rotor blades (2) in a gas duct (7), and having a casing (17) and funnel-like guide parts (14/15) which are located therein, are secured against rotation and are axially mutually displaceable, it being possible for at least one of the funnel-like guide parts (14/15) to be displaced axially under control by a motor, characterized in that the guide parts (14/15) are designed as carriers for rings (12/13) forming an outer jacket of the gas duct (7).
- Gas turbine according to claim 1, characterized in that the motor used is a plurality of hydraulic or pneumatic presses distributed over the circumference of the guide part (14/15).
- Gas turbine according to claim 1 or 2, characterized in that pistons (24) of the presses are supported with their free end on a rigid rib (18) fixed to the casing.
- 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).
- Gas turbine according to one of claims 1 to 4, characterized in that the guide part (14/15) carries at least one ring of stator blades (4), in addition to the rings (12/13) bounding the gas duct (7).
- 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) in the manner of a flange is supported with its free end on the rigid rib (18) fixed to the casing, and can be deformed elastically by the presses.
- Gas turbine according to one of claims 1 to 6, characterized in that a force that can be generated by presses acting jointly on the same guide part (14/15) is greater, at least by the factor 10, than an axial force induced by operation acting on the stop rib (19).
- 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 induced by operation acting on the stop rib (19).
- Gas turbine according to one of claims 1 to 8, characterized in that the restoring force enlarges a rotor blade tip gap by displacing the funnel-like guide part (14/15).
- Gas turbine according to one of claims 1 to 9, characterized in that the flange-like, elastically deformable stop rib (19) has at its root an end stop (reinforcement 21) which limits the elastic deformation.
- Gas turbine according to one of claims 1 to 10, characterized in that the guide part (14/15) is secured against tilting both axially in front of and axially behind the stop rib (19) and the rib (18) fixed to the casing by means of a plurality of axial guides (block 16) distributed over the circumference of the guide part (14).
- Gas turbine according to one of claims 1 to 11, characterized in that the axial guides (block 16) are borne by the casing (17).
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
| EP01109198A EP1249577B1 (en) | 2001-04-12 | 2001-04-12 | Gas turbine with axially movable shroud elements |
| 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 EP1249577A1 (en) | 2002-10-16 |
| EP1249577B1 true EP1249577B1 (en) | 2007-06-06 |
Family
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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9057281B2 (en) | 2009-03-26 | 2015-06-16 | Siemens Aktiengesellschaft | Axial turbomachine having an axially displaceable guide-blade carrier |
Families Citing this family (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7222488B2 (en) * | 2002-09-10 | 2007-05-29 | General Electric Company | Fabricated cowl for double annular combustor of a gas turbine engine |
| US7125223B2 (en) * | 2003-09-30 | 2006-10-24 | General Electric Company | Method and apparatus for turbomachine active clearance control |
| GB0411850D0 (en) * | 2004-05-27 | 2004-06-30 | Rolls Royce Plc | Spacing arrangement |
| US7234918B2 (en) * | 2004-12-16 | 2007-06-26 | Siemens Power Generation, Inc. | Gap control system for turbine engines |
| DE102005018716A1 (en) * | 2005-04-21 | 2006-10-26 | Priebe, Klaus-Peter, Dipl.-Ing. | Sealing gap control |
| 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 |
| US20080063513A1 (en) * | 2006-09-08 | 2008-03-13 | Siemens Power Generation, Inc. | Turbine blade tip gap reduction system for a turbine engine |
| EP1965035B1 (en) | 2007-03-02 | 2013-12-18 | Siemens Aktiengesellschaft | Minimisation of the axial gap for adjustable guide vanes and for a contour ring for hot gas expanders |
| FR2920469A1 (en) * | 2007-08-30 | 2009-03-06 | Snecma Sa | TURBOMACHINE VARIABLE CALIBRATION |
| WO2009074355A1 (en) * | 2007-12-10 | 2009-06-18 | Siemens Aktiengesellschaft | Axial turbo machine having reduced gap leakage |
| 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 |
| 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 |
| US8939715B2 (en) * | 2010-03-22 | 2015-01-27 | General Electric Company | Active tip clearance control for shrouded gas turbine blades and related method |
| 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 |
| 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 |
| WO2015044266A1 (en) * | 2013-09-27 | 2015-04-02 | Siemens Aktiengesellschaft | Inner housing hub for a gas turbine |
| JP6223774B2 (en) * | 2013-10-15 | 2017-11-01 | 三菱日立パワーシステムズ株式会社 | gas turbine |
| US9840932B2 (en) | 2014-10-06 | 2017-12-12 | General Electric Company | System and method for blade tip clearance control |
| 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 |
| US10323536B2 (en) * | 2015-04-09 | 2019-06-18 | United Technologies Corporation | Active clearance control for axial rotor systems |
| CN106837432B (en) * | 2015-12-03 | 2019-10-11 | 上海电气电站设备有限公司 | Steam turbine differential expansion control structure and control method |
| WO2018093429A1 (en) * | 2016-08-10 | 2018-05-24 | In2Rbo, Inc. | Multistage radial compressor and turbine |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1426818A1 (en) * | 1963-07-26 | 1969-03-13 | Licentia Gmbh | Device for the radial adjustment of segments of a ring of an axial turbine machine, in particular a gas turbine, which carries guide vanes and / or surrounds rotor blades |
| US3227418A (en) * | 1963-11-04 | 1966-01-04 | Gen Electric | Variable clearance seal |
| US3520635A (en) * | 1968-11-04 | 1970-07-14 | Avco Corp | Turbomachine shroud assembly |
| CH538046A (en) * | 1971-11-10 | 1973-06-15 | Bbc Brown Boveri & Cie | Device for setting the tip clearance on turbomachines |
| DE2165528A1 (en) * | 1971-12-30 | 1973-07-12 | Kloeckner Humboldt Deutz Ag | DEVICE FOR CREATING A SMALL GAP BETWEEN THE ROTATING SHOVELS AND THE WALL OF A FLOW MACHINE |
| US4177004A (en) | 1977-10-31 | 1979-12-04 | General Electric Company | Combined turbine shroud and vane support structure |
| GB2042646B (en) * | 1979-02-20 | 1982-09-22 | Rolls Royce | Rotor blade tip clearance control for gas turbine engine |
| EP0103260A3 (en) * | 1982-09-06 | 1984-09-26 | Hitachi, Ltd. | Clearance control for turbine blade tips |
| US5203673A (en) * | 1992-01-21 | 1993-04-20 | Westinghouse Electric Corp. | Tip clearance control apparatus for a turbo-machine blade |
| EP1243756A1 (en) * | 2001-03-23 | 2002-09-25 | Siemens Aktiengesellschaft | Turbine |
-
2001
- 2001-04-12 ES ES01109198T patent/ES2286054T3/en not_active Expired - Lifetime
- 2001-04-12 EP EP01109198A patent/EP1249577B1/en not_active Expired - Lifetime
- 2001-04-12 DE DE50112597T patent/DE50112597D1/en not_active Expired - Lifetime
-
2002
- 2002-04-09 JP JP2002106196A patent/JP4283488B2/en not_active Expired - Fee Related
- 2002-04-11 US US10/120,808 patent/US6676372B2/en not_active Expired - Lifetime
- 2002-04-12 CN CNB02119078XA patent/CN100400797C/en not_active Expired - Fee Related
Non-Patent Citations (1)
| Title |
|---|
| None * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9057281B2 (en) | 2009-03-26 | 2015-06-16 | Siemens Aktiengesellschaft | Axial turbomachine having an axially displaceable guide-blade carrier |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4283488B2 (en) | 2009-06-24 |
| EP1249577A1 (en) | 2002-10-16 |
| CN100400797C (en) | 2008-07-09 |
| US6676372B2 (en) | 2004-01-13 |
| US20020164246A1 (en) | 2002-11-07 |
| CN1381670A (en) | 2002-11-27 |
| ES2286054T3 (en) | 2007-12-01 |
| JP2002327603A (en) | 2002-11-15 |
| DE50112597D1 (en) | 2007-07-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1249577B1 (en) | Gas turbine with axially movable shroud elements | |
| EP1471211B1 (en) | Sealing arrangement between stator blades and rotor of a high pressure turbine | |
| DE859089C (en) | Bladed gyroscope through which a work equipment flows | |
| DE69926332T2 (en) | Brush seal for a turbo machine | |
| DE60318792T2 (en) | Bleed air housing for a compressor | |
| DE3226052A1 (en) | DECKBAND STRUCTURE FOR A GAS TURBINE ENGINE | |
| DE60319489T2 (en) | sealing arrangement | |
| DE3941174C2 (en) | Tip gap adjustment device for the turbine rotor blades of a gas turbine engine | |
| EP0568909B1 (en) | Rotating disc obturator for steam turbine | |
| DE102004023879B4 (en) | axial flow steam turbine | |
| EP2179143B1 (en) | Gap cooling between combustion chamber wall and turbine wall of a gas turbine installation | |
| CH645432A5 (en) | GAS TURBINE ENGINE. | |
| DE2915626A1 (en) | COOLING AIR LINE FOR A GAS TURBINE ENGINE | |
| DE102013108862A1 (en) | Seal design and active gap control strategy for turbomachinery | |
| EP2824282A1 (en) | Gas turbine with high pressure turbine cooling system | |
| DE2554563B2 (en) | Arrangement for the blade tip seal in gas turbines | |
| DE2943464A1 (en) | GASKET DEVICE FOR A GAS TURBINE ENGINE | |
| EP2239423A1 (en) | Axial turbomachine with passive blade tip gap control | |
| EP2379846B1 (en) | Guide vane support system for a turbomachine | |
| CH697962B1 (en) | Inner housing for a rotary machine, rotary machine and method for controlling a measure of a split ring in a rotary machine. | |
| DE102014219552A1 (en) | Guide vane adjusting a gas turbine | |
| DE2907748A1 (en) | DEVICE FOR MINIMIZING AND MAINTAINING THE SHOVEL TIP GAMES EXISTING WITH AXIAL TURBINES, IN PARTICULAR FOR GAS TURBINE ENGINES | |
| EP0984138B1 (en) | Turbomachine with shaft cooling | |
| DE69913880T2 (en) | poetry | |
| EP2324208B1 (en) | Turbine lead rotor holder for a gas 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 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
| AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
| 17P | Request for examination filed |
Effective date: 20021118 |
|
| AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT |
|
| 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): DE ES FR GB IT |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
| REF | Corresponds to: |
Ref document number: 50112597 Country of ref document: DE Date of ref document: 20070719 Kind code of ref document: P |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20070704 |
|
| ET | Fr: translation filed | ||
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2286054 Country of ref document: ES Kind code of ref document: T3 |
|
| 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 |
|
| 26N | No opposition filed |
Effective date: 20080307 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 17 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20170724 Year of fee payment: 17 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 18 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20180619 Year of fee payment: 18 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20180423 Year of fee payment: 18 Ref country code: FR Payment date: 20180412 Year of fee payment: 18 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20180410 Year of fee payment: 18 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20190912 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20180413 |
|
| REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 50112597 Country of ref document: DE |
|
| GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20190412 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190412 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20191101 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190430 |
|
| 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 NON-PAYMENT OF DUE FEES Effective date: 20190412 |