EP1654441B1 - Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement - Google Patents

Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement Download PDF

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Publication number
EP1654441B1
EP1654441B1 EP04762528A EP04762528A EP1654441B1 EP 1654441 B1 EP1654441 B1 EP 1654441B1 EP 04762528 A EP04762528 A EP 04762528A EP 04762528 A EP04762528 A EP 04762528A EP 1654441 B1 EP1654441 B1 EP 1654441B1
Authority
EP
European Patent Office
Prior art keywords
coating
run
titanium
housing
aluminium
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
EP04762528A
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German (de)
English (en)
Other versions
EP1654441A1 (fr
Inventor
Erwin Bayer
Wilfried Smarsly
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines 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 MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1654441A1 publication Critical patent/EP1654441A1/fr
Application granted granted Critical
Publication of EP1654441B1 publication Critical patent/EP1654441B1/fr
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
    • F01D11/122—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 erodable or abradable material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12389—All metal or with adjacent metals having variation in thickness

Definitions

  • the invention relates to an inlet lining for gas turbines according to the preamble of patent claim 1, as from the publication US 4,155,755 A and US 5667898 is known. Furthermore, the invention relates to a method for producing a Einlaufbelags according to the preamble of claim 9.
  • Gas turbines such as aircraft engines, typically include a plurality of rotating blades and a plurality of fixed vanes, the blades rotating together with a rotor, and wherein the blades and the vanes are enclosed by a fixed housing of the gas turbine.
  • sealing systems include the so-called sealing systems in aircraft engines.
  • Particularly problematic in aircraft engines is keeping clean a minimum gap between the rotating blades and the stationary housing of a high pressure compressor. Namely, the highest absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing of the compressor. This is partly due to the fact that in compressor blades on shrouds, such as those used in turbines, is dispensed with.
  • blades in the compressor have no shroud.
  • tips of the rotating blades are exposed to direct frictional contact with the housing during so-called rubbing into the stationary housing.
  • Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances.
  • As is removed by the frictional contact of the tips of the rotating blades on the same material can over the entire circumference of the housing and rotor set an undesirable gap magnification.
  • the present invention is based on the problem of creating a novel inlet lining for gas turbines.
  • the inlet lining for gas turbines serves to seal a radial gap between a stationary housing of the gas turbine and rotating blades thereof.
  • the inlet lining is attached to the housing.
  • the inlet lining is produced from an intermetallic titanium-aluminum material, wherein the inlet lining made of the Ti-Al material has a graduated or graded material composition over the thickness of the inlet lining.
  • the inlet lining of the titanium-aluminum material has a graded or graded porosity.
  • the inlet lining in an inner, directly adjacent to the housing area and at an outer, immediately adjacent to the blades lying area is less porous than between these two areas.
  • the inlet lining is accordingly denser and harder on the inner region immediately adjacent to the housing and on the outer region immediately adjacent to the rotor blades.
  • the inner, immediately adjacent to the housing area serves to provide adhesion; the outer area immediately adjacent the blades serves to provide erosion protection.
  • Fig. 1 shows a highly schematic of a rotating blade 10 of a gas turbine, which rotates relative to a fixed housing 11 in the direction of the arrow 12.
  • an inlet lining 13 is arranged on the housing 11.
  • the inlet lining 13 serves to seal a radial gap between a tip or end 14 of the rotating blade 10 and the stationary housing 11.
  • the requirements placed on such an inlet lining are very complex.
  • the inlet lining must have an optimized abrasion behavior, ie it must be ensured good chip formation and Entfemles the abrasion.
  • no transfer of material to the rotating blades 10 may take place.
  • the inlet lining 13 must furthermore have a low frictional resistance.
  • the inlet lining 13 must not ignite when rubbed by the rotating blades 10.
  • its here the erosion resistance, temperature resistance, thermal shock resistance, corrosion resistance to lubricants and seawater exemplified.
  • Fig. 1 illustrates that due to the centrifugal forces occurring during operation of the gas turbine and the heating of the gas turbine, the ends 14 of the blades 10 come into contact with the inlet lining 13 and so an abrasion 15 is released. This pulverized abrasion 15 must not cause any damage to the rotating blades 10.
  • housing 11 is in the preferred embodiment, the housing of a high pressure compressor.
  • Such housing of high-pressure compressors are increasingly made of intermetallic materials of the type TiAl or Ti 3 Al.
  • Such titanium-aluminum intermetallic materials have a lower density and are superior in temperature resistance to conventional titanium alloys.
  • an inlet lining 13 also applied from an intermetallic titanium-aluminum material. It should be noted that such an inlet lining of an intermetallic titanium-aluminum material can also be applied to a housing which consists of a conventional titanium alloy.
  • the inlet lining 13 of the intermetallic titanium-aluminum material has a stepped, i. gradually changing, or over a graded, i. over a nearly infinitely variable, material composition and / or porosity.
  • a stepped, i. gradually changing, or over a graded, i. over a nearly infinitely variable, material composition and / or porosity By the targeted adjustment of the material composition and / or porosity, the properties of the inlet lining 13 can be adapted to the specific requirements of the same.
  • the inlet lining 13 has a low porosity in an inner region 16 immediately adjacent to the housing 11, as well as in an outer region 17 immediately adjacent to the moving blades 10. Between this inner region 16 and this outer region 17, on the other hand, the porosity of the inlet lining is increased.
  • the inner, directly on the housing 11 adjacent area 16 of the inlet lining 13 serves for bonding between inlet lining 13 and housing 11.
  • the outer, immediately adjacent to the blades 10 area 17 of the inlet lining 13 forms an erosion protection. Depending on the requirements of the inlet lining 13, however, this erosion protection can also be dispensed with.
  • the ratio of titanium and aluminum within the inlet lining 13 produced from the intermetallic titanium-aluminum material is preferably approximately constant. This means that in this case only the porosity of the inlet lining 13 is graded or graded to influence the hardness and strength thereof.
  • the ratio of titanium and aluminum within the inlet lining 13 is graded or graded.
  • more titanium is preferably contained in the inner lining immediately adjacent to the housing 11 in the inlet lining 13 than in the outer region 17 of the inlet lining 13. This means that in the outer region 17 of the inlet lining 13 more aluminum is contained than in the inner region 16 thereof, which is adjacent to the housing 11.
  • an inlet lining of a titanium-aluminum intermetallic material on a housing which is also formed of an intermetallic titanium-aluminum material or a titanium alloy, has the advantage that the connection of the inlet lining to the housing takes place via chemical bonds and so that the connection is safer and more durable than with inlet coverings according to the prior art. Furthermore, there will be no high-temperature diffusion between the housing and the inlet lining between an inlet lining and a housing, which have the same basic composition. Furthermore, there are no thermal expansion problems, since the housing and inlet lining evenly expand or contract with temperature increase or decrease in temperature. As a result, a more uniform gap position and a longer service life of the inlet lining can be achieved.
  • An inventively formed inlet lining further has a high oxidation resistance and high thermal shock resistance. The blade tips of the rotating blades are subject to minimal blade tip abrasion.
  • the inlet lining 13 by providing the inlet lining 13 in the form of a slip material and applying it to the housing 11 using the slip technique.
  • a slip material based on an intermetallic Titanium-aluminum material is preferably applied to the housing 11 by brushing, dipping or spraying. This is preferably done in several steps or layers, so that a multi-layer inlet lining 13 is formed.
  • additional materials are incorporated into the slip material.
  • hardening or burning in of the slip material takes place on the housing 11.
  • the additives added to the slip material evaporate, as a result of which the pores within the inlet lining 13 remain.
  • the number and type of added additives allows the porosity, namely the number and size of the pores, to be adjusted.
  • the run-in pad 13 can also be made by applying it using a directional matter vapor jet.
  • a directed matter vapor jet may be generated by a PVD (Physical Vapor Deposition) process or a CVD (Chemical Vapor Deposition) process.
  • PVD Physical Vapor Deposition
  • CVD Chemical Vapor Deposition
  • the porosity adjunct additives may be so-called microballs, i. filled or hollow plastic beads, polystyrene beads, or other materials that vaporize upon firing of the titanium-aluminum intermetallic material.
  • the inlet lining according to the invention can be produced particularly favorable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Claims (15)

  1. Revêtement de rodage pour turbines à gaz, destiné à rendre étanche une fente radiale entre un carter (11) de la turbine à gaz et des aubes mobiles (10) rotatives de ladite turbine à gaz, ledit revêtement de rodage (13) étant appliqué sur le carter (11), ledit revêtement de rodage (13) étant constitué d'un matériau intermétallique titane-aluminium, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium présente une composition échelonnée ou graduelle et/ou une porosité échelonnée sur l'épaisseur du revêtement de rodage.
  2. Revêtement de rodage selon la revendication 1, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est prévu avec une porosité sur une zone opposée au carter (11) inférieure à celle d'une zone opposée aux aubes mobiles (10) rotatives.
  3. Revêtement de rodage selon l'une ou plusieurs des revendications 1 et 2, caractérisé en ce que ledit revêtement de rodage (13) est, dans une zone intérieure, directement adjacente au carter (11) et sur une zone extérieure, directement adjacente aux aubes mobiles (10), prévu avec une porosité inférieure à celle présentée entre ces deux zones.
  4. Revêtement de rodage selon l'une ou plusieurs des revendications 1 à 3, caractérisé en ce que le rapport entre titane et aluminium est sensiblement constant à l'intérieur du revêtement de rodage (13), seule la porosité étant échelonnée ou graduelle pour la définition d'une densité et/ou d'une dureté et/ou d'une solidité de celui-ci.
  5. Revêtement de rodage selon l'une ou plusieurs des revendications 1 à 3, caractérisé en ce que le rapport entre titane et aluminium est lui aussi échelonné ou graduel à l'intérieur du revêtement de rodage (13), le revêtement de rodage (13) présentant, sur une zone opposée aux aubes mobiles (10) rotatives, une teneur en aluminium supérieure à celle d'une zone opposée au carter (11).
  6. Revêtement de rodage selon l'une ou plusieurs des revendications 1 à 5, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est appliqué sur un carter (11) en matériau intermétallique titane-aluminium.
  7. Revêtement de rodage selon la revendication 6, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est directement appliqué sur le carter (11) en matériau titane-aluminium.
  8. Procédé de fabrication d'un revêtement de rodage pour turbines à gaz, destiné à rendre étanche une fente radiale entre un carter (11) de la turbine à gaz et des aubes mobiles (10) rotatives de celle-ci, ledit revêtement de rodage (13) étant appliqué sur le carter (11), comportant les étapes suivantes :
    a) préparation d'un carter (11),
    b) application sur le carter du revêtement de rodage (13) en matériau intermétallique titane-aluminium,
    caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est appliqué de manière à présenter une composition échelonnée ou graduelle et/ou une porosité échelonnée sur l'épaisseur du revêtement de rodage.
  9. Procédé selon la revendication 8, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est appliqué de manière à présenter sur une zone opposée au carter (11) une porosité inférieure à celle d'une zone opposée aux aubes mobiles (10) rotatives.
  10. Procédé selon l'une ou plusieurs des revendications 8 et 9, caractérisé en ce que ledit revêtement de rodage (13) en matériau titane-aluminium est appliqué sur un carter (11) en matériau intermétallique titane-aluminium.
  11. Procédé selon l'une ou plusieurs des revendications 8 à 10, caractérisé en ce qu'en liaison avec l'étape b), le revêtement de rodage (13) est appliqué sur le carter (11) de telle manière qu'au moins une couche d'un matériau de barbotine titane-aluminium est appliquée à cet effet sur le carter (11), la couche, ou chaque couche du matériau de barbotine titane-aluminium étant ensuite durcie par cuisson.
  12. Procédé selon la revendication 11, caractérisé en ce que des matériaux additifs sont incorporés dans la couche, ou dans chaque couche du matériau de barbotine titane-aluminium, lesdits matériaux additifs étant vaporisés lors de la cuisson en formant alors les pores à l'intérieur de la couche, ou de chaque couche du revêtement de rodage (13).
  13. Procédé selon la revendication 11 ou la revendication 12, caractérisé en ce que la couche, ou chaque couche du matériau de barbotine titane-aluminium est appliquée au pinceau, ou par plongée ou par pulvérisation.
  14. Procédé selon l'une ou plusieurs des revendications 8 à 10, caractérisé en ce qu'en liaison avec l'étape b), le revêtement de rodage (13) est appliqué sur le carter (11) de telle manière qu'au moins une couche titane-aluminium est appliquée à cet effet sur le carter (11) par jet de vapeur de matériau orienté, en particulier jet de matériau PVD, la couche, ou chaque couche du jet de matériau étant ensuite durcie par cuisson.
  15. Procédé selon la revendication 14, caractérisé en ce que peu avant l'incidence du jet de vapeur de matériau titane-aluminium orienté, des matériaux additifs sont introduits dans le jet de vapeur de matériau titane-aluminium, lesdits matériaux additifs étant vaporisés lors de la cuisson en formant alors les pores à l'intérieur de la couche, ou de chaque couche du revêtement de rodage (13).
EP04762528A 2003-08-12 2004-07-28 Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement Expired - Lifetime EP1654441B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10337094A DE10337094A1 (de) 2003-08-12 2003-08-12 Einlaufbelag für Gasturbinen sowie Verfahren zur Herstellung desselben
PCT/DE2004/001683 WO2005014979A1 (fr) 2003-08-12 2004-07-28 Revetement de rodage pour turbines a gaz compose d'un materiau titane-aluminium

Publications (2)

Publication Number Publication Date
EP1654441A1 EP1654441A1 (fr) 2006-05-10
EP1654441B1 true EP1654441B1 (fr) 2012-08-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP04762528A Expired - Lifetime EP1654441B1 (fr) 2003-08-12 2004-07-28 Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement

Country Status (4)

Country Link
US (1) US7699581B2 (fr)
EP (1) EP1654441B1 (fr)
DE (1) DE10337094A1 (fr)
WO (1) WO2005014979A1 (fr)

Families Citing this family (12)

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Publication number Priority date Publication date Assignee Title
DE102006050789A1 (de) * 2006-10-27 2008-04-30 Mtu Aero Engines Gmbh Aufgedampfte Beschichtung und thermisch belastbares Bauteil mit einer solchen Beschichtung, sowie Verfahren und Vorrichtung zur Herstellung einer solchen Beschichtung
DE102007025949A1 (de) * 2007-06-04 2008-12-11 Federal-Mogul Burscheid Gmbh Kolbenring mit gradierten Schichten
US8257016B2 (en) 2008-01-23 2012-09-04 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with a compressor with self-healing abradable coating
DE102008005482A1 (de) * 2008-01-23 2009-07-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit einem Verdichter mit selbstheilender Einlaufschicht
EP2202264B1 (fr) 2008-12-24 2018-04-18 Safran Aero Boosters SA Procédé de fabrication par moulage d'un élément structurel de machine avec une surface abradable
JP5210984B2 (ja) * 2009-06-29 2013-06-12 株式会社日立製作所 タービン用高信頼性メタルシール材
GB0911500D0 (en) * 2009-07-03 2009-08-12 Rolls Royce Plc Rotor blade over-tip leakage control
DE102009036407A1 (de) 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Abreibbarer Schaufelspitzenbelag
US20160003083A1 (en) * 2013-02-19 2016-01-07 United Technologies Corporation Abradable seal including an abradability characteristic that varies by locality
US20150093237A1 (en) * 2013-09-30 2015-04-02 General Electric Company Ceramic matrix composite component, turbine system and fabrication process
EP3222812A1 (fr) * 2016-03-24 2017-09-27 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube directrice, aube directrice, procede de fabrication ou de reparation d'un boitier d'une turbomachine et boitier
DE102016224532A1 (de) 2016-12-08 2018-06-14 MTU Aero Engines AG Hochtemperaturschutzschicht für Titanaluminid-Legierungen

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US4155755A (en) * 1977-09-21 1979-05-22 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
EP0187612B1 (fr) * 1984-12-24 1990-09-12 United Technologies Corporation Joint d'étanchéité abrasable ayant une résistance élevée à l'érosion
US5667898A (en) * 1989-01-30 1997-09-16 Lanxide Technology Company, Lp Self-supporting aluminum titanate composites and products relating thereto
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EP0526670B1 (fr) * 1991-06-21 1995-10-25 Praxair S.T. Technology, Inc. Revêtements doubles pour substrats variés
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DE10150948C1 (de) * 2001-10-11 2003-05-28 Fraunhofer Ges Forschung Verfahren zur Herstellung gesinterter poröser Körper
US6982126B2 (en) * 2003-11-26 2006-01-03 General Electric Company Thermal barrier coating

Also Published As

Publication number Publication date
US7699581B2 (en) 2010-04-20
DE10337094A1 (de) 2005-03-03
WO2005014979A1 (fr) 2005-02-17
US20090110560A1 (en) 2009-04-30
EP1654441A1 (fr) 2006-05-10

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