EP1654441A1 - Revetement de rodage pour turbines a gaz compose d'un materiau titane-aluminium - Google Patents

Revetement de rodage pour turbines a gaz compose d'un materiau titane-aluminium

Info

Publication number
EP1654441A1
EP1654441A1 EP04762528A EP04762528A EP1654441A1 EP 1654441 A1 EP1654441 A1 EP 1654441A1 EP 04762528 A EP04762528 A EP 04762528A EP 04762528 A EP04762528 A EP 04762528A EP 1654441 A1 EP1654441 A1 EP 1654441A1
Authority
EP
European Patent Office
Prior art keywords
titanium
housing
aluminum
inlet lining
inlet
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.)
Granted
Application number
EP04762528A
Other languages
German (de)
English (en)
Other versions
EP1654441B1 (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
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 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 - Fee Related legal-status Critical Current

Links

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.
  • the invention further relates to a method for producing an inlet lining according to the preamble of patent claim 9.
  • Gas turbines such as aircraft engines, as a rule, comprise a plurality of rotating rotor blades and a plurality of stationary guide vanes, the rotor blades rotating together with a rotor and the rotor blades and the guide vanes being enclosed by a stationary housing of the gas turbine.
  • This also includes the so-called sealing systems in aircraft engines. Maintaining a minimal gap between the rotating blades and the fixed housing of a high-pressure compressor is particularly problematic in aircraft engines. In the case of high-pressure compressors, the greatest absolute temperatures and temperature gradients occur, which makes it difficult to maintain the gaps between the rotating blades and the stationary housing of the compressor.
  • shrouds such as those used in turbines are not used in compressor rotor blades.
  • blades in the compressor do not have a shroud.
  • the ends or tips of the rotating blades are therefore exposed to a direct frictional contact with the housing when they are rubbed into the fixed housing.
  • Such a rubbing of the tips of the rotor blades into the housing is caused by manufacturing tolerances when a minimal radial gap is set. Since the friction of the tips of the rotating blades removes the same material, an undesirable increase in gap can occur over the entire circumference of the housing and rotor.
  • the present invention is based on the problem of creating a new inlet lining for gas turbines.
  • the inlet lining for gas turbines serves to seal a radial gap between a fixed housing of the gas turbine and rotating rotor blades.
  • the inlet lining is attached to the housing.
  • According to the inlet lining is made of an intermetallic titanium-aluminum material.
  • the inlet lining made of the titanium-aluminum material has a graded or graded material composition and / or porosity.
  • a particularly preferred embodiment is one in which the inlet lining is less porous in an inner region directly adjacent to the housing and in an outer region directly adjacent to the blades than between these two regions.
  • the inlet lining is therefore made denser and harder on the inner region immediately adjacent to the housing and on the outer region directly adjacent to the rotor blades.
  • the inner area immediately adjacent to the housing is used to impart adhesion; the outer area immediately adjacent to the blades serves to provide erosion protection.
  • the method according to the invention for producing an inlet covering is defined in independent claim 9.
  • Fig. 1 shows a highly schematic of a rotating blade 10 of a gas turbine, which rotates in the direction of arrow 12 relative to a fixed housing 11.
  • An inlet covering 13 is arranged on the housing 11.
  • the inlet lining 13 serves to seal a radial gap between a tip or an end 14 of the rotating rotor blade 10 and the fixed housing 11.
  • the requirements placed on such an inlet lining are very complex.
  • the run-in covering must have an optimized abrasion behavior, ie good chip formation and removal of the abrasion must be guaranteed.
  • no material transfer to the rotating blades 10 may take place.
  • the inlet lining 13 must also have a low frictional resistance.
  • the inlet coating 13 must not ignite when brushed against by the rotating blades 10.
  • 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.
  • the housing 11 shown schematically in FIG. 1 is, according to the preferred embodiment, the housing of a high-pressure compressor.
  • Such housings of high-pressure compressors increasingly consist of intermetallic materials of the type TiAl or Ti 3 AI.
  • Such intermetallic titanium-aluminum materials have a lower density and are superior in terms of temperature resistance to conventional titanium alloys.
  • a run-in coating 13 likewise made of an intermetallic titanium-aluminum material to a housing 11 which is made from an intermetallic titanium-aluminum material. It should be pointed out that such an inlet lining made of an intermetallic titanium-aluminum material can also be applied to a housing which consists of a conventional titanium alloy.
  • the inlet lining 13 made of the intermetallic titanium-aluminum material has a graduated, i.e. gradually changing, or over a graded, i.e. about an almost continuously changing material composition and / or porosity.
  • a graduated i.e. gradually changing, or over a graded, i.e. about an almost continuously changing material composition and / or porosity.
  • the same has a low porosity in an inner region 16 directly adjacent to the housing 11, as well as in an outer region 17 directly adjacent to the blades 10. Between this inner region 16 and this outer region In contrast, area 17 increases the porosity of the inlet covering.
  • the inner region 16 of the inlet lining 13, which lies directly against the housing 11, serves to promote adhesion between the inlet lining 13 and the housing 11.
  • the outer region 17 of the inlet lining 13, which is directly adjacent to the blades 10, forms an erosion protection. Depending on the requirements of the running-in covering 13, however, this erosion protection can also be dispensed with.
  • the ratio of titanium and aluminum within the inlet lining 13 made from the intermetallic titanium-aluminum material is preferably approximately constant. This means that in this case only the porosity of the running-in coating 13 is graded or graded to influence the hardness and strength thereof.
  • the ratio of titanium and aluminum within the inlet lining 13 is graduated or graded.
  • more titanium is preferably contained in the inner area 16 directly adjacent to the housing 11 in the inlet lining 13 than in the outer area 17 of the inlet lining 13.
  • more aluminum is contained in the outer area 17 of the inlet lining 13 than in the inner one Area 16 of the same, which is adjacent to the housing 1 1.
  • an inlet lining made of an intermetallic titanium-aluminum material on a housing which is also made 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 permanent than with the leading-edge coverings according to the state of the art. Furthermore, there will be no high-temperature diffusion between the housing and the inlet lining between an inlet lining and a housing that have the same basic composition. Furthermore, there are no thermal expansion problems, since the housing and the inlet lining expand or contract evenly when the temperature rises or falls. This enables a more even gap and a longer lifespan for the inlet covering.
  • a running-in covering designed according to the invention also has a high resistance to oxidation and a high resistance to thermal cycling. The blade tips of the rotating blades are subject to minimal blade tip wear.
  • the inlet covering 13 by providing the inlet covering 13 in the form of a slip material and applying it to the housing 11 using the slip technology.
  • 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-layered inlet covering 13 is formed.
  • the slip material is cured or baked onto the housing 11.
  • the additives added to the slip material evaporate, as a result of which the pores remain within the run-in coating 13.
  • the porosity namely the number and size of the pores, can be set by the number and type of additives added.
  • the inlet covering 13 can also be produced by applying the same with the aid of a directed material vapor jet.
  • a directed material vapor jet can be generated using a PVD (Physical Vapor Deposition) process or a CVD (Chemical Vapor Deposition) process.
  • PVD Physical Vapor Deposition
  • CVD Chemical Vapor Deposition
  • the additives for adjusting the porosity can be so-called microballs, i.e. filled or hollow plastic beads, are polystyrene beads or other materials that evaporate when the intermetallic titanium-aluminum material is burned in.
  • the inlet covering according to the invention can be produced particularly inexpensively both with the aid of the slip technology and the PVD or CVD technology.

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)

Abstract

L'invention concerne un revêtement de rodage pour turbines à gaz, ce revêtement de routage servant à l'étanchéité d'une fente radiale entre le carter (11) de la turbine à gaz et les pales tournantes (10) de cette turbine, ledit revêtement de rodage (13) étant appliqué sur le carter. Selon l'invention, le revêtement de rodage (13) est constitué par un matériau intermétallique titane-aluminium, et sa composition et/ou sa porosité peut être graduée ou échelonnée. Les procédés pour réaliser ce revêtement de rodage font appel, par exemple, à la technique de la barbotine, du dépôt physique en phase gazeuse (PVD) et du dépôt chimique en phase vapeur (CVD).
EP04762528A 2003-08-12 2004-07-28 Revêtement de turbine à gaz et procédé de fabrication d'un tel revêtement Expired - Fee Related 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 true EP1654441A1 (fr) 2006-05-10
EP1654441B1 EP1654441B1 (fr) 2012-08-29

Family

ID=34112112

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04762528A Expired - Fee Related 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)

* Cited by examiner, † Cited by third party
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
DE102008005482A1 (de) * 2008-01-23 2009-07-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit einem Verdichter mit selbstheilender Einlaufschicht
US8257016B2 (en) 2008-01-23 2012-09-04 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with a compressor with self-healing abradable coating
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
EP2959115B1 (fr) * 2013-02-19 2019-08-21 United Technologies Corporation Joint abradable comprenant une caractéristique d'abradabilité qui varie en fonction de l'emplacement
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

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3340084A (en) * 1959-02-19 1967-09-05 Gen Electric Method for producing controlled density heterogeneous material
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
US5340783A (en) * 1989-01-30 1994-08-23 Lanxide Technology Company, Lp Method of producing self-supporting aluminum titanate composites and products relating thereto
US5667898A (en) * 1989-01-30 1997-09-16 Lanxide Technology Company, Lp Self-supporting aluminum titanate composites and products relating thereto
US5484665A (en) 1991-04-15 1996-01-16 General Electric Company Rotary seal member and method for making
ATE129544T1 (de) 1991-06-21 1995-11-15 Praxair Technology Inc Duplexbeschichtungen für verschiedene substrate.
DE19937577A1 (de) 1999-08-09 2001-02-15 Abb Alstom Power Ch Ag Reibungsbehaftete Gasturbinenkomponente
US6660405B2 (en) 2001-05-24 2003-12-09 General Electric Co. High temperature abradable coating for turbine shrouds without bucket tipping
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005014979A1 *

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
EP1654441B1 (fr) 2012-08-29

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