EP2206889A1 - Method of reducing tip clearance using a rotor displacement device and related gas turbine - Google Patents
Method of reducing tip clearance using a rotor displacement device and related gas turbine Download PDFInfo
- Publication number
- EP2206889A1 EP2206889A1 EP09000358A EP09000358A EP2206889A1 EP 2206889 A1 EP2206889 A1 EP 2206889A1 EP 09000358 A EP09000358 A EP 09000358A EP 09000358 A EP09000358 A EP 09000358A EP 2206889 A1 EP2206889 A1 EP 2206889A1
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- Prior art keywords
- turbine
- rotor
- gas turbine
- compressor
- displacement device
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/052—Axially shiftable rotors
Definitions
- the invention relates to a gas turbine with an axial compressor and an axial turbine, whose radial gaps are reduced, and a method for reducing the radial gaps in the gas turbine.
- An axial-flow gas turbine includes a compressor, a turbine, and a rotor having compressor blade rows in the compressor and turbine blade rows in the turbine. Between the compressor blade rows and the inner contour of the housing of the compressor, a radial gap is provided. In an analogous manner, a radial gap is also provided between the turbine blade rows and the inner contour of the housing of the turbine.
- the radial gaps lead to significant losses in the efficiency of the compressor and the turbine. In order to achieve the highest possible efficiency of the compressor and the turbine, it is desirable to keep the radial gaps as small as possible at all operating times.
- the radial gaps change over time.
- the radial gaps change when switching from part load operation to full load operation of the gas turbine.
- the compressor and turbine are designed such that the radial gaps are sufficiently large for all compressor blade rows and turbine blade rows for the operating case where the radial gaps are found to be smallest so that there is virtually no contact between the rotor blade rows and the inner contour of the housing comes. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this critical operating condition, which is associated with a significant loss of efficiency.
- the temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the compressor and the turbine, in particular the rotor, the compressor blade rows, the turbine blade rows, the compressor housing and the turbine housing.
- the temporal change of the radial gap is caused by the centrifugal force expansion of the blade rows, the transverse contraction of the rotor, a possible play in the thrust bearing of the rotor, in particular in connection with the reversal of axial thrust under appropriate operating conditions of the gas turbine, a possible ovalization of the housing due to montage charitableer Preload and uneven heating of the housing.
- the object of the invention is to provide a gas turbine with a high thermal efficiency.
- the gas turbine according to the invention comprises an axial compressor with a compressor housing inner contour tapering in the throughflow direction of the gas turbine, an axial turbine with a turbine housing inner contour widening in the throughflow direction, on which an axially displaceable turbine guide carrier is mounted, and a rotor with at least one compressor blade row and at least one turbine blade row and rotor displacement means for axially displacing the rotor and turbine vane support shifting means for axially displacing the turbine vane support, wherein the rotor displacement means and the turbine vane support displacement means are arranged such that when the rotor is shifted from a first position to a second position axially in the flow direction by means of the rotor displacement means TurbinenleitschaufelifverschiebeISS the turbine vane carrier is axially displaced in the flow direction from a third position to a fourth position, whereby the radial gaps are both between the compressor blade row and the compressor housing internal contour as well as the turbine blade row and the turbine housing inner contour are adapted
- the radial gaps in the compressor can be reduced with the rotor displacement device, wherein without actuation of the turbine guide plate carrier displacement device, the radial gaps in the turbine would be increased.
- the magnification caused by the rotor displacement device can be reversed and also the radial gaps in the turbine are set to smaller size.
- a hydraulically drivable drive is preferably provided on the turbine as the turbine vane carrier displacement device with which the turbine vane carrier is displaceable between the third position and the fourth position.
- the hydraulically driven drive preferably has a plurality of hydraulic cylinders, which are mounted distributed on the turbine over the circumference.
- the hydraulic cylinders can be operated for example by an externally generated pressure.
- the turbine vane carrier is suitably mounted to provide its axial displaceability.
- a pneumatically drivable drive is preferably provided as Turbinenleitschaufelaverschiebe highlighted with which the Turbinenleitschaufelani between the third position and the fourth position is displaceable.
- the pneumatically driven drive preferably has a pressure chamber which is integrated on the turbine guide vane carrier.
- the pressure chamber is preferably designed as a thrust balance piston.
- the pneumatically driven drive is preferably drivable with removed from the compressor compressed air.
- the rotor displacement device is preferably hydraulically operable.
- the inventive method for reducing radial gaps in the gas turbine comprises the steps of: providing a correspondingly formed gas turbine; Moving the rotor from the first position to the second position axially in the flow direction by means of the rotor displacement device; Axially displacing the turbine vane support in the flow direction by means of the turbine vane support displacement device so that the radial gaps are reduced between both the compressor blade row and the compressor housing inner contour and the turbine blade row and the turbine housing inner contour.
- the displacement of the rotor by means of the rotor displacement device and the displacement of the turbine guide vane carrier by means of the turbine vane carrier displacement device during stationary operation of the gas turbine is accomplished.
- FIG. 1 schematically, a gas turbine 1 a compressor 2, a combustion chamber 3 and a turbine 4.
- the gas turbine 1 is in operation in FIG. 1 flows through from left to right, so that the flow direction the gas turbine 1 in the 1 to 4 from left to right.
- the compressor 2 has a housing with a compressor housing inner contour 17, which tapers in the direction of flow.
- the turbine 4 has a housing with a turbine housing inner contour 18, which tapers counter to the direction of flow.
- the gas turbine 1 further comprises a rotor, not shown, on which compressor rotor blades 2 are provided with radially arranged compressor rotor blades, each having a compressor blade 5.
- turbine blade rows are attached to the rotor, which are formed by turbine blades, each having a turbine blade airfoil 6.
- Both the compressor blade 5 and the turbine blade 6 extend radially outward from the center, ie, rotor of the compressor 2 and the turbine 4, respectively, spaced from each other to form the compressor housing inner contour 17 and the turbine housing inner contour 18, respectively, forming a radial gap 19.
- the gas turbine 1 further comprises a rotor displacement device, with which the rotor in a rotor displacement direction 7 in 1 to 4 from left to right is axially displaceable.
- a rotor displacement device With which the rotor in a rotor displacement direction 7 in 1 to 4 from left to right is axially displaceable.
- both the compressor blade 5 and the turbine blade 6 is moved from a first position 8 to a second position 9, wherein the second position 9 with respect to the first position 8 in 1 to 4 is settled further to the right.
- the compressor housing inner contour 17 in FIG. 1 is formed tapering from left to right, the radial gap on the compressor blade 5 in the first position 8 is greater than in the second position 9.
- the radial gap on the turbine blade airfoil 6 is smaller in the first position 8 than in the second position 9.
- a turbine vane carrier 10 is provided in FIGS. 2 to 4 in the turbine 4, a turbine vane carrier 10 is provided.
- the turbine vane carrier 10 is mounted axially displaceable parallel to the rotor displacement direction 7, so that the turbine guide vane carrier 10 can be brought from a third position 12 to a fourth position 13.
- the third position 12 is located farther to the right than the fourth position 13.
- the third position 12 is tuned to the first position 8 such that, when the compressor blade 5 is in the first position 8, a corresponding radial gap suitable for operating the gas turbine 1 is set on the turbine blade 6.
- the fourth position 13 is selected such that when the rotor is displaced from the rotor shifting device into the rotor shifting direction 7 such that the compressor blade 5 is in the second position 9 on the turbine blade 6 in the second position 9 and the turbine blade carrier 10 in FIG the fourth position 13, a corresponding to the operation of the gas turbine 1 suitable radial gap is set.
- the gas turbine 1 has a turbine vane support displacement device 11.
- the turbine vane support displacement device 11 is set to operate the rotor displacement device such that, when the rotor displacement device is displaced in the rotor displacement direction 7, so that the compressor blade 5 is brought from the first position 8 to the second position 9, the turbine guide 10 of the Turbine vane support displacement device 11 is brought from the third position 12 to the fourth position 13.
- the turbine vane support displacement device 11 is formed as a hydraulic cylinder 14.
- the hydraulic cylinder 14 is arranged to be actuatable in the axial direction of the gas turbine 1, so that with the hydraulic cylinder 14 on the turbine blade carrier 10, an axial compressive force can be applied. Because of the turbine vane carrier 10 is slidably mounted parallel to the axial direction of the gas turbine 1, upon actuation of the hydraulic cylinder 14, the turbine vane carrier 10 can be axially displaced when the turbine blade carrier 10 is displaced from the hydraulic cylinder 14 from the third position 12 to the fourth position.
- the turbine vane support shifting device 11 may be shown in FIG. 4 pneumatically driven, for which purpose compressed air is branched off from the compressor 2, which applies an axial force to the turbine guide vane carrier 10 in a pressure chamber 16, which is coupled to the turbine guide vane carrier 10.
- the pressure chamber 16 is designed in principle like a thrust balance piston.
Abstract
Description
Die Erfindung betrifft eine Gasturbine mit einem Axialverdichter und einer Axialturbine, deren Radialspalte vermindert sind, und ein Verfahren zur Verminderung der Radialspalte in der Gasturbine.The invention relates to a gas turbine with an axial compressor and an axial turbine, whose radial gaps are reduced, and a method for reducing the radial gaps in the gas turbine.
Eine Gasturbine in Axialbauweise weist einen Verdichter, eine Turbine und einen Rotor auf, der in dem Verdichter Verdichterlaufschaufelreihen und in der Turbine Turbinenlaufschaufelreihen aufweist. Zwischen den Verdichterlaufschaufelreihen und der Innenkontur des Gehäuses des Verdichters ist ein Radialspalt vorgesehen. In analoger Weise ist zwischen den Turbinenlaufschaufelreihen und der Innenkontur des Gehäuses der Turbine ebenfalls ein Radialspalt vorgesehen. Die Radialspalte führen jedoch zu erheblichen Einbußen im Wirkungsgrad des Verdichters und der Turbine. Um einen möglichst hohen Wirkungsgrad des Verdichters und der Turbine zu erzielen ist es erstrebenswert, die Radialspalte zu allen Betriebszeitpunkten möglichst klein zu halten.An axial-flow gas turbine includes a compressor, a turbine, and a rotor having compressor blade rows in the compressor and turbine blade rows in the turbine. Between the compressor blade rows and the inner contour of the housing of the compressor, a radial gap is provided. In an analogous manner, a radial gap is also provided between the turbine blade rows and the inner contour of the housing of the turbine. However, the radial gaps lead to significant losses in the efficiency of the compressor and the turbine. In order to achieve the highest possible efficiency of the compressor and the turbine, it is desirable to keep the radial gaps as small as possible at all operating times.
Beim Anfahren und Abfahren der Gasturbine verändern sich jedoch die Radialspalte über die Zeit. Außerdem verändern sich die Radialspalte beim Wechsel vom Teillastbetrieb zum Volllastbetrieb der Gasturbine. Herkömmlich sind der Verdichter und die Turbine derart ausgelegt, dass die Radialspalte für alle Verdichterlaufschaufelreihen und alle Turbinenlaufschaufelreihen für den Betriebsfall, in dem sich die Radialspalte als am kleinsten einstellen, ausreichend groß dimensioniert sind, so dass es so gut wie zu keiner Berührung zwischen den Laufschaufelreihen und der Innenkontur des Gehäuses kommt. Dies hat zur Folge, dass im Dauerbetrieb der Gasturbine für diesen kritischen Betriebszustand unnötig große Radialspalte vorgehalten werden müssen, womit ein erheblicher Wirkungsgradverlust einhergeht.When starting and stopping the gas turbine, however, the radial gaps change over time. In addition, the radial gaps change when switching from part load operation to full load operation of the gas turbine. Conventionally, the compressor and turbine are designed such that the radial gaps are sufficiently large for all compressor blade rows and turbine blade rows for the operating case where the radial gaps are found to be smallest so that there is virtually no contact between the rotor blade rows and the inner contour of the housing comes. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this critical operating condition, which is associated with a significant loss of efficiency.
Die zeitliche Veränderung der Radialspalte ist die Folge von unterschiedlichem thermischem Trägheitsverhalten der einzelnen Komponenten des Verdichters und der Turbine, insbesondere des Rotors, der Verdichterlaufschaufelreihen, der Turbinenlaufschaufelreihen, des Verdichtergehäuses und des Turbinengehäuses. Außerdem wird die zeitliche Veränderung der Radialspalte verursacht von der Fliehkraftdehnung der Laufschaufelreihen, der Querkontraktion des Rotors, einem eventuellen Spiel im Axiallager des Rotors, insbesondere im Zusammenhang mit der Umkehr von Axialschub bei entsprechenden Betriebsbedingungen der Gasturbine, einer eventuell auftretenden Ovalisierung des Gehäuses infolge von montagebedingter Vorspannung und ungleichmäßiger Erwärmung des Gehäuses.The temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the compressor and the turbine, in particular the rotor, the compressor blade rows, the turbine blade rows, the compressor housing and the turbine housing. In addition, the temporal change of the radial gap is caused by the centrifugal force expansion of the blade rows, the transverse contraction of the rotor, a possible play in the thrust bearing of the rotor, in particular in connection with the reversal of axial thrust under appropriate operating conditions of the gas turbine, a possible ovalization of the housing due to montagebedingter Preload and uneven heating of the housing.
Aufgabe der Erfindung ist es eine Gasturbine mit einem hohen thermischen Wirkungsgrad zu schaffen.The object of the invention is to provide a gas turbine with a high thermal efficiency.
Die erfindungsgemäße Gasturbine weist einen Axialverdichter mit einer in die Durchströmungsrichtung der Gasturbine sich verjüngenden Verdichtergehäuseinnenkontur, eine Axialturbine mit einer in die Durchströmungsrichtung sich aufweitenden Turbinengehäuseinnenkontur, an der ein in Axialrichtung verschiebbar Turbinenleitschaufelträger angebaut ist, und einen Rotor mit mindestens einer Verdichterlaufschaufelreihe und mindestens einer Turbinenlaufschaufelreihe sowie eine Rotorverschiebeeinrichtung zum Axialverschieben des Rotors und eine Turbinenleitschaufelträgerverschiebeeinrichtung zum Axialverschieben des Turbinenleitschaufelträgers auf, wobei die Rotorverschiebeeinrichtung und die Turbinenleitschaufelträgerverschiebeeinrichtung derart eingerichtet sind, dass, wenn mittels der Rotorverschiebeeinrichtung der Rotor von einer ersten Position in eine zweite Position axial in die Durchströmungsrichtung verschoben ist, mittels der Turbinenleitschaufelträgerverschiebeeinrichtung der Turbinenleitschaufelträger axial in die Durchströmungsrichtung von einer dritten Position in eine vierte Position verschoben ist, wodurch die Radialspalte sowohl zwischen der Verdichterlaufschaufelreihe und der Verdichtergehäuseinnenkontur als auch der Turbinenlaufschaufelreihe und der Turbinengehäuseinnenkontur angepasst und vorzugsweise verringert sind.The gas turbine according to the invention comprises an axial compressor with a compressor housing inner contour tapering in the throughflow direction of the gas turbine, an axial turbine with a turbine housing inner contour widening in the throughflow direction, on which an axially displaceable turbine guide carrier is mounted, and a rotor with at least one compressor blade row and at least one turbine blade row and rotor displacement means for axially displacing the rotor and turbine vane support shifting means for axially displacing the turbine vane support, wherein the rotor displacement means and the turbine vane support displacement means are arranged such that when the rotor is shifted from a first position to a second position axially in the flow direction by means of the rotor displacement means Turbinenleitschaufelträgerverschiebeeinrichtung the turbine vane carrier is axially displaced in the flow direction from a third position to a fourth position, whereby the radial gaps are both between the compressor blade row and the compressor housing internal contour as well as the turbine blade row and the turbine housing inner contour are adapted and preferably reduced.
Dadurch können beim Betrieb der Gasturbine die Radialspalte im Verdichter mit der Rotorverschiebeeinrichtung verkleinert werden, wobei ohne Betätigung der Turbinenleitschaufelträgerverschiebeinrichtung die Radialspalte in der Turbine vergrößert werden würden. Dem entgegenwirkend wird die Turbinenleitschaufelträgerverschiebeeinrichtung betätigt, wodurch einerseits die Vergrößerung hervorgerufen durch die Rotorverschiebeeinrichtung rückgängig gemacht werden kann und außerdem die Radialspalte in der Turbine auf geringere Größe einstellbar sind.Thereby, during operation of the gas turbine, the radial gaps in the compressor can be reduced with the rotor displacement device, wherein without actuation of the turbine guide plate carrier displacement device, the radial gaps in the turbine would be increased. Counteracting the Turbinenleitschaufelträgerverschiebeinrichtung is actuated, whereby on the one hand, the magnification caused by the rotor displacement device can be reversed and also the radial gaps in the turbine are set to smaller size.
An der Turbine ist bevorzugt als die Turbinenleitschaufelträgerverschiebeeinrichtung ein hydraulisch antreibbarer Antrieb vorgesehen, mit dem der Turbinenleitschaufelträger zwischen der dritten Position und der vierten Position verschiebbar ist. Der hydraulisch antreibbare Antrieb weist bevorzugt eine Mehrzahl an Hydraulikzylindern auf, die an der Turbine über den Umfang verteilt angebracht sind. Die Hydraulikzylinder können beispielsweise durch einen extern erzeugten Druck betrieben werden. Der Turbinenleitschaufelträger ist zur Bereitstellung seiner axialen Verschiebbarkeit entsprechend geeignet gelagert.A hydraulically drivable drive is preferably provided on the turbine as the turbine vane carrier displacement device with which the turbine vane carrier is displaceable between the third position and the fourth position. The hydraulically driven drive preferably has a plurality of hydraulic cylinders, which are mounted distributed on the turbine over the circumference. The hydraulic cylinders can be operated for example by an externally generated pressure. The turbine vane carrier is suitably mounted to provide its axial displaceability.
Alternativ ist bevorzugt als Turbinenleitschaufelträgerverschiebeeinrichtung ein pneumatisch antreibbarer Antrieb vorgesehen, mit dem der Turbinenleitschaufelträger zwischen der dritten Position und der vierten Position verschiebbar ist. Der pneumatisch antreibbare Antrieb weist bevorzugt eine Druckkammer auf, die am Turbinenleitschaufelträger integriert ist. Die Druckkammer ist bevorzugt als ein Schubausgleichskolben ausgelegt. Der pneumatisch antreibbare Antrieb ist bevorzugt mit von dem Verdichter entnommener Druckluft antreibbar. Die Rotorverschiebeeinrichtung ist bevorzugt hydraulisch betreibbar.Alternatively, a pneumatically drivable drive is preferably provided as Turbinenleitschaufelträgerverschiebeeinrichtung with which the Turbinenleitschaufelträger between the third position and the fourth position is displaceable. The pneumatically driven drive preferably has a pressure chamber which is integrated on the turbine guide vane carrier. The pressure chamber is preferably designed as a thrust balance piston. The pneumatically driven drive is preferably drivable with removed from the compressor compressed air. The rotor displacement device is preferably hydraulically operable.
Das erfindungsgemäße Verfahren zur Verminderung von Radialspalten in der Gasturbine weist die Schritte auf: Bereitstellen einer entsprechend ausgebildeten Gasturbine; Verschieben des Rotors von der ersten Position in die zweite Position axial in Durchströmungsrichtung mittels der Rotorverschiebeeinrichtung; Verschieben des Turbinenleitschaufelträgers mittels der Turbinenleitschaufelträgerverschiebeeinrichtung axial in Durchströmungsrichtung, so dass die Radialspalte sowohl zwischen der Verdichterlaufschaufelreihe und der Verdichtergehäuseinnenkontur als auch der Turbinenlaufschaufelreihe und der Turbinengehäuseinnenkontur vermindert sind.The inventive method for reducing radial gaps in the gas turbine comprises the steps of: providing a correspondingly formed gas turbine; Moving the rotor from the first position to the second position axially in the flow direction by means of the rotor displacement device; Axially displacing the turbine vane support in the flow direction by means of the turbine vane support displacement device so that the radial gaps are reduced between both the compressor blade row and the compressor housing inner contour and the turbine blade row and the turbine housing inner contour.
Bevorzugt wird das Verschieben des Rotors mittels der Rotorverschiebeeinrichtung und das Verschieben des Turbinenleitschaufelträgers mittels der Turbinenleitschaufelträgerverschiebeeinrichtung beim stationären Betrieb der Gasturbine bewerkstelligt.Preferably, the displacement of the rotor by means of the rotor displacement device and the displacement of the turbine guide vane carrier by means of the turbine vane carrier displacement device during stationary operation of the gas turbine is accomplished.
Im Folgenden werden bevorzugte Ausführungsformen einer erfindungsgemäßen Gasturbine anhand der beigefügten schematischen Zeichnungen erläutert. Es zeigen:
-
FIG 1 einen schematischen Längsschnitt durch die Gasturbine, -
FIG 2 einen schematischen Längsschnitt durch eine erste erfindungsgemäße Ausführungsform der Turbine, -
FIG 3 einen schematischen Längsschnitt einer zweiten erfindungsgemäßen Ausführungsform der Turbine und -
FIG 4 einen schematischen Längsschnitt einer dritten erfindungsgemäßen Ausführungsform der Turbine.
-
FIG. 1 a schematic longitudinal section through the gas turbine, -
FIG. 2 FIG. 2 shows a schematic longitudinal section through a first embodiment of the turbine according to the invention, FIG. -
FIG. 3 a schematic longitudinal section of a second embodiment of the invention of the turbine and -
FIG. 4 a schematic longitudinal section of a third embodiment of the turbine according to the invention.
Wie es aus
Die Gasturbine 1 weist ferner eine Rotorverschiebeeinrichtung auf, mit der der Rotor in eine Rotorverschieberichtung 7 in
In
Zum Verschieben des Turbinenleitschaufelträgers 10 parallel zur Axialrichtung der Gasturbine 1 von der dritten Position 12 in die vierte Position 13 und zurück weist die Gasturbine 1 eine Turbinenleitschaufelträgerverschiebeeinrichtung 11 auf. Die Turbinenleitschaufelträgerverschiebeeinrichtung 11 ist auf den Betrieb der Rotorverschiebeeinrichtung derart eingestellt, dass, wenn von der Rotorverschiebeeinrichtung der Rotor in die Rotorverschieberichtung 7 verschoben ist, so dass das Verdichterlaufschaufelblatt 5 von der ersten Position 8 in die zweite Position 9 gebracht ist, der Turbinenleitschaufelträger 10 von der Turbinenleitschaufelträgerverschiebeeinrichtung 11 von der dritten Position 12 in die vierte Position 13 gebracht ist.For displacing the turbine vane support 10 parallel to the axial direction of the gas turbine 1 from the
Gemäß
Alternativ kann die Turbinenleitschaufelträgerverschiebeeinrichtung 11 gemäß
Claims (10)
wobei an der Turbine (4) als die Turbinenleitschaufelträgerverschiebeeinrichtung (11) ein hydraulisch antreibbarer Antrieb vorgesehen ist, mit dem der Turbinenleitschaufelträger (10) zwischen der dritten Position (12) und der vierten Position (13) verschiebbar ist.Gas turbine according to claim 1,
wherein the turbine (4) as the turbine vane support displacement means (11) is provided a hydraulically drivable drive, with which the turbine vane support (10) between the third position (12) and the fourth position (13) is displaceable.
wobei der hydraulisch antreibbare Antrieb eine Mehrzahl an Hydraulikzylindern (14) aufweist, die an der Turbine (4) über den Umfang verteilt angebracht sind.Gas turbine according to claim 2,
wherein the hydraulically drivable drive comprises a plurality of hydraulic cylinders (14) which are mounted distributed on the turbine (4) over the circumference.
wobei an der Turbine (4) als die Turbinenleitschaufelträgerverschiebeeinrichtung (11) ein pneumatisch antreibbarer Antrieb vorgesehen ist, mit dem der Turbinenleitschaufelträger (10) zwischen der dritten Position (12) und der vierten Position (13) verschiebbar ist.Gas turbine according to claim 1,
wherein the turbine (4) as the turbine vane support displacement means (11) is provided a pneumatically drivable drive, with which the turbine vane support (10) between the third position (12) and the fourth position (13) is displaceable.
wobei der pneumatisch antreibbare Antrieb eine Druckkammer (16) aufweist, die am Turbinenleitschaufelträger (10) integriert ist.Gas turbine according to claim 4,
wherein the pneumatically driven drive comprises a pressure chamber (16) integrated with the turbine vane support (10).
wobei die Druckkammer (16) als ein Schubausgleichskolben ausgelegt ist.Gas turbine according to claim 5,
wherein the pressure chamber (16) is designed as a thrust balance piston.
wobei der pneumatisch antreibbare Antrieb mit von dem Verdichter (2) entnommer Druckluft (15) antreibbar ist.Gas turbine according to claim 5 or 6,
wherein the pneumatically driven drive with the compressor (2) entnommer compressed air (15) is drivable.
wobei die Rotorverschiebeeinrichtung hydraulisch betriebbar ist.Gas turbine according to one of claims 1 to 7,
wherein the rotor displacement device is hydraulically operated.
wobei das Verschieben des Rotors mittels der Rotorverschiebeeinrichtung und das Verschieben des Turbinenleitschaufelträgers (10) mittels der Turbinenleitschaufelträgerverschiebeeinrichtung (11) beim stationären Betrieb der Gasturbine (1) bewerkstelligt wird.Method according to claim 9,
wherein the displacement of the rotor by means of the rotor displacement device and the displacement of the turbine guide vane carrier (10) by means of the turbine vane carrier displacement device (11) during stationary operation of the gas turbine (1) is accomplished.
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EP09000358A EP2206889A1 (en) | 2009-01-13 | 2009-01-13 | Method of reducing tip clearance using a rotor displacement device and related gas turbine |
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EP09000358A EP2206889A1 (en) | 2009-01-13 | 2009-01-13 | Method of reducing tip clearance using a rotor displacement device and related gas turbine |
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
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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 |
DE102011003841A1 (en) * | 2011-02-09 | 2012-08-09 | Siemens Aktiengesellschaft | Turbine with relatively adjustable rotor and turbine housing |
US20160160875A1 (en) * | 2013-08-26 | 2016-06-09 | United Technologies Corporation | Gas turbine engine with fan clearance control |
EP3203016A1 (en) * | 2016-02-04 | 2017-08-09 | United Technologies Corporation | Clearance control in a gas turbine engine by means of thrust balance vents |
CN113756883A (en) * | 2021-09-26 | 2021-12-07 | 中国联合重型燃气轮机技术有限公司 | Active control device and method for gas turbine blade top clearance |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
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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 |
DE102011003841A1 (en) * | 2011-02-09 | 2012-08-09 | Siemens Aktiengesellschaft | Turbine with relatively adjustable rotor and turbine housing |
US20160160875A1 (en) * | 2013-08-26 | 2016-06-09 | United Technologies Corporation | Gas turbine engine with fan clearance control |
EP3203016A1 (en) * | 2016-02-04 | 2017-08-09 | United Technologies Corporation | Clearance control in a gas turbine engine by means of thrust balance vents |
US10247029B2 (en) | 2016-02-04 | 2019-04-02 | United Technologies Corporation | Method for clearance control in a gas turbine engine |
CN113756883A (en) * | 2021-09-26 | 2021-12-07 | 中国联合重型燃气轮机技术有限公司 | Active control device and method for gas turbine blade top clearance |
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