EP2410133A1 - Gas turbine and method for sealing leakages - Google Patents

Gas turbine and method for sealing leakages Download PDF

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Publication number
EP2410133A1
EP2410133A1 EP10170462A EP10170462A EP2410133A1 EP 2410133 A1 EP2410133 A1 EP 2410133A1 EP 10170462 A EP10170462 A EP 10170462A EP 10170462 A EP10170462 A EP 10170462A EP 2410133 A1 EP2410133 A1 EP 2410133A1
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EP
European Patent Office
Prior art keywords
gas turbine
sealing
sealing strip
blade
blades
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Withdrawn
Application number
EP10170462A
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German (de)
French (fr)
Inventor
Gernot Lang
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
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Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10170462A priority Critical patent/EP2410133A1/en
Publication of EP2410133A1 publication Critical patent/EP2410133A1/en
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0463—Cobalt
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2300/612—Foam

Definitions

  • the invention relates to a gas turbine according to the preamble of claim 1, and to a method for sealing leakage currents according to claims 6 and 7.
  • blades of gas turbines have an airfoil and a shroud formed on the blade tip with radially outwardly facing and aligned in the direction of rotation cutting on. Between shroud and one, the flow channel forming the housing inner wall of the turbine housing, a radial gap is formed.
  • a honeycomb-shaped sealing band is usually fastened to the housing inner wall. This must fill the radial gap so far that the cutting edges of the shrouds at least partially engage in this sealing strip.
  • the rotating blades dig into the sealing band, forming grooves that create a quasi labyrinth-like seal of these blades and the sealing band.
  • Corresponding measures can also be provided laterally on the blade blade for sealing the gap between blades and vanes.
  • the object of the invention is therefore to provide a gas turbine and a method for sealing such leakage currents, which overcome the disadvantages described above.
  • the open-pored metal structure could consist of a material based on nickel or a nickel-cobalt alloy, for example. Both materials are characterized by high oxidation and corrosion resistance even at high temperatures, and are therefore ideally suited for use in gas turbines.
  • the thermal and mechanical properties of these materials can be easily adapted to the requirements as a sealing tape for sealing leakage currents.
  • these sealing tapes according to the invention of such open-pore metal structures in contrast to the known honeycomb-like sealing tapes, easier to manufacture and less prone to mechanical deformation and thus less maintenance-intensive and thus more cost-effective.
  • FIG. 1 schematically a single blade of a blade row of the gas turbine.
  • the rotor blade 10 has an airfoil 11 and a shroud 12 formed on the blade tip, with blades 13 pointing radially outwards and oriented in the direction of rotation.
  • a radial gap 21 is formed, which is filled with a fixed to the housing inner wall 20 sealing tape 30, that the cutting edges 13 of the shrouds 12 at least partially engage in the sealing strip 30.
  • the sealing strip 30 is made of an open-pore metal structure and thus form a seal for leakage currents in the radial gap 21 with the cutting edges 13, which virtually burrow into the sealing strip.
  • FIG. 2 shows a further embodiment, in addition to or independent of the in FIG. 1 illustrated embodiment may be provided in the gas turbine.
  • the blade blade 11 of the blade 11 here at its axial sides in the direction of rotation aligned cutting 13 'on.
  • These cutting edges 13 ' are formed so that they engage in corresponding, arranged on the adjacent vanes 23 sealing strips 30' so that the axial gap between the blade 10 and the guide vane 23 is sealed.
  • additional sealing plates 24 are provided on the guide vane 23, which engage over the cutting edges 13 'in the axial direction and at whose, to the cutting edges 13' directed sides, the sealing strip 30 'is provided.
  • the sealing strip 30 'shown here is made according to the invention of an open-pore metal structure and causes a hot gas infeed can be safely avoided in the Radrete Congress Congress even at low barrier airflows.

Abstract

The gas turbine has a turbine housing and rotor blade rows, where the rotor blades (10) of the rotor blade rows represent in radially outward manner and have blade edges (13') that are aligned in circulating direction. A sealing band (30') is made from a porous metal structure that is a nickel-based material or nickel-cobalt alloy-based material. An independent claim is also included for a method for sealing leakage in gas turbine.

Description

Gasturbine und Verfahren zum Abdichten von Leckströmen in einer solchenGas turbine and method for sealing leakage currents in such

Die Erfindung betrifft eine Gasturbine gemäß dem Oberbegriff des Anspruchs 1, sowie ein Verfahren zum Abdichten von Leckströmen gemäß Anspruch 6 und 7.The invention relates to a gas turbine according to the preamble of claim 1, and to a method for sealing leakage currents according to claims 6 and 7.

Um einen möglichst hohen Wirkungsgrad der Gasturbine zu erzielen, müssen Verluste in der Gasturbine gezielt unterbunden werden. Verluste können insbesondere im Bereich des Strömungskanals entstehen. Hier müssen spezielle Maßnahmen vorgesehen werden, um die für den Betrieb der Gasturbine notwendigen Spalte zwischen den rotierenden Laufschaufelreihen und den stationären Anlagenkomponenten, wie beispielsweise den Leitschaufeln oder den den Strömungskanal bildenden Gehäuseteilen, abzudichten. Leckströme des durch den Strömungskanal strömenden Heißgases, die an diesen Spalten auftreten können, können so weitgehend unterbunden werden.In order to achieve the highest possible efficiency of the gas turbine, losses in the gas turbine must be selectively prevented. Losses can occur especially in the region of the flow channel. Here special measures must be provided to seal the necessary for the operation of the gas turbine column between the rotating blade rows and the stationary plant components, such as the vanes or the flow channel forming housing parts. Leakage currents of the hot gas flowing through the flow channel, which can occur at these gaps, can thus be largely prevented.

Laufschaufeln von Gasturbinen weisen deshalb ein Schaufelblatt und ein an der Schaufelspitze ausgebildetes Deckband mit radial nach außen zeigenden und in Umlaufrichtung ausgerichteten Schneiden auf. Zwischen Deckband und einer, den Strömungskanal bildenden Gehäuseinnenwand des Turbinengehäuses ist ein Radialspalt ausgebildet. Zum Abdichten dieses Radialspaltes wird üblicherweise ein wabenförmiges Dichtband an der Gehäuseinnenwand befestigt. Dieses muss dabei den Radialspalt soweit ausfüllen, dass die Schneiden der Deckbänder zumindest teilweise in dieses Dichtband eingreifen. Die rotierenden Schneiden graben sich in das Dichtband ein und bilden so Furchen, was eine quasi labyrinthartige Dichtung aus diesen Schneiden und dem Dichtband entstehen lässt. Entsprechende Maßnahmen können auch seitlich am Laufschaufelblatt zur Abdichtung der Spalte zwischen Lauf- und Leitschaufeln vorgesehen werden.Therefore, blades of gas turbines have an airfoil and a shroud formed on the blade tip with radially outwardly facing and aligned in the direction of rotation cutting on. Between shroud and one, the flow channel forming the housing inner wall of the turbine housing, a radial gap is formed. For sealing this radial gap, a honeycomb-shaped sealing band is usually fastened to the housing inner wall. This must fill the radial gap so far that the cutting edges of the shrouds at least partially engage in this sealing strip. The rotating blades dig into the sealing band, forming grooves that create a quasi labyrinth-like seal of these blades and the sealing band. Corresponding measures can also be provided laterally on the blade blade for sealing the gap between blades and vanes.

Durch solche Abdichtungen können Leckströme durch diese Spalte verringert werden. Dichtbänder mit wabenförmigen Strukturen sind aber sehr aufwändig in der Herstellung und damit teuer. Zudem sind sie aufgrund ihrer filigranen Struktur anfällig gegen Verformungen und daher auch sehr wartungsintensiv.Such seals can reduce leakage currents through these gaps. But sealing tapes with honeycomb structures are very expensive to manufacture and therefore expensive. In addition, due to their filigree structure they are susceptible to deformation and therefore also very maintenance-intensive.

Aufgabe der Erfindung ist es daher, eine Gasturbine sowie ein Verfahren zum Abdichten solcher Leckströme bereitzustellen, welche die zuvor beschriebenen Nachteile überwinden.The object of the invention is therefore to provide a gas turbine and a method for sealing such leakage currents, which overcome the disadvantages described above.

Diese Aufgabe wird mit einer Gasturbine mit den Merkmalen des Anspruchs 1, sowie mit dem Verfahren zum Abdichten von Leckströmen mit den Merkmalen des Anspruchs 6 und 7 gelöst.This object is achieved with a gas turbine with the features of claim 1, as well as with the method for sealing leakage currents with the features of claim 6 and 7.

Erfindungsgemäß ist dabei vorgesehen, bekannte wabenförmige Dichtbänder durch Dichtbänder aus einer offenporigen Metallstruktur zu ersetzen. Die offenporige Metallstruktur könnte dabei beispielsweise aus einem auf Nickel oder einer Nickel-Kobalt-Legierung basierenden Material bestehen. Beide Materialien zeichnen sich durch hohe Oxidations- und Korrosionsbeständigkeit auch bei hohen Temperaturen aus, und sind somit für den Einsatz in Gasturbinen bestens geeignet. Durch eine geeignete Wahl der Porengröße lassen sich die thermischen und mechanischen Eigenschaften dieser Materialien einfach an die Erfordernisse als Dichtband zum Abdichten von Leckströmen anpassen. Zudem sind diese erfindungsgemäßen Dichtbänder aus solchen offenporigen Metallstrukturen, im Gegensatz zu den bekannten wabenartigen Dichtbändern, einfacher in der Herstellung und weniger anfällig gegen mechanische Verformungen und damit weniger wartungsintensiv und somit auch kostengünstiger.According to the invention, it is provided to replace known honeycomb-shaped sealing tapes with sealing tapes made of an open-pore metal structure. The open-pored metal structure could consist of a material based on nickel or a nickel-cobalt alloy, for example. Both materials are characterized by high oxidation and corrosion resistance even at high temperatures, and are therefore ideally suited for use in gas turbines. By a suitable choice of the pore size, the thermal and mechanical properties of these materials can be easily adapted to the requirements as a sealing tape for sealing leakage currents. In addition, these sealing tapes according to the invention of such open-pore metal structures, in contrast to the known honeycomb-like sealing tapes, easier to manufacture and less prone to mechanical deformation and thus less maintenance-intensive and thus more cost-effective.

Die Erfindung soll nun nachfolgend anhand der nachfolgenden Figuren beispielhaft erläutert werden. Es zeigen:

FIG 1
schematisch eine Ausführungsform für die radiale Abdichtung,
FIG 2
schematisch eine Ausführungsform für die axiale Abdichtung.
The invention will now be explained by way of example with reference to the following figures. Show it:
FIG. 1
schematically an embodiment for the radial seal,
FIG. 2
schematically an embodiment for the axial seal.

Dargestellt ist in FIG 1 schematisch eine einzelne Laufschaufel einer Laufschaufelreihe der Gasturbine. Die Laufschaufel 10 weist ein Schaufelblatt 11 und ein an der Schaufelspitze ausgebildetes Deckband 12, mit radial nach außen zeigenden und in Umlaufrichtung ausgerichteten Schneiden 13, auf. Zwischen einer, einen Strömungskanal bildenden Gehäuseinnenwand 20 des Turbinengehäuses und den Deckbändern 12, der im Strömungskanal rotierenden Laufschaufelreihen, ist ein Radialspalt 21 ausgebildet, der so mit einem an der Gehäuseinnenwand 20 befestigten Dichtband 30 aufgefüllt ist, dass die Schneiden 13 der Deckbänder 12 zumindest teilweise in das Dichtband 30 eingreifen. Erfindungsgemäß ist nun vorgesehen, dass das Dichtband 30 aus einer offenporigen Metallstruktur hergestellt ist und somit mit den Schneiden 13, die sich quasi in das Dichtband eingraben, eine Dichtung für Leckströme im Radialspalt 21 bilden.Is shown in FIG. 1 schematically a single blade of a blade row of the gas turbine. The rotor blade 10 has an airfoil 11 and a shroud 12 formed on the blade tip, with blades 13 pointing radially outwards and oriented in the direction of rotation. Between a, a flow channel forming housing inner wall 20 of the turbine housing and the shrouds 12, the rotating rotor in the flow channel rows, a radial gap 21 is formed, which is filled with a fixed to the housing inner wall 20 sealing tape 30, that the cutting edges 13 of the shrouds 12 at least partially engage in the sealing strip 30. According to the invention it is now provided that the sealing strip 30 is made of an open-pore metal structure and thus form a seal for leakage currents in the radial gap 21 with the cutting edges 13, which virtually burrow into the sealing strip.

FIG 2 zeigt eine weitere Ausführung, die zusätzlich oder auch unabhängig von der in FIG 1 dargestellten Ausführungsform in der Gasturbine vorgesehen werden kann. Im Gegensatz zu der in FIG 1 dargestellten Ausführungsform weist das Laufschaufelblatt 11 der Laufschaufel 11 hier an seinen axialen Seiten in Umlaufrichtung ausgerichtete Schneiden 13' auf. Diese Schneiden 13' sind so ausgebildet, dass sie in entsprechende, an den benachbarten Leitschaufeln 23 angeordnete Dichtbänder 30' so eingreifen, dass der axiale Spalt zwischen Laufschaufel 10 und Leitschaufel 23 abgedichtet wird. Im hier dargestellten Ausführungsbeispiel sind hierfür zusätzliche Dichtbleche 24 an der Leitschaufel 23 vorgesehen, die die Schneiden 13' in axialer Richtung übergreifen und an deren, zu den Schneiden 13' gerichteten Seiten, das Dichtband 30' vorgesehen ist. Auch das hier gezeigte Dichtband 30' ist erfindungsgemäß aus einer offenporigen Metallstruktur hergestellt und führt dazu, dass in den Radseitenräumen auch bei geringen Sperrluftströmen sicher ein Heißgaseinzug vermieden werden kann. FIG. 2 shows a further embodiment, in addition to or independent of the in FIG. 1 illustrated embodiment may be provided in the gas turbine. Unlike the in FIG. 1 illustrated embodiment, the blade blade 11 of the blade 11 here at its axial sides in the direction of rotation aligned cutting 13 'on. These cutting edges 13 'are formed so that they engage in corresponding, arranged on the adjacent vanes 23 sealing strips 30' so that the axial gap between the blade 10 and the guide vane 23 is sealed. In the embodiment shown here additional sealing plates 24 are provided on the guide vane 23, which engage over the cutting edges 13 'in the axial direction and at whose, to the cutting edges 13' directed sides, the sealing strip 30 'is provided. Also, the sealing strip 30 'shown here is made according to the invention of an open-pore metal structure and causes a hot gas infeed can be safely avoided in the Radseitenräumen even at low barrier airflows.

Claims (7)

Gasturbine mit einem Turbinengehäuse und darin rotierenden Laufschaufelreihen, wobei Laufschaufeln (10) der Laufschaufelreihen jeweils radial nach außen zeigende und in Umlaufrichtung ausgerichtete Schneiden (13, 13') aufweisen, und wobei zwischen den Laufschaufeln (10) und feststehenden Teilen der Gasturbine (20,23) ein Spalt (21,22) ausgebildet ist, der soweit mit einem an den feststehenden Teilen (20,23) angeordneten Dichtband (30, 30') aufgefüllt ist, dass die Schneiden (13,13') zumindest teilweise in das Dichtband (30,30') eingreifen,
dadurch gekennzeichnet, dass das Dichtband (30,30') aus einer offenporigen Metallstruktur besteht.A gas turbine having a turbine housing and rotating blade rows therein, wherein blades (10) of the blade rows each have radially outwardly facing and circumferentially oriented blades (13, 13 '), and between the blades (10) and stationary parts of the gas turbine (20, 23) a gap (21,22) is formed, which is so far filled with a on the fixed parts (20,23) arranged sealing strip (30, 30 '), that the cutting (13,13') at least partially in the sealing strip (30,30 ') intervene,
characterized in that the sealing strip (30,30 ') consists of an open-pored metal structure. Gasturbine nach Anspruch 1,
dadurch gekennzeichnet, dass die offenporige Metallstruktur ein auf Nickel basierendes Material ist.Gas turbine according to claim 1,
characterized in that the open-pore metal structure is a nickel-based material. Gasturbine nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass die offenporige Metallstruktur ein auf einer Nickel-Kobalt Legierung basierendes Material ist.Gas turbine according to claim 1 or 2,
characterized in that the open-pore metal structure is a nickel-cobalt alloy based material. Gasturbine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Laufschaufeln (10) der Laufschaufelreihen jeweils ein Schaufelblatt (11), und ein an der Schaufelspitze ausgebildetes Deckband (12) mit den Schneiden (13) aufweisen, und wobei zwischen einer Gehäuseinnenwand (20) als feststehendes Teil der Gasturbine und den Deckbändern (12) der im Strömungskanal rotierenden Laufschaufelreihen ein Radialspalt (21) ausgebildet ist, der soweit mit dem an der Gehäuseinnenwand (20) befestigten Dichtband (30) aufgefüllt ist, dass die Schneiden (13) der Deckbänder (12) zumindest teilweise in das Dichtband (30) eingreifen.Gas turbine according to one of claims 1 to 3, characterized in that the blades (10) of the blade rows each have an airfoil (11), and formed on the blade tip shroud (12) with the cutting edges (13), and wherein between a housing inner wall (20) is formed as a fixed part of the gas turbine and the shrouds (12) of the rotating rotor blades in the flow row a radial gap (21) which is as far filled with the on the housing inner wall (20) attached sealing strip (30) that the cutting (13 ) of the shrouds (12) at least partially in the sealing strip (30) intervene. Gasturbine nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Laufschaufeln (10) der Laufschaufelreihen jeweils ein Schaufelblatt (11) mit an benachbarten Leitschaufeln (23) zugewandten Seiten des Schaufelblatts (11) angeordneten Schneiden (13') aufweisen, und wobei zwischen den Leitschaufeln (23) als feststehende Teile der Gasturbine und den Seiten des Schaufelblatts (11) ein Spalt (22) ausgebildet ist, der soweit mit dem an den Leitschaufeln (23) befestigten Dichtband (30') aufgefüllt ist, dass die Schneiden (13') zumindest teilweise in das Dichtband (30') eingreifen.Gas turbine according to one of claims 1 to 4, characterized in that the rotor blades (10) of the rotor blade rows each have an airfoil (11) with adjacent vanes (23) facing sides of the airfoil (11) arranged cutting edges (13 '), and wherein between the guide vanes (23) as stationary parts of the gas turbine and the sides of the blade (11) a gap (22) is formed, which is as far filled with the attached to the vanes (23) sealing strip (30 ') that the cutting ( 13 ') at least partially engage in the sealing strip (30'). Verfahren zum Abdichten von Leckströmen in Gasturbinen, dadurch gekennzeichnet, dass in einen Radialspalt zwischen einer einen Strömungskanal bildenden Gehäuseinnenwand einer Gasturbine und Deckbändern von in diesem Strömungskanal rotierenden Laufschaufelreihen an der Gehäuseinnenwand ein Dichtband aus einer offenporigen Metallstruktur so angebracht wird, dass in Umlaufrichtung ausgerichtete Schneiden auf dem Deckband zumindest teilweise in das Dichtband eingreifen.A method for sealing leakage currents in gas turbines, characterized in that in a radial gap between a flow channel forming a housing inner wall of a gas turbine and shrouds of rotating in this flow channel rows of blades on the housing inner wall, a sealing tape of an open-pore metal structure is mounted so that aligned in the direction of rotation cutting engage the shroud at least partially in the sealing tape. Verfahren zum Abdichten von Leckströmen in Gasturbinen, dadurch gekennzeichnet, dass in einen Axialspalt zwischen einer Leitschaufel und einem Schaufelblatt einer Laufschaufel ein Dichtband aus einer offenporigen Metallstruktur so angebracht wird, dass in Umlaufrichtung ausgerichtete Schneiden an der Seite zumindest teilweise in das Dichtband eingreifen.A method for sealing leakage currents in gas turbines, characterized in that in an axial gap between a vane and a blade of a blade, a sealing tape of an open-pore metal structure is mounted so that aligned in the circumferential direction cutting on the side at least partially engage in the sealing strip.
EP10170462A 2010-07-22 2010-07-22 Gas turbine and method for sealing leakages Withdrawn EP2410133A1 (en)

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EP10170462A EP2410133A1 (en) 2010-07-22 2010-07-22 Gas turbine and method for sealing leakages

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EP2410133A1 true EP2410133A1 (en) 2012-01-25

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
EP1146204A2 (en) * 2000-04-12 2001-10-17 ROLLS-ROYCE plc Abradable seals
EP1152124A1 (en) * 2000-05-04 2001-11-07 Siemens Aktiengesellschaft Sealing device
US20040022625A1 (en) * 2002-03-15 2004-02-05 Care Ian C. D. Cellular materials
DE10360164A1 (en) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gas turbine component
EP1878876A2 (en) * 2006-07-11 2008-01-16 Rolls-Royce plc Gas turbine abradable seal
DE102008019331A1 (en) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Inlet seal for compressor of gas-turbine engine, has open-porous metallic sponge with filling material made of heat resistant duroplastic synthetic resin infiltrated in open-porous cavities of metallic sponge
EP2196632A2 (en) * 2008-12-10 2010-06-16 Rolls-Royce plc A seal in a gas turbine and a method of manufacturing a seal

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
EP1146204A2 (en) * 2000-04-12 2001-10-17 ROLLS-ROYCE plc Abradable seals
EP1152124A1 (en) * 2000-05-04 2001-11-07 Siemens Aktiengesellschaft Sealing device
US20040022625A1 (en) * 2002-03-15 2004-02-05 Care Ian C. D. Cellular materials
DE10360164A1 (en) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gas turbine component
EP1878876A2 (en) * 2006-07-11 2008-01-16 Rolls-Royce plc Gas turbine abradable seal
DE102008019331A1 (en) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Inlet seal for compressor of gas-turbine engine, has open-porous metallic sponge with filling material made of heat resistant duroplastic synthetic resin infiltrated in open-porous cavities of metallic sponge
EP2196632A2 (en) * 2008-12-10 2010-06-16 Rolls-Royce plc A seal in a gas turbine and a method of manufacturing a seal

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