DE102005021446B3 - Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid - Google Patents
Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid Download PDFInfo
- Publication number
- DE102005021446B3 DE102005021446B3 DE102005021446A DE102005021446A DE102005021446B3 DE 102005021446 B3 DE102005021446 B3 DE 102005021446B3 DE 102005021446 A DE102005021446 A DE 102005021446A DE 102005021446 A DE102005021446 A DE 102005021446A DE 102005021446 B3 DE102005021446 B3 DE 102005021446B3
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- Prior art keywords
- gas turbine
- grid
- vane grille
- guide vane
- turbine according
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C19/00—Bearings with rolling contact, for exclusively rotary movement
- F16C19/50—Other types of ball or roller bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
- F01D25/164—Flexible supports; Vibration damping means associated with the bearing
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/03—Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
- F16C27/04—Ball or roller bearings, e.g. with resilient rolling bodies
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/80—Diagnostics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/90—Braking
- F05D2260/902—Braking using frictional mechanical forces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C19/00—Bearings with rolling contact, for exclusively rotary movement
- F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
- F16C19/34—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load
- F16C19/38—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung betrifft Gasturbinen, wie sie im stationären aber ggf. auch im mobilen Einsatz betrieben werden können.The The invention relates to gas turbines, as in stationary but possibly also be operated in mobile use.
Bei allen Gasturbinen entstehen mehr oder weniger ausgeprägte Inhomogenitäten im Niveau der Heißgastemperatur über dem Umfang am Brennkammeraustritt, die auch am Austritt aus der Turbine noch festgestellt werden. Sie sind besonders ausgeprägt bei Gasturbinen mit Einzelbrennkammern, betreffen aber auch Gasturbinen mit Ringbrennkammern.at All gas turbines generate more or less pronounced inhomogeneities in the level the hot gas temperature above that Extent at the combustion chamber exit, which also at the exit from the turbine still be determined. They are particularly pronounced in gas turbines with single combustion chambers, but also relate to gas turbines with annular combustion chambers.
Üblicherweise sind Leitschaufelgitter vor Laufschaufelgittern stationär angeordnet. Dabei sind die Leitschaufelgitter der Heißgasströmung aus Brennkammern ausgesetzt und in Folge der Temperaturdifferenzen über dem Umfang der Heißgasströmung treten an einzelnen Positionen an Leitschaufeln unterschiedliche Tem peraturen auf.Usually Leitschaufelgitter are arranged stationary before blade lattices. The guide vanes are exposed to the hot gas flow from combustion chambers and due to the temperature differences occur over the circumference of the hot gas flow different temperatures at individual positions on vanes on.
Auch mit üblicherweise eingesetzten Mitteln zur Kühlung von Leitschaufelgittern und Beschichtungen kann keine ausreichende Kompensation der unterschiedlichen Temperaturen an unterschiedlichen Positionen von Leitschaufelgittern erreicht werden.Also with usually used means for cooling of vane grids and coatings can not provide sufficient Compensation of the different temperatures at different Positions of vane grids are achieved.
Da das Heißgas, das aus Brennkammern austritt, Temperaturen von ca. 1000 °C und darüber hinaus aufweisen kann, sind die einzelnen Elemente von Leitschaufelgittern thermisch sehr hoch beansprucht, so dass sie eine entsprechend begrenzte Lebensdauer erreichen und dementsprechend nach einer bestimmten Betriebszeit ausgetauscht werden müssen.There the hot gas, which comes out of combustion chambers, temperatures of about 1000 ° C and beyond may be the individual elements of vane grids thermally highly stressed, so they have a correspondingly limited life reach and accordingly after a certain operating time need to be replaced.
So sind die Leitschaufeln aus hochtemperaturfesten Werkstoffen hergestellt, die dementsprechende Kosten verursachen.So the vanes are made of high temperature resistant materials, which cause corresponding costs.
Da auch der Austausch einzelner Leitschaufeln oder vollständiger Leitschaufelgitter aufwendig ist, müssen Stillstandszeiten in Kauf genommen werden, die die Verfügbarkeit einer Gasturbine negativ beeinflussen.There also the replacement of individual vanes or complete vane grille is expensive, must Downtime can be accepted, the availability negatively affect a gas turbine.
Bisher werden lediglich punktuelle Temperaturmessungen mit unterschiedlicher Messstellendichte über dem Umfang am Gasturbinenaustritt oder an den hinteren Gasturbinenstufen durchgeführt, mit denen nur näherungsweise die reale ungleichförmige Temperaturverteilung im Arbeitsfluid vor Turbineneintritt bestimmbar ist. Damit können thermische Ungleichbeanspruchungen insbesondere in den vorderen Laufschaufelgittern nur in begrenztem Maße erkannt, aber unter Betriebsbedingungen nicht beseitigt werden.So far are only punctual temperature measurements with different Measuring point density over the circumference at the gas turbine outlet or at the rear gas turbine stages carried out, with those only approximately the real uneven temperature distribution can be determined in the working fluid before turbine entry. This can be thermal Unequal stresses, especially in the front blade lattices only to a limited extent detected, but not eliminated under operating conditions.
Eine direkte Bestimmung der Heißgastemperaturen am Austritt von Brennkammern ist nur in sehr begrenztem Maß möglich. Damit können thermische Ungleichbeanspruchungen zwar erkannt, aber nicht beseitigt werden.A direct determination of the hot gas temperatures at the outlet of combustion chambers is possible only to a very limited extent. In order to can thermal unequal stresses recognized, but not eliminated become.
Die
ungleichförmige
Temperaturverteilung im Heißgas
vor Turbineneintritt, die von Bauart, Betrieb und Zustand der Brennkammersektion
und des zugehörigen
Brennstoff-Verteilungssystems abhängig ist, kann nicht vermieden
werden. Mit Anpassung der Schaufelkühlung und wärmedämmenden Schaufelbeschichtungen
je nach Umfangsposition gelingt es nur zum Teil, die thermische
Ungleichbeanspruchung der Leitschaufeln (
Bereits eine geringfügige Erhöhung der Werkstofftemperatur führt zu einer deutlichen Verkürzung der Lebensdauer der Leitschaufelgitter und/oder ihrer Elemente.Already a minor one increase the material temperature leads to a significant shortening the lifetime of the vane grille and / or its elements.
Es ist daher Aufgabe der Erfindung, die von der thermischen Beanspruchung abhängende Lebensdauer von Leitschaufelgittern und ihren Elementen durch Reduzierung des Einflusses lokaler Heißgastemperaturunterschiede zu vergleichmäßigen.It is therefore an object of the invention, by the thermal stress abhängende Life of vane grates and their elements by reduction the influence of local hot gas temperature differences to equalize.
Erfindungsgemäß wird diese Aufgabe mit einer Gasturbine, die die Merkmale des Anspruchs 1 aufweist, gelöst. Vorteilhafte Ausgestaltungsformen und Weiterbildungen der Erfindung können mit den in den untergeordneten Ansprüchen bezeichneten Merkmalen erreicht werden.According to the invention this Task with a gas turbine having the features of claim 1, solved. Advantageous embodiments and developments of the invention can having the features indicated in the subordinate claims be achieved.
Die erfindungsgemäße Gasturbine ist dabei so ausgebildet, dass zwischen dem Brennkammeraustritt mindes tens einer Brennkammer und einem Laufschaufelgitter ein Leitschaufelgitter angeordnet ist, das mit Leitschaufeln bestückt ist, angeordnet und um die Rotationsachse der Gasturbine drehbar gelagert ist.The Gas turbine according to the invention is designed so that between the combustion chamber exit At least one combustion chamber and a blade grid a vane grille is arranged, which is equipped with vanes, arranged and order the axis of rotation of the gas turbine is rotatably mounted.
Die Rotation eines so drehbar angeordneten Leitschaufelgitters kann mittels der auf die einzelnen Leitschaufeln des Leitschaufelgitters auftreffenden Heißgasströmung aus der Brennkammer, also ohne einen zusätzlichen Antrieb erreicht werden.The Rotation of such a rotatably arranged Leitschaufelgitters can by means of the individual vanes of the vane grille impinging hot gas flow out the combustion chamber, so without an additional drive can be achieved.
Erfindungsgemäß soll dabei die jeweilige Drehzahl eines drehbar angeordneten Leitschaufelgitters auf maximal 10 Umdrehungen, bevorzugt auf eine, oder darunter liegende Drehzahl begrenzt werden.According to the invention is intended the respective speed of a rotatably arranged guide vane grille to a maximum of 10 revolutions, preferably to one or less Speed be limited.
Eine solche Drehzahl reicht ohne Weiteres aus, um eine Vergleichmäßigung der lokalen Temperaturverteilung an einem Leitschaufelgitter zu erreichen.Such a speed is readily sufficient to achieve homogenization of the local temperature distribution on a vane grille chen.
Eine Beeinträchtigung der Anströmung der Heißgasströmung, ausgehend von den Leitschaufeln eines auf diese Weise rotierenden Leitschaufelgitters auf ein in Strömungsrichtung nachfolgendes Laufschaufelgitter konnte nicht festgestellt werden.A impairment the flow the hot gas flow, starting from the vanes of a rotating vane grille in this way one in the flow direction Subsequent blade lattice could not be determined.
Die
Lösung
hebt sich dabei auch von an sich bekannten rotierenden Leitschaufelgittern,
wie sie in Verdichtterstufen von Gasturbinen eingesetzt werden und
in
Die erfindungsgemäß zu begrenzende Drehzahl eines ro tierenden Leitschaufelgitters kann mittels einer zusätzlichen Einrichtung, die am rotierenden Leitschaufelgitter angreift, erreicht werden.The to be limited according to the invention The speed of a rotating vane grille can be determined by means of a additional Means, which acts on the rotating vane grille reached become.
Dabei kann es sich bevorzugt um eine über ein Getriebe an das Leitschaufelgitter gekoppelte Bremse handeln.there it may preferably be one over one Transmission act on the vane grille coupled brake.
Das entsprechende Getriebe kann beispielsweise mit Schnecken- und/oder Kegelrädern ausgebildet sein.The appropriate gear can, for example, with screw and / or bevel gears be educated.
Es besteht aber auch die Möglichkeit, mehr als eine solche Einrichtung zur Begrenzung der jeweiligen Drehzahl eines rotierenden Leitschaufelgitters vorzusehen.It but it is also possible more than one such device for limiting the respective speed to provide a rotating vane grille.
An einer Gasturbine sollte bevorzugt zumindest das Leitschaufelgitter der ersten Stufe einer Gasturbine, also das Leitschaufelgitter, das einer Brennkammer am Nächsten angeordnet ist, um die Rotationsachse der Gasturbine drehbar sein.At a gas turbine should preferably at least the vane grille the first stage of a gas turbine, ie the vane grille, the closest to a combustion chamber is arranged to be rotatable about the axis of rotation of the gas turbine.
Die Lagerung von drehbar ausgebildeten Leitschaufelgittern sollte bevorzugt mittels Wälzlagern, besonders bevorzugt mittels Rollenlagern realisiert sein. Dabei können Vorkehrungen getroffen werden, um Wärmeausdehnungen zu kompensieren und eine Blockierung der Drehbewegung zu vermeiden.The Storage of rotatable vane grids should be preferred by rolling bearings, be particularly preferably realized by means of roller bearings. there can Precautions are taken to compensate for thermal expansion and to avoid blocking the rotation.
Eine Lagerung eines rotierenden Leitschaufelgitters kann dabei innerhalb von zwei Halbringelementen, die die Lagerung in axialer Richtung beidseitig einschließen, angeordnet sein.A Storage of a rotating vane grille can be within of two half-ring elements, which support the storage in the axial direction enclose on both sides, be arranged.
Mittels der Halbringelemente oder auch bei einem anders ausgebildeten konstruktivem Aufbau ist es vor teilhaft einen umlaufenden Ringraum vorzusehen, über den ein Kühlmedium, z. B. Kühlluft, zugeführt und an die einzelnen Leitschaufeln eines erfindungsgemäß ausgebildeten Leitschaufelgitters verteilt wird. Dabei sollten die Leitschaufeln als Hohlschaufeln ausgebildet sein. Dabei kann eine zentrale einzige Zuführung des Kühlmediums zu einem solchen Ringraum vorgesehen werden und trotzdem annähernd gleiche Kühleffekte in Folge der Drehung des Leitschaufelgitters an den einzelnen Leitschaufeln durch die Rotation des Leitschaufelgitters erreicht werden, was bei stationären Leitschaufelgittern nicht ohne Weiteres möglich ist.through the half-ring elements or even in a differently designed constructive Structure is before geous to provide a circumferential annulus over the a cooling medium, z. B. cooling air, supplied and to the individual guide vanes of an inventively designed Leitschaufelgitters is distributed. It should be the vanes be designed as hollow blades. It can be a central single feed of the cooling medium be provided for such an annulus and still approximately the same cooling effects due to the rotation of the vane grille on the individual vanes be achieved by the rotation of the vane grille what at inpatient Leitschaufelgittern is not readily possible.
Die einzelnen Leitschaufeln können in Axialnuten eindeutig fixiert werden. Das entspricht der Befestigung von Laufschaufeln, allerdings mit dem Unterschied, dass die Schaufelfüße dann am äußeren Umfang angeordnet sind. Ebenso ist aber auch die Positionierung in einer Umfangsnut möglich.The individual vanes can Clearly fixed in axial grooves. This corresponds to the attachment of blades, but with the difference that the blade feet then on the outer circumference are arranged. Likewise, however, is the positioning in one Circumferential groove possible.
An den einzelnen Leitschaufeln können an den radialen Stirnseiten Deckplatten ausgebildet sein, die im montierten Zustand eines Leitschaufelgitters ein geschlossenes Deckband bilden. Ein solches Deckband ist ähnlich ausgebildet, wie dies an Laufschaufeln der Fall ist, ihre Anordnung liegt jedoch im Gegensatz dazu am Innenradius. Diese Deckplatten können zur Reduzierung von Spaltströmen mit Dichtungselementen ausgeführt sein.At the individual vanes can be formed on the radial end faces cover plates in the mounted state of a vane grille a closed shroud form. Such a shroud is similar, as this on blades is the case, but their arrangement is in contrast to the inner radius. These cover plates can be used to reduce crevasse flows Performed sealing elements be.
Nachfolgend soll die Erfindung beispielhaft näher erläutert werden.following the invention will be explained in more detail by way of example.
Dabei zeigen:there demonstrate:
und
and
In
der schematischen Darstellung nach
Die
Teilschnittdarstellung nach
Innerhalb
von zwei Halbringelementen
Dabei
werden in jedem Lagerelement
Vorteilhaft
ist für
eine Temperaturkompensation eine Druckfeder
Des
Weiteren ist am Leitgitterring
Zwischen
den Halbringelementen
Innerhalb
der Halbringelemente
Die
Leitschaufeln
Claims (11)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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DE102005021446A DE102005021446B3 (en) | 2005-05-04 | 2005-05-04 | Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005021446A DE102005021446B3 (en) | 2005-05-04 | 2005-05-04 | Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid |
Publications (1)
Publication Number | Publication Date |
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DE102005021446B3 true DE102005021446B3 (en) | 2006-06-29 |
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DE102005021446A Expired - Fee Related DE102005021446B3 (en) | 2005-05-04 | 2005-05-04 | Gas turbine, has guide vane grid rotatably supported around rotational axis of gas turbine, and brake provided for reducing number of revolutions of guide vane grid lesser than ten revolution per minute and engaging at grid |
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DE (1) | DE102005021446B3 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007003470A1 (en) * | 2007-01-24 | 2008-07-31 | Schaeffler Kg | Bearing unit with adjustable friction torque to provide a braking function |
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US20210156257A1 (en) * | 2019-11-27 | 2021-05-27 | General Electric Company | Damper assemblies for rotating drum rotors of gas turbine engines |
US20210156279A1 (en) * | 2019-11-27 | 2021-05-27 | General Electric Company | Rotor support structures for rotating drum rotors of gas turbine engines |
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Cited By (13)
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DE102007003470A1 (en) * | 2007-01-24 | 2008-07-31 | Schaeffler Kg | Bearing unit with adjustable friction torque to provide a braking function |
EP2107219A1 (en) * | 2008-04-03 | 2009-10-07 | Siemens Aktiengesellschaft | Vane ring segment and vane ring carrier for a horizontally split turbo engine casing |
WO2009121653A1 (en) * | 2008-04-03 | 2009-10-08 | Siemens Aktiengesellschaft | Device for a horizontally split turbomachine housing, guide disc segment and guide blade carrier for a horizontally split turbomachine housing |
CN101983280A (en) * | 2008-04-03 | 2011-03-02 | 西门子公司 | Device for a horizontally split turbomachine housing, guide disc segment and guide blade carrier for a horizontally split turbomachine housing |
JP2011516776A (en) * | 2008-04-03 | 2011-05-26 | シーメンス アクチエンゲゼルシヤフト | Horizontally split turbine casing stationary blade ring installation device, horizontally split turbine casing stationary blade ring segment and stator blade holder |
CN101983280B (en) * | 2008-04-03 | 2014-03-05 | 西门子公司 | Device for horizontally split turbomachine housing, guide disc segment and guide blade carrier for horizontally split turbomachine housing |
US8708648B2 (en) | 2008-04-03 | 2014-04-29 | Siemens Aktiengesellschaft | Device for a horizontally split turbomachine housing, guide vane ring segment and guide vane carrier for a horizontally split turbomachine housing |
US20210156257A1 (en) * | 2019-11-27 | 2021-05-27 | General Electric Company | Damper assemblies for rotating drum rotors of gas turbine engines |
US20210156279A1 (en) * | 2019-11-27 | 2021-05-27 | General Electric Company | Rotor support structures for rotating drum rotors of gas turbine engines |
CN112855275A (en) * | 2019-11-27 | 2021-05-28 | 通用电气公司 | Damper assembly for a rotating drum rotor of a gas turbine engine |
US11274557B2 (en) * | 2019-11-27 | 2022-03-15 | General Electric Company | Damper assemblies for rotating drum rotors of gas turbine engines |
US11280219B2 (en) * | 2019-11-27 | 2022-03-22 | General Electric Company | Rotor support structures for rotating drum rotors of gas turbine engines |
CN112855275B (en) * | 2019-11-27 | 2023-12-22 | 通用电气公司 | Damper assembly for a rotating drum rotor of a gas turbine engine |
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