EP2302174A2 - Gas turbine shroud labyrinth seal - Google Patents
Gas turbine shroud labyrinth seal Download PDFInfo
- Publication number
- EP2302174A2 EP2302174A2 EP10007636A EP10007636A EP2302174A2 EP 2302174 A2 EP2302174 A2 EP 2302174A2 EP 10007636 A EP10007636 A EP 10007636A EP 10007636 A EP10007636 A EP 10007636A EP 2302174 A2 EP2302174 A2 EP 2302174A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- housing
- turbine according
- shroud
- sealing rib
- 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.)
- Withdrawn
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Definitions
- the invention relates to a gas turbine with a shroud labyrinth seal according to the features of the preamble of claim 1.
- the invention relates to an axial turbine of a gas turbine, in which at least one rotor provided with blades is provided, which has on its outer periphery, connecting the blade tips, a cover strip formed from segments.
- housing is to be understood according to the invention as meaning a non-rotating component which may also be formed as a tubular component which does not form a housing in the strict sense.
- the component designated according to the invention as a housing can consist of an arrangement of components, a ring or a part of the actual turbine housing.
- the turbine In a turbine of a gas turbine, work is taken from the gas flow exiting the combustion chamber to thereby generate a torque for driving a compressor.
- the turbine has a number of stationary blades and at least one rotor provided with a blade row. The number of these components may vary according to the invention.
- the rotor moves relative to the housing, wherein between the rotor and the housing, a gap is provided, which is required for free mobility of the rotor.
- a gap is provided, which is required for free mobility of the rotor.
- the leakage flow reduces the gas mass which flows through the rotor, so that the work taken becomes smaller.
- the flow caused by the gap results in an impairment of the actual flow through the turbine, as it has different angles and different local velocities. This results in a mixture of the two streams and in a reduction of the aerodynamic efficiency.
- the Leakage flow also leads to a deterioration of the flow of a subsequent stator blade row.
- FIG. 3 and 4 show a schematic representation of a blade root 7, which is part of a rotor 9. At the respective blade root 7, a blade 2 is arranged. The radially outer end regions of the blades 2 are connected by means of a shroud 3, which is formed substantially annular and is composed for example of individual segments.
- the shroud 3 is provided with a plurality of sealing ribs 5 extending substantially in the radial direction.
- the Fig. 3 and 4 each show three such sealing ribs. 5
- Fig. 3 a stepped housing contour is provided with housing stages 8, while according to Fig. 4 a conically widening housing cross-sectional shape (in the axial cross-section) is shown.
- the Fig. 3 and 4 thus show a meridional section of the turbine rotor and the housing.
- the annular ribs 5 may be purely radially aligned, it is also possible to tilt them in the axial direction, as in the Fig. 3 and 4 is shown. Furthermore, it is known from the prior art to provide varying numbers of such annular ribs 5.
- the invention has for its object to provide a gas turbine with shroud labyrinth seal, which avoids the disadvantages of the prior art with a simple design and simple, cost-effective manufacturability and ensures an optimized seal.
- At least one, at least over a part of the circumference substantially radially to the shroud extending sealing rib is formed on the housing, which extends at least partially into a space between the annular ribs.
- the sealing rib which according to the invention can be designed as a closed axial ring or segmented in the circumferential direction, thus constitutes a flow barrier, which additionally impedes the leakage flow. Thus, the flow mass of the leakage flow is reduced.
- the sealing ribs according to the invention can have a constant cross section or a varying cross section in the circumferential direction.
- the cross section may be rectangular with sharp edges, but it is also possible to provide a rounded cross section or to create a further leakage flow barrier by special cross sectional design.
- the cross section of the sealing ribs can furthermore be designed so that the sealing ribs are arranged inclined in the axial direction. It is possible to angle one or both sides, with respect to the axial direction, angularly.
- the radially arranged end face can also be chamfered or straight. It is also possible to provide a stepped cross section or a parallelogram-like cross section.
- the sealing ribs can either be formed integrally with the housing, but it is also possible to form them as a separate component and to connect to the housing, for example by ring segments or the like.
- the invention is applicable both in conically smooth, widening housing cross-sections, as well as in stepped housing cross-sections (each based on an axial section view).
- the leakage flow through the annular gap between the surface of the shroud and the housing is significantly hindered.
- the accelerated after the overflow of the annular ribs, jet-like flow is significantly hindered by the impact on the sealing ribs according to the invention and deflected with respect to the flow direction.
- kinetic energy of the leakage flow is destroyed, resulting in a reduced mass of the leakage flow.
- the leakage air flowing past the sealing ribs is hindered when hitting the next sealing rib of the housing or shroud in the axial direction, whereby flow energy is also dissipated in this case.
- Fig. 1 and 2 show, analogous to Fig. 3 and 4 , a housing 1, which may be provided with housing steps 8 ( Fig. 1 ) or with a smooth, conically widening surface.
- Fig. 1 and 2 show in dashed line the flow through the gap between the shroud 3 and the surface of the housing first
- sealing grooves 6 are arranged in the spaces between axially spaced annular ribs, which extend substantially in the radial direction. It is thus provided in each space a sealing rib 6.
- This is according to the embodiments of the Fig. 1 and 2 provided with a rectangular cross-section. However, it is also possible to vary the cross section, both in the circumferential direction and deviating from the rectangular cross section.
- the sealing ribs 6 are formed so that they hinder the flow, without coming into contact with the shroud 3 and / or the annular ribs 5. It is therefore not sealing elements, which form part of a squeal seal, but a defined distance between the sealing ribs 6 and the shroud 3 and / or the annular ribs 5 is provided.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
Description
Die Erfindung bezieht sich auf eine Gasturbine mit einer Deckband-Labyrinthdichtung gemäß den Merkmalen des Oberbegriffs des Anspruchs 1.The invention relates to a gas turbine with a shroud labyrinth seal according to the features of the preamble of claim 1.
Im Einzelnen bezieht sich die Erfindung auf eine Axialturbine einer Gasturbine, bei welcher zumindest ein mit Schaufeln versehener Rotor vorgesehen ist, welcher an seinem Außenumfang, die Schaufelspitzen verbindend, ein aus Segmenten gebildetes Deckband aufweist.In detail, the invention relates to an axial turbine of a gas turbine, in which at least one rotor provided with blades is provided, which has on its outer periphery, connecting the blade tips, a cover strip formed from segments.
Der Begriff "Gehäuse" ist erfindungsgemäßen so zu verstehen, dass er ein nicht rotierendes Bauelement bezeichnet, welches auch als rohrförmiges Bauteil ausgebildet sein kann, welches nicht im eigentlichen Sinn ein Gehäuse bildet. Das erfindungsgemäß als Gehäuse bezeichnete Bauteil kann aus einer Anordnung von Bauelementen, einem Ring oder einem Teil des eigentlichen Turbinengehäuses bestehen.The term "housing" is to be understood according to the invention as meaning a non-rotating component which may also be formed as a tubular component which does not form a housing in the strict sense. The component designated according to the invention as a housing can consist of an arrangement of components, a ring or a part of the actual turbine housing.
Bei einer Turbine einer Gasturbine wird Arbeit von der aus der Brennkammer austretenden Gasströmung entnommen, um auf diese Weise ein Drehmoment zum Antrieb eines Verdichters zu erzeugen. Hierzu weist die Turbine eine Reihe von stationären Schaufeln sowie zumindest einen mit einer Schaufelreihe versehenen Rotor auf. Die Anzahl dieser Bauelemente kann erfindungsgemäß variieren.In a turbine of a gas turbine, work is taken from the gas flow exiting the combustion chamber to thereby generate a torque for driving a compressor. For this purpose, the turbine has a number of stationary blades and at least one rotor provided with a blade row. The number of these components may vary according to the invention.
Der Rotor bewegt sich relativ zu dem Gehäuse, wobei zwischen dem Rotor und dem Gehäuse ein Spalt vorgesehen ist, der zur freien Bewegbarkeit des Rotors erforderlich ist. Durch diesen Spalt tritt stets eine gewisse Leckageströmung auf, welche insbesondere zwei negative Effekte mit sich bringt, die den Wirkungsgrad der Turbine herabsetzen. Zum einen reduziert die Leckageströmung die Gasmasse, welche durch den Rotor strömt, so dass die entnommene Arbeit geringer wird. Zum zweiten führt die durch den Spalt hervorgerufene Strömung zu einer Beeinträchtigung der eigentlichen Strömung durch die Turbine, da diese unterschiedliche Winkel und unterschiedliche lokale Geschwindigkeiten aufweist. Dies resultiert in einer Mischung der beiden Ströme und in einer Verminderung des aerodynamischen Wirkungsgrades. Die Leckageströmung führt auch zu einer Verschlechterung der Anströmung einer nachfolgenden Statorschaufelreihe.The rotor moves relative to the housing, wherein between the rotor and the housing, a gap is provided, which is required for free mobility of the rotor. Through this gap always occurs a certain leakage flow, which brings in particular two negative effects, which reduce the efficiency of the turbine. On the one hand, the leakage flow reduces the gas mass which flows through the rotor, so that the work taken becomes smaller. Secondly, the flow caused by the gap results in an impairment of the actual flow through the turbine, as it has different angles and different local velocities. This results in a mixture of the two streams and in a reduction of the aerodynamic efficiency. The Leakage flow also leads to a deterioration of the flow of a subsequent stator blade row.
Aus dem Stand der Technik ist es bekannt, geeignete Dichtungsmaßnahmen in Form einer Labyrinthdichtung vorzunehmen, um die Leckageströmung zu vermindern. Die
Das Deckband 3 ist mit mehreren sich im Wesentlichen in Radialrichtung erstreckenden Dichtungsrippen 5 versehen. Die
Die Dichtungsrippen 5 bilden zusammen mit der Wandung eines Gehäuses 1 eine Labyrinthdichtung 4. Die gestrichelten Linien der
Die Ringrippen 5 können rein radial ausgerichtet sein, es ist auch möglich, diese in Axialrichtung zu neigen, so wie dies in den
Aus den Darstellungen der
Der Erfindung liegt die Aufgabe zugrunde, eine Gasturbine mit Deckband-Labyrinthdichtung zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit die Nachteile des Standes der Technik vermeidet und eine optimierte Abdichtung gewährleistet.The invention has for its object to provide a gas turbine with shroud labyrinth seal, which avoids the disadvantages of the prior art with a simple design and simple, cost-effective manufacturability and ensures an optimized seal.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
Erfindungsgemäß ist somit vorgesehen, dass am Gehäuse zumindest eine, sich zumindest über einen Teil des Umfangs im Wesentlichen radial zum Deckband erstreckende Dichtungsrippe ausgebildet ist, welche sich zumindest zum Teil in einen Zwischenraum zwischen den Ringrippen erstreckt.According to the invention, it is thus provided that at least one, at least over a part of the circumference substantially radially to the shroud extending sealing rib is formed on the housing, which extends at least partially into a space between the annular ribs.
Die Dichtungsrippe, welche erfindungsgemäß als geschlossener Axialring oder in Umfangsrichtung segmentiert ausgebildet sein kann, stellt somit eine Strömungsbarriere dar, welche die Leckageströmung zusätzlich behindert. Somit wird die Strömungsmasse der Leckageströmung verringert.The sealing rib, which according to the invention can be designed as a closed axial ring or segmented in the circumferential direction, thus constitutes a flow barrier, which additionally impedes the leakage flow. Thus, the flow mass of the leakage flow is reduced.
Die erfindungsgemäßen Dichtungsrippen können in Umfangsrichtung einen gleichbleibenden Querschnitt oder einen variierenden Querschnitt aufweisen. Der Querschnitt kann beispielsweise rechteckig mit scharfen Kanten sein, es ist jedoch auch möglich, einen abgerundeten Querschnitt vorzusehen oder durch spezielle Querschnittsgestaltung eine weitere Leckageströmungsbarriere zu schaffen. Der Querschnitt der Dichtungsrippen kann weiterhin so ausgebildet sein, dass die Dichtungsrippen in Axialrichtung geneigt angeordnet sind. Es ist dabei möglich, eine oder beide Seiten, bezogen auf die Axialrichtung, winkelmäßig zu neigen. Auch die radial angeordnete Stirnseite kann abgeschrägt oder gerade ausgebildet sein. Es ist auch möglich, einen gestuften Querschnitt oder einen parallelogramm-artigen Querschnitt vorzusehen.The sealing ribs according to the invention can have a constant cross section or a varying cross section in the circumferential direction. For example, the cross section may be rectangular with sharp edges, but it is also possible to provide a rounded cross section or to create a further leakage flow barrier by special cross sectional design. The cross section of the sealing ribs can furthermore be designed so that the sealing ribs are arranged inclined in the axial direction. It is possible to angle one or both sides, with respect to the axial direction, angularly. The radially arranged end face can also be chamfered or straight. It is also possible to provide a stepped cross section or a parallelogram-like cross section.
Erfindungsgemäß können die Dichtungsrippen entweder einstückig mit dem Gehäuse ausgebildet sein, es ist jedoch auch möglich, diese als separates Bauteil auszubilden und mit dem Gehäuse zu verbinden, beispielsweise durch Ringsegmente oder Ähnliches.According to the invention, the sealing ribs can either be formed integrally with the housing, but it is also possible to form them as a separate component and to connect to the housing, for example by ring segments or the like.
Die Erfindung ist sowohl bei konisch glatten, sich erweiternden Gehäusequerschnitten anwendbar, als auch bei gestuften Gehäusequerschnitten (bezogen jeweils auf eine Axialschnittansicht).The invention is applicable both in conically smooth, widening housing cross-sections, as well as in stepped housing cross-sections (each based on an axial section view).
Erfindungsgemäß ergibt sich somit der Vorteil, dass die Leckageströmung durch den Ringspalt zwischen der Oberfläche des Deckbandes und dem Gehäuse erheblich behindert wird. Die nach der Überströmung der Ringrippen beschleunigte, jet-artige Strömung, wird durch das Auftreffen auf die erfindungsgemäßen Dichtungsrippen erheblich behindert und hinsichtlich der Strömungsrichtung umgelenkt. Hierdurch wird kinetische Energie der Leckageströmung vernichtet, so dass sich eine verringerte Masse der Leckageströmung ergibt. In analoger Weise wird die an den Dichtungsrippen vorbeiströmende Leckageluft beim Auftreffen auf die in Axialrichtung nächste Dichtungsrippe des Gehäuses oder des Deckbandes behindert, wobei auch hierbei Strömungsenergie abgebaut wird. Somit ergibt sich durch eine oder mehrere Abfolgen von Ringrippen und Dichtungsrippen eine erhebliche Behinderung der Leckageströmung, welche zu einer besseren Dichtwirkung führt. Hierdurch werden die Anfangs beschriebenen negativen Effekte verringert, so dass die Strömung durch die Schaufelbereiche ungestörter und in einem besseren Wirkungsgrad erfolgen kann. Hierdurch ergibt sich ein insgesamt höherer Wirkungsgrad der Turbine.According to the invention, there is thus the advantage that the leakage flow through the annular gap between the surface of the shroud and the housing is significantly hindered. The accelerated after the overflow of the annular ribs, jet-like flow is significantly hindered by the impact on the sealing ribs according to the invention and deflected with respect to the flow direction. As a result, kinetic energy of the leakage flow is destroyed, resulting in a reduced mass of the leakage flow. In an analogous manner, the leakage air flowing past the sealing ribs is hindered when hitting the next sealing rib of the housing or shroud in the axial direction, whereby flow energy is also dissipated in this case. This results in one or more sequences of annular ribs and sealing ribs a significant impediment to the leakage flow, which leads to a better sealing effect. As a result, the initially described negative effects are reduced, so that the flow through the blade areas can be done undisturbed and in a better efficiency. This results in an overall higher efficiency of the turbine.
Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:
- Fig. 1
- eine schematische Axial-Schnittansicht eines ersten Ausführungsbeispiels der Erfindung,
- Fig. 2
- eine Ansicht, analog
Fig. 1 , eines abgewandelten Ausführungsbeispiels der Erfindung, und - Fig. 3
- eine Abbildung zum Stand der Technik, analog
Fig. 2 .
- Fig. 1
- a schematic axial sectional view of a first embodiment of the invention,
- Fig. 2
- a view, analog
Fig. 1 , a modified embodiment of the invention, and - Fig. 3
- a picture of the prior art, analog
Fig. 2 ,
Bei den Ausführungsbeispielen sind gleiche Teile mit gleichen Bezugsziffern versehen.In the embodiments, the same parts are provided with the same reference numerals.
Die
Hinsichtlich der Beschreibung des Rotors 9, der Schaufeln 2, des Deckbands 3 und der Ringrippen 4 wird auf die Beschreibung der
Die
Erfindungsgemäß sind in den Zwischenräumen zwischen axial beabstandeten Ringrippen 5 Dichtungsrippen 6 angeordnet, welche sich im Wesentlichen in Radialrichtung erstrecken. Es ist somit in jedem Zwischenraum eine Dichtungsrippe 6 vorgesehen. Diese ist gemäß den Ausführungsbeispielen der
Aus den Darstellungen der
Erfindungsgemäß sind somit die Dichtungsrippen 6 so ausgebildet, dass sie die Strömung behindern, ohne in Kontakt mit dem Deckband 3 und/oder den Ringrippen 5 zu kommen. Es handelt sich somit nicht um Dichtungselemente, welche Teil einer Anstreifdichtung darstellen, vielmehr ist ein definierter Abstand zwischen den Dichtungsrippen 6 und dem Deckband 3 und/oder den Ringrippen 5 vorgesehen.According to the invention thus the sealing
- 11
- Gehäusecasing
- 22
- Schaufelshovel
- 33
- Deckbandshroud
- 44
- Labyrinthdichtunglabyrinth seal
- 55
- Ringrippe / Deckbandfinne / DeckbanddichtungsfinneRing rib / shroud fin / shroud seal fin
- 66
- Dichtungsrippe / Gehäusefinne / GehäusedichtungsfinneSealing rib / housing finger / housing sealing fin
- 77
- Schaufelfußblade
- 88th
- Gehäusestufehousing step
- 99
- Rotorrotor
Claims (13)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009042857A DE102009042857A1 (en) | 2009-09-24 | 2009-09-24 | Gas turbine with shroud labyrinth seal |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2302174A2 true EP2302174A2 (en) | 2011-03-30 |
EP2302174A3 EP2302174A3 (en) | 2014-01-22 |
Family
ID=42537784
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10007636.3A Withdrawn EP2302174A3 (en) | 2009-09-24 | 2010-07-22 | Gas turbine shroud labyrinth seal |
Country Status (3)
Country | Link |
---|---|
US (1) | US20110070074A1 (en) |
EP (1) | EP2302174A3 (en) |
DE (1) | DE102009042857A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US9416671B2 (en) | 2012-10-04 | 2016-08-16 | General Electric Company | Bimetallic turbine shroud and method of fabricating |
EP2650476B1 (en) * | 2012-04-13 | 2020-10-07 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
EP3822461A1 (en) * | 2019-11-15 | 2021-05-19 | MTU Aero Engines AG | Axial turbomachine sealing system |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5484990B2 (en) * | 2010-03-30 | 2014-05-07 | 三菱重工業株式会社 | Turbine |
US20120195742A1 (en) * | 2011-01-28 | 2012-08-02 | Jain Sanjeev Kumar | Turbine bucket for use in gas turbine engines and methods for fabricating the same |
US8807927B2 (en) | 2011-09-29 | 2014-08-19 | General Electric Company | Clearance flow control assembly having rail member |
US9109455B2 (en) | 2012-01-20 | 2015-08-18 | General Electric Company | Turbomachine blade tip shroud |
US8623708B1 (en) * | 2012-07-05 | 2014-01-07 | Stats Chippac Ltd. | Integrated circuit packaging system with grid-array mechanism and method of manufacture thereof |
WO2015061150A1 (en) * | 2013-10-21 | 2015-04-30 | United Technologies Corporation | Incident tolerant turbine vane gap flow discouragement |
JP6510915B2 (en) * | 2015-07-03 | 2019-05-08 | 株式会社神戸製鋼所 | Labyrinth seal |
CN107850082B (en) * | 2015-10-27 | 2019-11-05 | 三菱重工业株式会社 | Rotating machinery |
FR3055353B1 (en) * | 2016-08-25 | 2018-09-21 | Safran Aircraft Engines | LABYRINTH SEAL ASSEMBLY FOR TURBOMACHINE COMPRISING ABRADABLE AND INCLINED LECHETTES |
JP6706585B2 (en) * | 2017-02-23 | 2020-06-10 | 三菱重工業株式会社 | Axial rotating machine |
JP6917162B2 (en) | 2017-02-28 | 2021-08-11 | 三菱パワー株式会社 | Blades, rotor units, and rotating machines |
FR3065483B1 (en) * | 2017-04-24 | 2020-08-07 | Safran Aircraft Engines | SEALING DEVICE BETWEEN ROTOR AND TURBOMACHINE STATOR |
JP6856748B2 (en) * | 2017-06-12 | 2021-04-14 | 三菱パワー株式会社 | Axial rotating machine |
US20190072185A1 (en) | 2017-09-07 | 2019-03-07 | Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) | Labyrinth seal and labyrinth seal structure |
US10533610B1 (en) * | 2018-05-01 | 2020-01-14 | Florida Turbine Technologies, Inc. | Gas turbine engine fan stage with bearing cooling |
US11293295B2 (en) | 2019-09-13 | 2022-04-05 | Pratt & Whitney Canada Corp. | Labyrinth seal with angled fins |
CN113685234B (en) * | 2021-08-31 | 2022-08-09 | 北京航空航天大学 | Labyrinth sealing device based on hedging principle |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE533093A (en) * | 1953-11-12 | 1954-11-30 | ||
US4370094A (en) * | 1974-03-21 | 1983-01-25 | Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft | Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors |
DE2413655C3 (en) * | 1974-03-21 | 1978-05-03 | Maschinenfabrik Augsburg-Nuernberg Ag, 8500 Nuernberg | Device for dynamic stabilization of the rotor of a gas or steam turbine |
CH666326A5 (en) * | 1984-09-19 | 1988-07-15 | Bbc Brown Boveri & Cie | Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates |
US5735667A (en) * | 1996-05-06 | 1998-04-07 | Innovative Technology, L.L.C. | Method and apparatus for minimizing leakage in turbine seals |
DE59710621D1 (en) * | 1997-09-19 | 2003-09-25 | Alstom Switzerland Ltd | Gap sealing device |
EP1515000B1 (en) * | 2003-09-09 | 2016-03-09 | Alstom Technology Ltd | Blading of a turbomachine with contoured shrouds |
US6926495B2 (en) * | 2003-09-12 | 2005-08-09 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
US7255531B2 (en) * | 2003-12-17 | 2007-08-14 | Watson Cogeneration Company | Gas turbine tip shroud rails |
EP1557536A1 (en) * | 2004-01-22 | 2005-07-27 | Siemens Aktiengesellschaft | Gas turbine with axially displaceable rotor |
EP1905949A1 (en) * | 2006-09-20 | 2008-04-02 | Siemens Aktiengesellschaft | Cooling of a steam turbine component |
US7686568B2 (en) * | 2006-09-22 | 2010-03-30 | General Electric Company | Methods and apparatus for fabricating turbine engines |
JP2008169705A (en) * | 2007-01-09 | 2008-07-24 | Toshiba Corp | Steam turbine |
US8167547B2 (en) * | 2007-03-05 | 2012-05-01 | United Technologies Corporation | Gas turbine engine with canted pocket and canted knife edge seal |
JP4668976B2 (en) * | 2007-12-04 | 2011-04-13 | 株式会社日立製作所 | Steam turbine seal structure |
-
2009
- 2009-09-24 DE DE102009042857A patent/DE102009042857A1/en not_active Withdrawn
-
2010
- 2010-07-22 EP EP10007636.3A patent/EP2302174A3/en not_active Withdrawn
- 2010-09-14 US US12/881,655 patent/US20110070074A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
None |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2650476B1 (en) * | 2012-04-13 | 2020-10-07 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
US9416671B2 (en) | 2012-10-04 | 2016-08-16 | General Electric Company | Bimetallic turbine shroud and method of fabricating |
EP3822461A1 (en) * | 2019-11-15 | 2021-05-19 | MTU Aero Engines AG | Axial turbomachine sealing system |
Also Published As
Publication number | Publication date |
---|---|
DE102009042857A1 (en) | 2011-03-31 |
EP2302174A3 (en) | 2014-01-22 |
US20110070074A1 (en) | 2011-03-24 |
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