EP1013890B1 - Abradable seal for turbomachines - Google Patents

Abradable seal for turbomachines Download PDF

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Publication number
EP1013890B1
EP1013890B1 EP99124032A EP99124032A EP1013890B1 EP 1013890 B1 EP1013890 B1 EP 1013890B1 EP 99124032 A EP99124032 A EP 99124032A EP 99124032 A EP99124032 A EP 99124032A EP 1013890 B1 EP1013890 B1 EP 1013890B1
Authority
EP
European Patent Office
Prior art keywords
sealing
foamed
gas turbine
abradable seal
seal
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
Application number
EP99124032A
Other languages
German (de)
French (fr)
Other versions
EP1013890A2 (en
EP1013890A3 (en
Inventor
Karl Schreiber
Armin Dr. Plath
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1013890A2 publication Critical patent/EP1013890A2/en
Publication of EP1013890A3 publication Critical patent/EP1013890A3/en
Application granted granted Critical
Publication of EP1013890B1 publication Critical patent/EP1013890B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • 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 brush seal between a wall section and the blade tips of a gas turbine.
  • the invention further relates to a Method for producing a gas turbine with such a sealing seal.
  • DE 32 35 745 C2 the technical environment in particular to EP 0 605 417 B1 and to US 5,388,959 and US 4,392,656.
  • Bearing seals from or in gas turbines essentially have two Fulfill tasks, namely firstly a flow around the individual running stages prevent the gas turbine and secondly the housing structure or thermally insulate the hot gas in the gas turbine wall sections or control the heat flow passing into the wall sections in such a way that the thermal expansion of the housing is simultaneous with the thermal expansion of the rotating blades or the disks carrying them.
  • the so-called gap between the tips of the turbine blades and the these surrounding wall sections or that on the wall sections The intended sealing seal should namely over the entire operating area the gas turbine should be as small as possible because of any enlargement of the gap dimension a reduction in thrust and thus a reduced Efficiency.
  • the invention proposed here replaces the above. known Sealing systems through a metal foam.
  • a corrosion-resistant high-temperature alloy such as. Hastalloy X, IN 601, ODS alloys are the ones mentioned Requirements met in an excellent way.
  • the one is younger Metal foam technology that is currently up to date for the specialist basically known.
  • a suitable metal alloy is used
  • the present invention is a metallic corrosion-resistant High temperature alloy - foamed using known methods, so that an essentially fine foam structure is formed, with thin metal walls enclosing a plurality of cavities between them.
  • a foaming method for example, a metal powder mixed with a metal hydrite and then extruded, after which this primary material is thermally foamed.
  • one is Appropriate manufacture from prefabricated hollow metal spheres possible. In general, this produces a mainly closed-pore foam Structure with high porosity and good thermal insulation properties educated.
  • a brush seal between a wall section and the blade tips of a gas turbine combines such a structure with high porosity, favorable running-in properties, high sealing capacity and good thermal insulation in a single material.
  • a sealing gasket can also be manufactured extremely simply, in fact Manufacturing process the porosity of the resulting structure as desired can be controlled. This in turn makes it possible for the enema that Sealing and insulating properties in the desired direction.
  • solder does not migrate (as for example in the case of open-pore structures or metal felts) from the joint into the sealing structure due to capillary forces; so that the foam is easy to solder.
  • An alternative production method is to connect the unfoamed primary material to the respective wall section or to the housing structure in a first process step and to foam this primary material in a second process step. This is followed by machining, of course, to bring the metal foam or the sealing gasket into the desired shape.
  • the use leads from metal foam seals to better sealing behavior while improving the insulation of the housing structure against that in the gas turbine or between the brush seals and the turbine blades led hot gas.
  • the relatively simple manufacturing route leads to cost savings.

Abstract

The contact seal consists entirely of a foamed metallic corrosion-resistant high-temperature alloy, fixed to the wall sector by high temperature soldering. Since there is no open-pore structure, the solder is not taken into the seal structure by capillary attraction, so the foam is easy to solder. The unfoamed raw material may first be connected to the wall sector, and then foamed.

Description

Die Erfindung betrifft eine Anstreifdichtung zwischen einem Wandabschnitt und den Schaufelspitzen einer Gasturbine. Ferner betrifft die Erfindung ein Verfahren zum Herstellen einer Gasturbine mit einer derartigen Anstreifdichtung. Zum technischen Umfeld wird neben der DE 32 35 745 C2 insbesondere auf die EP 0 605 417 B1 sowie auf die US 5,388,959 und die US 4,392,656 verwiesen.The invention relates to a brush seal between a wall section and the blade tips of a gas turbine. The invention further relates to a Method for producing a gas turbine with such a sealing seal. In addition to DE 32 35 745 C2, the technical environment in particular to EP 0 605 417 B1 and to US 5,388,959 and US 4,392,656.

Anstreifdichtungen von bzw. in Gasturbinen müssen im wesentlichen zwei Aufgaben erfüllen, nämlich erstens eine Umströmung der einzelnen Laufstufen der Gasturbine verhindern und zweitens die Gehäusestruktur bzw. die das Heißgas in der Gasturbine führenden Wandabschnitte thermisch isolieren bzw. den in die Wandabschnitte übertretenden Wärmestrom derart steuern, daß die thermische Gehäusedehnung simultan zur thermischen Dehnung der rotierenden Schaufeln bzw. der diese tragenden Scheiben verläuft. Das sog. Spaltmaß zwischen den Spitzen der Turbinen-Schaufeln und den diese umgebenden Wandabschnitten bzw. der auf den Wandabschnitten vorgesehenen Anstreifdichtung sollte nämlich über dem gesamten Betriebsbereich der Gasturbine so gering als möglich sein, da jede Vergrößerung des Spaltmaßes eine Schubverminderung und somit einen reduzierten Wirkungsgrad zur Folge hat.Bearing seals from or in gas turbines essentially have two Fulfill tasks, namely firstly a flow around the individual running stages prevent the gas turbine and secondly the housing structure or thermally insulate the hot gas in the gas turbine wall sections or control the heat flow passing into the wall sections in such a way that the thermal expansion of the housing is simultaneous with the thermal expansion of the rotating blades or the disks carrying them. The so-called gap between the tips of the turbine blades and the these surrounding wall sections or that on the wall sections The intended sealing seal should namely over the entire operating area the gas turbine should be as small as possible because of any enlargement of the gap dimension a reduction in thrust and thus a reduced Efficiency.

Diese genannten Anforderungen können mit den bisherigen in Serie befindlichen Anstreifdichtungen nicht vollständig erfüllt werden. So sind gut dichtende, fein strukturierte Wabendichtungsstrukturen, so wie sie in der eingangs erstgenannten Schrift gezeigt sind, nicht hinreichend gut mit isolierendem Material befüllbar. Gröbere, gut befüllbare Wabendichtungsstrukturen hingegen weisen keine befriedigenden Dichteigenschaften auf. Bekannt sind ferner Metall-Keramik Verbindungen, bspw. zwischen einer Wabendichtungsstruktur und deren Füllung, die jedoch insbesondere bei thermozyklischer Beanspruchung eine eingeschränkte Lebensdauer zeigen. Ferner existieren aufgespritzte Dichtschichten (wie bspw. METCO), die jedoch Nachteile hinsichtlich des Einlaufverhaltens, der thermischen Isolierung und ihrem Dichtungsverhalten zeigen.These requirements can be used in series with the previous ones Contact seals are not completely fulfilled. So are well sealing, finely structured honeycomb seal structures, as in the beginning first mentioned font are shown, not sufficiently good with isolating Material can be filled. Coarser, easily fillable honeycomb sealing structures, however do not have satisfactory sealing properties. Are also known Metal-ceramic connections, for example between a honeycomb sealing structure and their filling, which is particularly the case with thermocyclic Show a limited service life. Furthermore exist sprayed-on sealing layers (such as METCO), which, however, have disadvantages with regard to the running-in behavior, the thermal insulation and their sealing behavior demonstrate.

Die eingangs zuletzt genannte US 4,392,656 beschreibt, zum Beispiel, ein gekühltes Dichtungselement, dessen Grundfunktion in der Luftdurchlässigkeit, offenporige Struktur, begründet ist. Hierbei wird Kompressorluft zur Kühlung der Dichtungsstruktur und der Schaufelspitzen von außen durch die Dichtungselemente hindurch in Richtung Triebwerksmittelachse befördert.The last mentioned US 4,392,656 describes, for example, a cooled sealing element, the basic function of which is air permeability, open-pored structure is justified. Here, compressor air is used for cooling the sealing structure and the blade tips from the outside through the Sealing elements conveyed in the direction of the engine center axis.

Eine im Hinblick auf die genannten Anforderungen verbesserte Anstreifdichtung zwischen einem Wandabschnitt und den Schaufelspitzen einer Gasturbine aufzuzeigen, ist Aufgabe der vorliegenden Erfindung.An improved sealing seal with regard to the requirements mentioned between a wall section and the blade tips of a gas turbine to demonstrate is the object of the present invention.

Die Lösung dieser Aufgabe ist dadurch gekennzeichnet, dass die Anstreifdichtung vollständig aus einer aufgeschäumten, metallischen, korrosionsbeständigen Hochtemperaturlegierung besteht, wobei diese Hochtemperaturlegierung eine geschlossenporige Struktur aufweist. In den Unteransprüchen ist ein vorteilhaftes Verfahren zum Herstellen einer Gasturbine mit einer derartigen Metallschaum-Anstreifdichtung angegeben.The solution to this problem is characterized in that the brush seal completely from a foamed, metallic, corrosion-resistant High temperature alloy is made, this high temperature alloy is a closed-pore Has structure. In the subclaims is an advantageous one Method for manufacturing a gas turbine with such a metal foam brush seal specified.

Einfach ausgedrückt ersetzt die hier vorgeschlagene Erfindung die o.g. bekannten Dichtsysteme durch einen Metallschaum. Durch die Verwendung einer gleichmäßig aufgeschäumten korrosionsbeständigen Hochtemperaturlegierung wie z.B. Hastalloy X, IN 601, ODS-Legierungen werden die genannten Anforderungen in hervorragender Weise erfüllt. Dabei ist die in jüngerer Zeit aktuell gewordene Metallschaum-Technologie dem Fachmann grundsätzlich bekannt. Hierbei wird eine geeignete Metall-Legierung - bei der vorliegenden Erfindung handelt es sich um eine metallische korrosionsbeständige Hochtemperaturlegierung - mittels bekannter Methoden aufgeschäumt, so dass sich eine im wesentlichen feine Schaumstruktur bildet, wobei dünne Metallwände eine Vielzahl von Hohlräumen zwischen sich einschließen. Bei einer solchen Aufschäummethode kann bspw. ein Metallpulver mit einem Metallhydrit vermengt und anschließend extrudiert werden, wonach dieses Vormaterial thermisch geschäumt wird. Alternativ ist eine entsprechende Herstellung aus vorgefertigten metallischen Hohlkugeln möglich. Generell wird hierdurch eine vornehmlich geschlossenporig geschäumte Struktur mit hoher Porosität und guten thermischen Isolationseigenschaften gebildet.Simply put, the invention proposed here replaces the above. known Sealing systems through a metal foam. By using a evenly foamed corrosion-resistant high-temperature alloy such as. Hastalloy X, IN 601, ODS alloys are the ones mentioned Requirements met in an excellent way. The one is younger Metal foam technology that is currently up to date for the specialist basically known. Here, a suitable metal alloy is used The present invention is a metallic corrosion-resistant High temperature alloy - foamed using known methods, so that an essentially fine foam structure is formed, with thin metal walls enclosing a plurality of cavities between them. With such a foaming method, for example, a metal powder mixed with a metal hydrite and then extruded, after which this primary material is thermally foamed. Alternatively, one is Appropriate manufacture from prefabricated hollow metal spheres possible. In general, this produces a mainly closed-pore foam Structure with high porosity and good thermal insulation properties educated.

Für den vorgeschlagenen Anwendungsfall, nämlich für eine Anstreifdichtung zwischen einem Wandabschnitt und den Schaufelspitzen einer Gasturbine, vereinigt eine solche Struktur mit hoher Porosität in sich günstige Einlaufeigenschaften, ein hohes Dichtvermögen und zusätzlich eine gute Wärmedämmung in einem einzigen Werkstoff. Vorteilhafterweise lässt sich eine derartige Anstreifdichtung auch äußerst einfach fertigen, wobei im eigentlichen Herstellprozess die Porosität der entstehenden Struktur wie gewünscht gesteuert werden kann. Damit wiederum ist es möglich, die Einlauf-, die Dicht- und die Dämmeigenschaften in der gewünschten Richtung zu beeinflussen.For the proposed application, namely for a brush seal between a wall section and the blade tips of a gas turbine, combines such a structure with high porosity, favorable running-in properties, high sealing capacity and good thermal insulation in a single material. Advantageously, one Such a sealing gasket can also be manufactured extremely simply, in fact Manufacturing process the porosity of the resulting structure as desired can be controlled. This in turn makes it possible for the enema that Sealing and insulating properties in the desired direction.

Für die Herstellung einer Gasturbine mit einer Metallschaum-Anstreifdichtung gemäß der vorangehenden Beschreibung gibt es zwei besonders geeignete Möglichkeiten. Zum einen können vorgefertigte und dabei geeignet geformte Metallschaumelemente durch Hochtemperaturlöten mit den jeweiligen Wandabschnitten verbunden werden. Da dieser Metallschaum eine geschlossenporige Struktur aufweist, ist dieser Metallschaum lötbar. For the production of a gas turbine with a metal foam brush seal as described above, there are two particular ones appropriate options. For one, prefabricated and suitable molded metal foam elements by high temperature soldering with the respective wall sections are connected. Because this metal foam has a closed-pore structure, this metal foam is solderable.

Das Lot wandert dabei nicht (wie z.B. bei offenporigen Strukturen oder Metallfilzen) durch Kapilarkräfte von der Fügestelle in die Dichtstruktur; so daß der Schaum gut lötbar ist.
Ein alternativer Herstellweg besteht darin, in einem ersten Prozessschritt das ungeschäumte Vormaterial mit dem jeweiligen Wandabschnitt bzw. mit der Gehäusestruktur zu verbinden und in einem zweiten Prozessschritt dieses Vormaterial zu schäumen. Danach erfolgt selbstverständlich eine spanende Bearbeitung, um den Metallschaum bzw. die Anstreifdichtung in die gewünschte Form zu bringen.The solder does not migrate (as for example in the case of open-pore structures or metal felts) from the joint into the sealing structure due to capillary forces; so that the foam is easy to solder.
An alternative production method is to connect the unfoamed primary material to the respective wall section or to the housing structure in a first process step and to foam this primary material in a second process step. This is followed by machining, of course, to bring the metal foam or the sealing gasket into the desired shape.

Gegenüber den bisherigen Lösungen für Anstreifdichtungen führt die Verwendung von Metallschaumdichtungen zu einem besseren Dichtverhalten bei gleichzeitiger Verbesserung der Isolierung der Gehäusestruktur gegen das in der Gasturbine bzw. zwischen den Anstreifdichtungen und den Turbinenschaufeln geführte Heißgas. Dabei führt der relativ einfache Herstellweg zu Kosteneinsparungen. Durch Einflussnahme auf die Aufschäumparameter ist die Zellstruktur der Anstreifdichtung in gewissen Grenzen beeinflussbar, so dass die Einlaufeigenschaften, die Umströmungsbehinderung und die Isolierwirkung auf diese Weise bestimmt werden können.Compared to the previous solutions for brush seals, the use leads from metal foam seals to better sealing behavior while improving the insulation of the housing structure against that in the gas turbine or between the brush seals and the turbine blades led hot gas. The relatively simple manufacturing route leads to cost savings. By influencing the frothing parameters the cell structure of the brush seal can be influenced within certain limits, so that the inlet properties, the flow restriction and the Isolation effect can be determined in this way.

Claims (2)

  1. Abradable seal between a wall section and the blade tips of a gas turbine which fully consists of foamed, metallic, corrosion-resistant high-temperature alloy, characterized in that this high-temperature alloy has a closed-pore structure.
  2. Method for the manufacture of a gas turbine with an abradable seal in accordance with Claim 1,
    characterized in that the non-foamed base material of the abradable seal is initially attached to the wall sections and is subsequently foamed.
EP99124032A 1998-12-16 1999-12-09 Abradable seal for turbomachines Expired - Lifetime EP1013890B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19858031A DE19858031A1 (en) 1998-12-16 1998-12-16 Contact seal between a wall section and the blade tips of a gas turbine
DE19858031 1998-12-16

Publications (3)

Publication Number Publication Date
EP1013890A2 EP1013890A2 (en) 2000-06-28
EP1013890A3 EP1013890A3 (en) 2001-11-07
EP1013890B1 true EP1013890B1 (en) 2004-02-04

Family

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Application Number Title Priority Date Filing Date
EP99124032A Expired - Lifetime EP1013890B1 (en) 1998-12-16 1999-12-09 Abradable seal for turbomachines

Country Status (3)

Country Link
EP (1) EP1013890B1 (en)
AT (1) ATE259027T1 (en)
DE (2) DE19858031A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007032707A1 (en) 2007-07-13 2009-01-15 Mtu Aero Engines Gmbh Run-in coating producing method for tip of rotating blade of turbo machine i.e. gas turbine, involves diffusion-heat treating component i.e. stator-sided housing section, in region of surface and hollow balls to connect balls with surface
EP2196632A2 (en) 2008-12-10 2010-06-16 Rolls-Royce plc A seal in a gas turbine and a method of manufacturing a seal
DE102009016803A1 (en) 2009-04-09 2010-10-14 Rolls-Royce Deutschland Ltd & Co Kg Labyrinth rubbing seal for a turbomachine
DE102011014292A1 (en) * 2011-03-17 2012-09-20 Rolls-Royce Deutschland Ltd & Co Kg Intermediate level sealing ring for gas turbine engine, is made of metal foam, and has element, which is made of wear-resistant material that is arranged in metal foam, where inner platform is provided for supporting guide vanes
EP2873811A1 (en) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Abradable material based on metal fibres

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1448874B1 (en) 2001-09-25 2007-12-26 ALSTOM Technology Ltd Joint system for reducing a sealing space in a rotary gas turbine
DE10360164A1 (en) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gas turbine component
DE102008007321A1 (en) 2008-02-02 2009-08-13 Mtu Aero Engines Gmbh Device, particularly gas turbine, has rotor and housing encompassing rotor, where rubbing seal is arranged between rotor and wall section of housing opposite rotor
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
GB0912796D0 (en) 2009-07-23 2009-08-26 Cummins Turbo Tech Ltd Compressor,turbine and turbocharger
DE102013219766A1 (en) 2013-09-30 2015-04-16 Siemens Aktiengesellschaft Adhesive seal and seal arrangement

Citations (1)

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US4392656A (en) * 1979-10-26 1983-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Air-cooled sealing rings for the wheels of gas turbines

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US4177308A (en) * 1978-08-10 1979-12-04 The United States Of America As Represented By The Secretary Of The Air Force Non-combustible high temperature abradable seal material
US4433845A (en) 1981-09-29 1984-02-28 United Technologies Corporation Insulated honeycomb seal
DE3203869C2 (en) * 1982-02-05 1984-05-10 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbine rotor blades for turbo machines, in particular gas turbine engines
US5350557A (en) * 1991-09-23 1994-09-27 Technetics Corp. Impermeable, abradable seal and method for the production thereof
DE4241420C1 (en) * 1992-12-09 1993-11-25 Mtu Muenchen Gmbh Process for the production of components or substrates with composite coatings and its application
US5388959A (en) 1993-08-23 1995-02-14 General Electric Company Seal including a non-metallic abradable material
DE19750516A1 (en) * 1997-11-14 1999-05-20 Asea Brown Boveri Abradable seal

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4392656A (en) * 1979-10-26 1983-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Air-cooled sealing rings for the wheels of gas turbines

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007032707A1 (en) 2007-07-13 2009-01-15 Mtu Aero Engines Gmbh Run-in coating producing method for tip of rotating blade of turbo machine i.e. gas turbine, involves diffusion-heat treating component i.e. stator-sided housing section, in region of surface and hollow balls to connect balls with surface
EP2196632A2 (en) 2008-12-10 2010-06-16 Rolls-Royce plc A seal in a gas turbine and a method of manufacturing a seal
US8650753B2 (en) 2008-12-10 2014-02-18 Rolls-Royce, Plc Seal and a method of manufacturing a seal
DE102009016803A1 (en) 2009-04-09 2010-10-14 Rolls-Royce Deutschland Ltd & Co Kg Labyrinth rubbing seal for a turbomachine
EP2241724A2 (en) 2009-04-09 2010-10-20 Rolls-Royce Deutschland Ltd & Co KG Labyrinth abradable seal for a turbomachine
DE102011014292A1 (en) * 2011-03-17 2012-09-20 Rolls-Royce Deutschland Ltd & Co Kg Intermediate level sealing ring for gas turbine engine, is made of metal foam, and has element, which is made of wear-resistant material that is arranged in metal foam, where inner platform is provided for supporting guide vanes
EP2873811A1 (en) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Abradable material based on metal fibres
DE102013223585A1 (en) 2013-11-19 2015-06-03 MTU Aero Engines AG Inlet lining based on metal fibers

Also Published As

Publication number Publication date
EP1013890A2 (en) 2000-06-28
DE59908461D1 (en) 2004-03-11
DE19858031A1 (en) 2000-06-21
EP1013890A3 (en) 2001-11-07
ATE259027T1 (en) 2004-02-15

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