EP0852659B1 - Dichtelement zur dichtung eines spaltes sowie gasturbinenanlage - Google Patents
Dichtelement zur dichtung eines spaltes sowie gasturbinenanlage Download PDFInfo
- Publication number
- EP0852659B1 EP0852659B1 EP96942252A EP96942252A EP0852659B1 EP 0852659 B1 EP0852659 B1 EP 0852659B1 EP 96942252 A EP96942252 A EP 96942252A EP 96942252 A EP96942252 A EP 96942252A EP 0852659 B1 EP0852659 B1 EP 0852659B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing element
- sealing
- component
- gap
- gas turbine
- 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
- F01D11/005—Sealing means between non relatively rotating elements
Definitions
- the invention relates to a sealing element for sealing a Gap, which between two thermally movable against each other Components with a respective opposite one another Component groove can be formed, especially in a gas turbine plant and a gas turbine system with sealing elements.
- thermomechanical machines and chemical plants where different Fluids are used this may be necessary Keep fluids separate from one another within the systems.
- thermal combustion plants Flow areas of hot combustion gases from flow areas to separate low-temperature cooling gases.
- gas turbine plants with high turbine inlet temperatures, of, for example, over 1000 ° C thermal expansions occur of the individual components of the gas turbine system, so that to avoid high thermal stresses and cracking neighboring components partly through a gap are spaced from each other.
- Such columns can be connections between flow areas of hot gases with flow areas represent cold gases. The influx of cold Reduce gas in the flow area of hot gases and thereby the temperature in the flow area of the hot In order not to lower gases, it is advantageous to seal the gaps.
- each a gas turbine with an outer casing and a two-part Describing the inner housing is corresponding to the seal a gap between the two inner housings Sealing element with a cross section of an elongated C's specified. Is between the inner case and the outer case an annular gap is formed through which cooling fluid is passed. The hot gas flows to the drive inside the inner housing the gas turbine.
- a gas turbine system is described in US Pat. No. 4,537,024, in the components of a nozzle structure with axial and radial sealing elements are sealed.
- the sealing elements should prevent that flowing through the nozzle structure Hot gas reaches turbine areas outside the hot gas duct.
- a sealing element can have approximately the shape in cross section have a compressed eight.
- US Pat. No. 1,816,293 relates to the tight connection of two Superheated steam pipes. This vapor-tight connection is made by a tight screwing of two flanges.
- the Flanges each have an annular sealing surface on that is serrated.
- the teeth of the pressed together Sealing surfaces are deformed to have an increased sealing effect achieve.
- a sealing ring inserted, which is toothed on both sides and by which the same sealing effect is achieved.
- the object of the invention is a sealing element for sealing a gap that is thermally free between two against each other movable components can be formed, specify which an effective seal even in the event of thermal expansion of the components ensured.
- Another task lies in the specification a gas turbine plant in which a hot gas-carrying area area leading from a cooling fluid, in particular cooling air is effectively sealed.
- the first-mentioned object is achieved by a Sealing element for sealing a gap which between two thermally movable components with one respective mutually opposite component groove can be formed is solved, which is directed along a main line and in a cross section substantially perpendicular to the main line is directed along a center line, a first End and a second end opposite this and a has serrated between the ends of the central region is.
- the sealing element By serrating the sealing element, it is the one hand Adaptable shape of each component groove, so that it is sealing abuts in each component groove, and on the other hand deformable is, causing thermal expansion of the components can follow. Thus, the gap continues to be sealed and inadmissible thermal stresses avoided.
- the material of the sealing element is this for use at high temperatures of over 1000 ° C usable. It is therefore preferably suitable in a thermal Internal combustion engine, in particular a gas turbine system.
- the sealing element is preferably in at least at the ends deformable in a direction substantially orthogonal to the center line. This ensures that a thermal Expansion of the component groove in the direction of the center line of the sealing element, the ends of this thermal expansion can follow and thus the sealing element tight in the component grooves is present without inadmissibly high thermal voltages cause. This is an almost backlash-free connection between the components and the sealing element. Due to the deformability of the sealing element is also still ensures the mobility of the components against each other.
- the center line of the sealing element is preferably a center axis, so that the sealing element is essentially flat. It can be made from a substantially flat sheet with a predetermined Wall thickness simple and on an industrial scale with corrugated (serrated) surface can be produced.
- the sealing element preferably has sealing grooves that face each other the center line at an angle of 50 ° are inclined up to 90 °.
- the sealing grooves preferably run essentially towards the main line. Through the sealing grooves the sealing element receives a profile, which a deformability both orthogonally and in the direction the center line guaranteed. Especially with a non-orthogonal one Course of the sealing grooves, i.e. at an angle of inclination less than 90 ° from the center line, becomes deformable in the substantially orthogonal direction to the center line guaranteed.
- the Angle of inclination of the sealing grooves at the ends is smaller than in The central region. This ensures that the sealing element especially at the ends protruding into the component grooves can follow the thermal expansion of the components well, so a particularly good seal is achieved.
- the sealing element has a first surface and a second Surface that run between the ends and in Are opposite to each other with respect to the center line.
- the the first surface is preferably serrated and the second Surface smooth.
- the toothed surface preferably the cooling gas area and the smooth surface facing the hot gas area.
- the sealing element preferably tapers from the central region towards the respective ends. Because the ends in a respective Project component groove and thermal expansion of the components against each other the gap between them is reduced, the sealing element penetrates with increasing temperatures further into a respective component groove. Through the Tapering towards the ends becomes with a rising temperature achieved that the sealing element is even closer in the respective Component groove rests and thus the sealing of the Gap is further improved.
- the sealing element is preferably suitable for sealing a Gaps in a gas turbine plant with a hot gas Area and a cooling gas area to be sealed therefrom for cooling guide vanes of the gas turbine system. It is arranged so that it is on the one hand in a component groove of a first component, in particular a guide vane or a wall component of the gas turbine system, and on the other hand into a component groove adjacent to the first component second component, in particular a further guide vane or a wall component engages, wherein between the components a gap is formed.
- the main axis of the gas turbine system is alternately guide vanes and blades arranged, the guide vanes with their guide vane plates on the housing of the gas turbine system are attached and between the vane and the Housing an area for guiding cooling gas is provided.
- the cooling gas area borders each guide vane in the axial direction a wall component separating from the hot gas-carrying area the gas turbine plant.
- Between this and in particular the vane plate is formed a gap that is preferably sealed by the sealing element.
- In the circumferential direction of the gas turbine system are each guide vanes arranged and by a respective gap from each other spaced.
- the wall components are in the area of the blades arranged, also by a corresponding Gap are spaced apart.
- the column between neighboring ones Guide vanes and adjacent wall components are preferably sealed by a sealing element.
- a sealing element is preferably also suitable for sealing of a gap between two components, the component grooves have, which itself away from the gap into the components rejuvenate.
- the degree of rejuvenation, especially a corresponding one Bevel angle, is preferably the operating temperature adapted to the gas turbine plant.
- a gas turbine plant Object achieved in that between each other in the circumferential direction neighboring components spaced apart by a gap, which is a hot gas area from a cooling fluid area separate, a sealing element with a serrated (corrugated) surface is inserted into corresponding grooves of the components.
- the hot gas area becomes the normal during operation Gas turbine plant of hot gas (up to over 1000 ° C) and the Cooling fluid area is preferably flowed through by cooling air axially spaced components, vane plate and a wall component arranged opposite a rotor blade, by a hollow body, in particular dumbbell- or eight-shaped, sealing element sealed.
- FIG 1 is directed along a major axis 14
- Gas turbine system 22 shown. This shows in a housing 17 alternating guide vanes 12 and in the axial direction Blades 15 on.
- the guide vanes 12 are along one Axis 18 directed perpendicular to the main axis 14 and along the circumference of the gas turbine system 22 arranged to form a circle.
- the guide vanes 12 are via a respective guide vane plate 16 with the housing 17 of the gas turbine system 22 connected.
- Adjacent guide vanes are located along the circumference 12 spaced from each other by a respective gap 5 (see Fig. 2), which means that they are largely free thermally can expand.
- the guide vane plate 16 separates one the main axis 14 of the gas turbine system 22 formed hot gas area 11 from one between the guide vane plate 16 and the turbine housing 17 formed cooling gas region 8.
- Die Rotor blades 15 are along a respective main axis 19 stretched, which are also substantially orthogonal to Main axis 14 of the gas turbine system are.
- the blades 15 lie completely in the hot gas area 11.
- This hot gas area 11 is formed by a plurality of wall components 13 along the circumference of the gas turbine plant 22 from the cooling air area 8 separated.
- the wall components 13 are here in each case adjacent to the blades 15.
- the wall components 13 are connected to the turbine housing 17. The clarity for the sake of being only one guide blade 12, a moving blade 15 and a wall component 13 are shown.
- This gap 5 is through a Sealing element 1 sealed, thereby largely a flow of cooling gas from the cooling gas area 8 into the hot gas area 11 is prevented.
- the guide vane 12 provides here a first component 2a and the wall part 13 a second component 2b.
- the Cooling gas area 8 from the hot gas area 11 between adjacent ones Guide vanes 12 and wall components 13 and in the circumferential direction each have a seal between adjacent guide vanes 12 and accordingly between adjacent wall components 13th
- FIG. 2 shows a cross section along the circumference of the Gas turbine plant 22 and in particular on an enlarged scale two adjacent components 2a, 2b, which are separated by a gap 5 are spaced from each other.
- the components 2a, 2b can each two adjacent guide vanes 12, in particular guide vane plates 16, as well as two adjacent wall components 13.
- a component groove 3a or 3b is provided in the components 2a, 2b is in the circumferential direction.
- a component groove 3a or 3b is provided in the Component grooves 3a, 3b sealingly engage the gap 5 with a sealing element 1 with a toothed contour.
- the sealing element 1 is along a main line 21 directed and points in the illustrated Cross section perpendicular to the main line 21 a first End 6a, a second end 6b and an intermediate one Middle area 10.
- the sealing element 1 faces the cooling gas area 8 executes a plurality of sealing grooves 7 on, between adjacent sealing grooves 7 each a sealing tip (sealing tooth) 20 is formed, the sealing to the corresponding component groove 3a, 3b abuts. Because usually the pressure of the cooling gas is higher than the pressure of the hot gas The sealing element 1 is located in the hot gas-carrying region 11 with its smooth surface on the component grooves 3a, 3b, so that the sealing tips 20 from a mechanical load are largely relieving. This will wear the Sealing element 1 significantly reduced.
- the hot gas-carrying area 11 is the smooth one Surface 9b and the cooling gas area 8 the profiled surface 9a with sealing grooves 7 and sealing tips in between 20 facing.
- the sealing element 1 tapers from its central region 10 towards the respective ends 6a, 6b.
- the component groove 3a also tapers from the gap 5 in the component 2a, the guide vane plate 16 into it.
- the sealing grooves 7 have compared to a center line 4, which in particular a main axis 4a of the sealing element 1, one Angle of inclination ⁇ . This angle of inclination ⁇ is in the middle range at about 90 °, so that there the sealing grooves 7 in run essentially orthogonal to the center line 4.
- a sealing element 1 with sealing grooves 7 is preferably used for Sealing a gap between adjacent guide vanes 12 or adjacent wall components 13 on the circumference of the gas turbine system.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- FIG 1
- einen Ausschnitt eines Langsschnitts durch eine Gasturbinenanlage und
- FIG 2 bis 4
- einen Querschnitt durch ein Dichtelement in einer Gasturbinenanlage.
Claims (11)
- Dichtelement (1) zur Dichtung eines Spaltes (5), welcher zwischen zwei thermisch gegeneinander beweglichen Bauteilen (2a, 2b), die jeweils eine Bauteilnut (3a, 3b) aufweisen, bildbar ist, welches entlang einer Hauptlinie (21) gerichtet ist und in einem im wesentlichen zur Hauptlinie (21) senkrechten Querschnitt einen zwischen einem ersten Ende (6a) und einem zweiten Ende (6b) angeordneten Mittelbereich (10) aufweist,
dadurch gekennzeichnet, dass der Mittelbereich (10) eine erste Oberfläche (9a) hat, die gezahnt ist. - Dichtelement (1) nach Anspruch 1, mit einer zweiten Oberfläche (9b), die in Bezug auf die Mittellinie (4) der ersten Oberfläche (9b) gegenüberliegt und glatt ist.
- Dichtelement (1) nach Anspruch 1 oder 2, mit einer Mehrzahl von Dichtungsnuten (7), die jeweils gegenüber der Mittellinie (4) um einen Neigungswinkel (α) von 50° bis 90° geneigt sind.
- Dichtelement (1) nach Anspruch 3, bei der die Dichtungsnuten (7) zum Mittelbereich (10) hin aufsteigend geneigt sind.
- Dichtelement (1) nach Anspruch 3 oder 4, bei dem die Dichtungsnuten (7) an den Enden (6a, 6b) einen geringeren Neigungswinkel (α) als im Mittelbereich (10) aufweisen, welcher Neigungswinkel (α) im Mittelbereich insbesondere 90° beträgt.
- Dichtelement (1) nach einem der vorhergehenden Ansprüche, welches sich von dem Mittelbereich (10) zu den Enden (6a, 6b) hin verjüngt.
- Dichtelement (1) nach einem der vorhergehenden Ansprüche, in einer Gasturbinenanlage (22) mit einem Heißgasbereich (11) und einem hiervon abzudichtenden Kühlgasbereich (8) zur Kühlung von Leitschaufeln (12) der Gasturbinenanlage (22), welches in eine Bauteilnut (3a) eines ersten Bauteils (2a) und in eine Bauteilnut (3b) eines an das erste Bauteil (2a) angrenzenden zweiten Bauteils (2b), insbesondere einer Leitschaufel (12) oder eines Wandbauteils (13), eingreift, wobei zwischen den Bauteilen (2a, 2b) ein Spalt (5) gebildet ist.
- Dichtelement (1) nach Anspruch 7, bei dem das in die jeweilige Bauteilnut (3a, 3b) einzuführende Ende (6a, 6b) gegenüber der Bauteilnut (3a, 3b) ein geringes Übermaß aufweist.
- Dichtelement (1) nach Anspruch 7 oder 8, welches in eine Bauteilnut (3a, 3b) eingreift, die sich von dem Spalt (5) weg in das Bauteile (12, 13) hinein verjüngt.
- Dichtelement (1) nach Anspruch 7,8 oder 9, bei dem die erste Oberfläche (9a) dem Kühlgasbereich (8) zugewandt ist.
- Gasturbinenanlage (22) mit einem Heißgasbereich (11) und einem hiervon abzudichtenden Kühlgasbereich (8) zur Kühlung von Leitschaufeln (12), wobei die Bereiche (8,11) durch eine Mehrzahl in Umfangsrichtung und in axialer Richtung angeordneter Bauteile (2a,2b) voneinander getrennt sind und zumindest ein erstes Bauteil (2a) und ein zweites Bauteil (2b) in Umfangsrichtung durch einen Spalt (5) beabstandet sind und jeweils eine dem Spalt (5) zugewandte Bauteilnut (3a, 3b) aufweisen,
dadurch gekennzeichnet, dass in die Bauteilnut (3a, 3b) den Spalt dichtend ein gezahntes Dichtelement (1) angeordnet ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19536535 | 1995-09-29 | ||
DE19536535 | 1995-09-29 | ||
PCT/DE1996/001861 WO1997012125A2 (de) | 1995-09-29 | 1996-09-27 | Dichtelement zur dichtung eines spaltes sowie gasturbinenanlage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0852659A2 EP0852659A2 (de) | 1998-07-15 |
EP0852659B1 true EP0852659B1 (de) | 2002-04-03 |
Family
ID=7773719
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP96942252A Expired - Lifetime EP0852659B1 (de) | 1995-09-29 | 1996-09-27 | Dichtelement zur dichtung eines spaltes sowie gasturbinenanlage |
Country Status (6)
Country | Link |
---|---|
US (1) | US5975844A (de) |
EP (1) | EP0852659B1 (de) |
JP (1) | JP3898225B2 (de) |
DE (1) | DE59609029D1 (de) |
RU (1) | RU2162556C2 (de) |
WO (1) | WO1997012125A2 (de) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2407641A1 (de) | 2010-07-13 | 2012-01-18 | Siemens Aktiengesellschaft | Dichtelement zur Dichtung eines Spalts sowie Dichtungsanordnung |
WO2014146954A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spaltes |
DE102013205028A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur Dichtung eines Spaltes |
WO2014146866A1 (de) | 2013-03-20 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spaltes und zugehörige gasturbine |
EP2915959A1 (de) | 2014-03-07 | 2015-09-09 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile |
EP2915960A1 (de) | 2014-03-07 | 2015-09-09 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile |
EP3000983A1 (de) | 2014-09-29 | 2016-03-30 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile sowie Verfahren zum Montieren und Demontieren einer solchen |
EP4074941A1 (de) | 2021-04-13 | 2022-10-19 | Siemens Energy Global GmbH & Co. KG | Dichtungsstreifenelement und dichtungsanordnung mit diesem dichtungsstreifenelement |
EP4137670A1 (de) | 2021-08-19 | 2023-02-22 | Siemens Energy Global GmbH & Co. KG | Dichtungsvorrichtung mit verschiebbarem widerlager |
WO2023020748A1 (en) | 2021-08-19 | 2023-02-23 | Siemens Energy Global GmbH & Co. KG | Sealing device with displaceable abutment |
Families Citing this family (46)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998055736A1 (fr) * | 1997-06-04 | 1998-12-10 | Mitsubishi Heavy Industries, Ltd. | Structure d'etancheite montee entre les disques d'une turbine a gaz |
JP4502517B2 (ja) * | 1999-03-24 | 2010-07-14 | シーメンス アクチエンゲゼルシヤフト | 流体機械の案内羽根及び案内羽根リング |
EP1118806A1 (de) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand |
JP2002201913A (ja) * | 2001-01-09 | 2002-07-19 | Mitsubishi Heavy Ind Ltd | ガスタービンの分割壁およびシュラウド |
US6568692B2 (en) * | 2001-03-02 | 2003-05-27 | Honeywell International, Inc. | Low stress seal |
GB0108398D0 (en) * | 2001-04-04 | 2001-05-23 | Siemens Ag | Seal element for sealing a gap and combustion turbine having a seal element |
US7080513B2 (en) * | 2001-08-04 | 2006-07-25 | Siemens Aktiengesellschaft | Seal element for sealing a gap and combustion turbine having a seal element |
GB2385642B (en) * | 2001-12-22 | 2004-01-14 | Alstom | Membrane seals |
DE10209295B4 (de) | 2002-03-01 | 2010-12-09 | Alstom Technology Ltd. | Spaltdichtung bei einer Gasturbine |
US6883807B2 (en) | 2002-09-13 | 2005-04-26 | Seimens Westinghouse Power Corporation | Multidirectional turbine shim seal |
US6733234B2 (en) | 2002-09-13 | 2004-05-11 | Siemens Westinghouse Power Corporation | Biased wear resistant turbine seal assembly |
US7562880B2 (en) * | 2004-02-09 | 2009-07-21 | Siemens Energy, Inc. | Seal usable between thermally movable components |
JP4495481B2 (ja) * | 2004-02-18 | 2010-07-07 | イーグル・エンジニアリング・エアロスペース株式会社 | シール装置 |
DE102004016467A1 (de) * | 2004-03-31 | 2005-10-20 | Alstom Technology Ltd Baden | Spaltdichtung zum Abdichten eines Spalts zwischen zwei benachbarten Bauteilen |
US20050242526A1 (en) * | 2004-04-30 | 2005-11-03 | Stefan Dahlke | Hot gas seal |
US8714565B1 (en) | 2005-01-27 | 2014-05-06 | Parker-Hannifim Corporation | Seal |
EP1848904B1 (de) * | 2005-02-15 | 2009-01-14 | Alstom Technology Ltd | Dichtungselement zur verwendung in einer strömungsmaschine |
US7527472B2 (en) * | 2006-08-24 | 2009-05-05 | Siemens Energy, Inc. | Thermally sprayed conformal seal |
US8561438B2 (en) | 2006-12-08 | 2013-10-22 | Lg Electronics Inc. | Complex washing machine and controlling method for the same |
GB2449493B (en) * | 2007-05-25 | 2009-08-12 | Rolls Royce Plc | Vibration damper assembly |
US8206087B2 (en) | 2008-04-11 | 2012-06-26 | Siemens Energy, Inc. | Sealing arrangement for turbine engine having ceramic components |
US7824150B1 (en) * | 2009-05-15 | 2010-11-02 | Florida Turbine Technologies, Inc. | Multiple piece turbine airfoil |
US8322977B2 (en) * | 2009-07-22 | 2012-12-04 | Siemens Energy, Inc. | Seal structure for preventing leakage of gases across a gap between two components in a turbine engine |
US8585354B1 (en) * | 2010-01-19 | 2013-11-19 | Florida Turbine Technologies, Inc. | Turbine ring segment with riffle seal |
US9534500B2 (en) * | 2011-04-27 | 2017-01-03 | Pratt & Whitney Canada Corp. | Seal arrangement for segmented gas turbine engine components |
US8562000B2 (en) * | 2011-05-20 | 2013-10-22 | Siemens Energy, Inc. | Turbine combustion system transition piece side seals |
EP2538031A1 (de) * | 2011-06-22 | 2012-12-26 | Siemens Aktiengesellschaft | Rotor mit Dichtelement für eine stationäre Gasturbine |
US20130028713A1 (en) * | 2011-07-25 | 2013-01-31 | General Electric Company | Seal for turbomachine segments |
GB201117084D0 (en) * | 2011-10-05 | 2011-11-16 | Rolls Royce Plc | Strip seals |
DE102013205922B4 (de) | 2013-04-04 | 2016-09-29 | MTU Aero Engines AG | Vorrichtung und Verfahren zur Befestigung von Dichtungselementen |
US9581036B2 (en) | 2013-05-14 | 2017-02-28 | General Electric Company | Seal system including angular features for rotary machine components |
EP3025030B1 (de) | 2013-07-24 | 2021-04-21 | Raytheon Technologies Corporation | Rinnendichtung für gasturbinenmotor |
US9988923B2 (en) | 2013-08-29 | 2018-06-05 | United Technologies Corporation | Seal for gas turbine engine |
WO2015038305A2 (en) | 2013-09-16 | 2015-03-19 | United Technologies Corporation | Gas turbine engine with disk having periphery with protrusions |
WO2015069362A2 (en) | 2013-09-17 | 2015-05-14 | United Technologies Corporation | Gas turbine engine with seal having protrusions |
EP3080419B1 (de) * | 2013-12-12 | 2021-04-07 | Raytheon Technologies Corporation | Umwickelte dog-bone-dichtung |
EP3092372B1 (de) * | 2014-01-08 | 2019-06-19 | United Technologies Corporation | Klemmdichtung für strahltriebwerk-mittelturbinenrahmen |
US9719427B2 (en) * | 2014-01-21 | 2017-08-01 | Solar Turbines Incorporated | Turbine blade platform seal assembly validation |
US9416675B2 (en) * | 2014-01-27 | 2016-08-16 | General Electric Company | Sealing device for providing a seal in a turbomachine |
EP2907977A1 (de) * | 2014-02-14 | 2015-08-19 | Siemens Aktiengesellschaft | Heißgasbeaufschlagbares Bauteil für eine Gasturbine sowie Dichtungsanordnung mit einem derartigen Bauteil |
CN104929700B (zh) * | 2015-06-05 | 2016-03-16 | 赵军 | 一种螺旋型多段组合式封严篦齿 |
US9810087B2 (en) | 2015-06-24 | 2017-11-07 | United Technologies Corporation | Reversible blade rotor seal with protrusions |
US10822988B2 (en) * | 2015-12-21 | 2020-11-03 | Pratt & Whitney Canada Corp. | Method of sizing a cavity in a part |
US10648479B2 (en) * | 2017-10-30 | 2020-05-12 | United Technologies Corporation | Stator segment circumferential gap seal |
EP3667132A1 (de) * | 2018-12-13 | 2020-06-17 | Siemens Aktiengesellschaft | Dichtungsanordnung für ein geteiltes gehäuse |
FR3100274B1 (fr) * | 2019-09-04 | 2022-05-06 | Safran Aircraft Engines | Distributeur pour turbine à gaz |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1816293A (en) * | 1925-09-30 | 1931-07-28 | William F Oberhuber | Method of making high pressure steam joints |
US2991045A (en) * | 1958-07-10 | 1961-07-04 | Westinghouse Electric Corp | Sealing arrangement for a divided tubular casing |
US3341172A (en) * | 1965-06-24 | 1967-09-12 | Westinghouse Electric Corp | Fluid machine casing sealing structure |
GB1493913A (en) * | 1975-06-04 | 1977-11-30 | Gen Motors Corp | Turbomachine stator interstage seal |
US4537024A (en) * | 1979-04-23 | 1985-08-27 | Solar Turbines, Incorporated | Turbine engines |
JPS58185903A (ja) * | 1982-04-23 | 1983-10-29 | Hitachi Ltd | 蒸気タ−ビン車室 |
US4452462A (en) * | 1983-10-06 | 1984-06-05 | Gray Tool Company | Temperature resistant joint packing with E-shaped spring seal |
US5058906A (en) * | 1989-01-19 | 1991-10-22 | Vetco Gray Inc. | Integrally redundant seal |
US5158430A (en) * | 1990-09-12 | 1992-10-27 | United Technologies Corporation | Segmented stator vane seal |
US5221096A (en) * | 1990-10-19 | 1993-06-22 | Allied-Signal Inc. | Stator and multiple piece seal |
US5374161A (en) * | 1993-12-13 | 1994-12-20 | United Technologies Corporation | Blade outer air seal cooling enhanced with inter-segment film slot |
US5586773A (en) * | 1995-06-19 | 1996-12-24 | General Electric Company | Gas-path leakage seal for a gas turbine made from metallic mesh |
US5509669A (en) * | 1995-06-19 | 1996-04-23 | General Electric Company | Gas-path leakage seal for a gas turbine |
-
1996
- 1996-09-27 RU RU98108420/06A patent/RU2162556C2/ru not_active IP Right Cessation
- 1996-09-27 JP JP51308597A patent/JP3898225B2/ja not_active Expired - Lifetime
- 1996-09-27 EP EP96942252A patent/EP0852659B1/de not_active Expired - Lifetime
- 1996-09-27 DE DE59609029T patent/DE59609029D1/de not_active Expired - Lifetime
- 1996-09-27 WO PCT/DE1996/001861 patent/WO1997012125A2/de active IP Right Grant
-
1998
- 1998-03-30 US US09/052,344 patent/US5975844A/en not_active Expired - Lifetime
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2407641A1 (de) | 2010-07-13 | 2012-01-18 | Siemens Aktiengesellschaft | Dichtelement zur Dichtung eines Spalts sowie Dichtungsanordnung |
WO2012007506A1 (de) | 2010-07-13 | 2012-01-19 | Siemens Aktiengesellschaft | Dichtungsanordnung zur dichtung eines spalts und dichtelement dafür |
WO2012007158A1 (de) | 2010-07-13 | 2012-01-19 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spalts |
US9382846B2 (en) | 2010-07-13 | 2016-07-05 | Siemens Aktiengesellschaft | Sealing element for sealing a gap |
WO2014146866A1 (de) | 2013-03-20 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spaltes und zugehörige gasturbine |
WO2014146954A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spaltes |
DE102013205028A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur Dichtung eines Spaltes |
WO2014146955A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur dichtung eines spaltes |
DE102013205031A1 (de) | 2013-03-21 | 2014-09-25 | Siemens Aktiengesellschaft | Dichtelement zur Dichtung eines Spaltes |
WO2015132012A1 (de) | 2014-03-07 | 2015-09-11 | Siemens Aktiengesellschaft | Turbinengehäuse mit einer dichtungsanordnung zum abdichten eines spalts zwischen zwei bei raumtemperatur spaltseitig flächig aneinander liegender bauteile |
EP2915960A1 (de) | 2014-03-07 | 2015-09-09 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile |
WO2015132013A1 (de) | 2014-03-07 | 2015-09-11 | Siemens Aktiengesellschaft | Dichtungsanordnung zum abdichten eines spalts zwischen zwei bei raumtemperatur spaltseitig flächig aneinander liegender bauteile |
EP2915959A1 (de) | 2014-03-07 | 2015-09-09 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile |
CN106103905A (zh) * | 2014-03-07 | 2016-11-09 | 西门子股份公司 | 用于密封在室温下在间隙侧彼此平靠的两个部件之间的间隙的密封装置 |
US10202861B2 (en) | 2014-03-07 | 2019-02-12 | Siemens Aktiengesellschaft | Sealing arrangement for sealing a gap between two components which bear flat against one another on the gap side at room temperature |
EP3000983A1 (de) | 2014-09-29 | 2016-03-30 | Siemens Aktiengesellschaft | Dichtungsanordnung zum Abdichten eines Spalts zwischen zwei bei Raumtemperatur spaltseitig flächig aneinander liegender Bauteile sowie Verfahren zum Montieren und Demontieren einer solchen |
WO2016050640A1 (de) | 2014-09-29 | 2016-04-07 | Siemens Aktiengesellschaft | Dichtungsanordnung zum abdichten eines spalts zwischen zwei bei raumtemperatur spaltseitig flächig aneinander liegender bauteile sowie verfahren zum montieren und demontieren einer solchen |
EP4074941A1 (de) | 2021-04-13 | 2022-10-19 | Siemens Energy Global GmbH & Co. KG | Dichtungsstreifenelement und dichtungsanordnung mit diesem dichtungsstreifenelement |
WO2022218735A1 (en) | 2021-04-13 | 2022-10-20 | Siemens Energy Global GmbH & Co. KG | Sealing strip element and sealing arrangement comprising said sealing strip element |
EP4137670A1 (de) | 2021-08-19 | 2023-02-22 | Siemens Energy Global GmbH & Co. KG | Dichtungsvorrichtung mit verschiebbarem widerlager |
WO2023020748A1 (en) | 2021-08-19 | 2023-02-23 | Siemens Energy Global GmbH & Co. KG | Sealing device with displaceable abutment |
Also Published As
Publication number | Publication date |
---|---|
US5975844A (en) | 1999-11-02 |
RU2162556C2 (ru) | 2001-01-27 |
JP3898225B2 (ja) | 2007-03-28 |
EP0852659A2 (de) | 1998-07-15 |
JPH11511535A (ja) | 1999-10-05 |
DE59609029D1 (de) | 2002-05-08 |
WO1997012125A2 (de) | 1997-04-03 |
WO1997012125A3 (de) | 1997-06-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0852659B1 (de) | Dichtelement zur dichtung eines spaltes sowie gasturbinenanlage | |
DE69937652T2 (de) | Bürstendichtung für eine Turbomaschine | |
EP0906494B1 (de) | Turbinenwelle sowie verfahren zur kühlung einer turbinenwelle | |
DE60201467T2 (de) | Gasturbinenbrennkammer aus Verbundwerkstoff mit keramischer Matrix | |
EP1664489B1 (de) | Gasturbine mit einem ringförmigen dichtungsmittel | |
DE3520208C2 (de) | Verbrennungsvorrichtung in einer Heißgasmaschine, insbesondere einer Stirlingmaschine | |
DE60212760T2 (de) | Turbine mit variabler Einlassgeometrie | |
DE3232925C2 (de) | ||
DE19620828C1 (de) | Turbinenwelle sowie Verfahren zur Kühlung einer Turbinenwelle | |
EP0856639A2 (de) | Abgasturbine eines Turboladers | |
EP3548705B1 (de) | Turbolader | |
DE2812051A1 (de) | Ringdichtung fuer ein gasturbinentriebwerk | |
DE2951197A1 (de) | Dichtungsteil, insbesondere dichtungsring, fuer ein gasturbinentriebwerk | |
EP1022437A1 (de) | Bauteil zur Verwendung in einer thermischen Machine | |
EP1848904B1 (de) | Dichtungselement zur verwendung in einer strömungsmaschine | |
WO1991019078A1 (de) | Leitkranz einer turbine eines gasturbinentriebwerks | |
EP0122872B1 (de) | MD-Dampfturbine in einflutiger Bauweise für eine Hochtemperaturdampfturbinenanlage mit Zwischenüb erhitzung | |
DE102010037844A1 (de) | Brennstoffdüsendichtungsabstandhalter und Verfahren zu seinem Einbau | |
EP1056931B1 (de) | Dichtungsanordnung sowie verwendung einer dichtungsanordnung | |
WO1989007194A1 (fr) | Turbine pour turbocompresseur | |
EP1118806A1 (de) | Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand | |
DE602004001306T2 (de) | Äussere Luftabdichtungsanordnung | |
EP1206627A1 (de) | Turbine sowie verfahren zur abführung von leckfluid | |
WO2009109430A1 (de) | Dichtungsanordnung und gasturbine | |
EP1268981B1 (de) | Turbinenanlage |
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 |
|
17P | Request for examination filed |
Effective date: 19980320 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): CH DE ES FR GB IT LI SE |
|
17Q | First examination report despatched |
Effective date: 20001218 |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE ES FR GB IT LI SE |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REF | Corresponds to: |
Ref document number: 59609029 Country of ref document: DE Date of ref document: 20020508 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20020703 |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20020618 |
|
ET | Fr: translation filed | ||
ET | Fr: translation filed | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20020930 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20020930 |
|
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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20021030 |
|
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: 20030106 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20150909 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20150910 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20150924 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20151120 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 59609029 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20160926 |
|
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 EXPIRATION OF PROTECTION Effective date: 20160926 |