EP2063072A2 - Dispositif d'étanchéité d'une turbomachine et procédé d'application d'un revêtement protecteur sur un composant de cette turbomachine - Google Patents

Dispositif d'étanchéité d'une turbomachine et procédé d'application d'un revêtement protecteur sur un composant de cette turbomachine Download PDF

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Publication number
EP2063072A2
EP2063072A2 EP08169608A EP08169608A EP2063072A2 EP 2063072 A2 EP2063072 A2 EP 2063072A2 EP 08169608 A EP08169608 A EP 08169608A EP 08169608 A EP08169608 A EP 08169608A EP 2063072 A2 EP2063072 A2 EP 2063072A2
Authority
EP
European Patent Office
Prior art keywords
armor
sealing system
based alloy
component
particles
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Withdrawn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
EP08169608A
Other languages
German (de)
English (en)
Other versions
EP2063072A3 (fr
Inventor
Manuel Hertter
Andreas Jakimov
Stefan Schneiderbanger
Ralf Stolle
Wolfgang Wachter
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 EP2063072A2 publication Critical patent/EP2063072A2/fr
Publication of EP2063072A3 publication Critical patent/EP2063072A3/fr
Withdrawn legal-status Critical Current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
    • F01D11/125—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 with a reinforcing structure
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/11—Iron
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness

Definitions

  • the invention relates to a sealing system of a turbomachine, in particular a gas turbine, according to the preamble of claim 1. Furthermore, the invention relates to a method for applying armor to a component of a turbomachine according to the preamble of claim 11.
  • Turbomachines such as gas turbines, typically include a plurality of rotating blades and a plurality of stationary vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a stationary housing.
  • a stationary housing typically includes a plurality of rotating blades and a plurality of stationary vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a stationary housing.
  • sealing systems include the so-called sealing systems.
  • the US 6,194,086 B1 discloses a blade of a gas turbine having a blade tip armor, the blade tip armor comprising a cover layer formed of abrasive particles incorporated in a metallic matrix material.
  • the present invention is based on the problem to provide a novel sealing system of a turbomachine, in particular a gas turbine, as well as a novel method for applying armor to a component of a turbomachine.
  • the rotating component is made of a relatively soft material, namely a titanium-based alloy or an aluminum-based alloy or a magnesium-based alloy; b) the armor associated with the rotating component made of a relatively hard material, namely a nickel-based alloy or iron-based alloy; and c) the inlet facing associated with the fixed component is made of an erosion-resistant material having a lower hardness than the relatively hard material of the armor.
  • FIG. 1 shows a schematic representation of a sealing system according to the invention of a turbomachine in the region of a rotor-side rotor blade 10, which is associated with armor 11 at a tip, and a stator-side housing 12, which is associated with an inlet lining 13, wherein the inlet lining 13 of the armor 11 adjacent is.
  • the sealing system of FIG. 1 is used to seal a gap 14 between the blade 10 and the housing 12.
  • the blade 10 runs this with their armor 11 in the housing 12 associated inlet lining 13 a.
  • the rotor-side moving blade 10 is made of a relatively soft material, namely a titanium-based alloy or an aluminum-based alloy or a magnesium-based alloy.
  • the blade 10 associated armor 11 is made of a relatively hard material, namely a nickel-based alloy or an iron-based alloy.
  • the housing 12 associated with inlet lining 13 is made of an erosion-resistant material having a lower hardness than the relatively hard material of the armor 11.
  • the material of the inlet lining 13 preferably has a hardness of between 35 and 70 HR15Y, which refers to a measurement of the Rockwell hardness.
  • hard particles or abrasive particles may be incorporated, wherein as hard particles preferably particles of oxides or carbides or nitrides are embedded in the nickel-based alloy or iron-based alloy of the armor 11.
  • particles of cubic boron nitride are embedded in the nickel-based alloy or iron-based alloy of the armor 11 as hard-material particles.
  • the erosion-resistant material of the inlet lining 13 is preferably porous.
  • the material of the inlet lining 13 preferably consists of a metallic matrix, preferably of a NiCrAl alloy with an additive and / or solid lubricant embedded in it. wherein it is the additive to particles of particular bentonite, that is a ceramic material of an aluminum silicate.
  • the solid lubricant is advantageously hexagonal boron nitride or graphite.
  • the armor 11 is applied to the rotor-side blade 10 via cold-kinetic compacting or kinetic cold gas spraying on the rotor-side blade 10.
  • the application of the armor 11 on the rotating component, namely, as shown in FIG. 1, the rotor-side blade 10, via cold-kinetic compaction or kinetic cold gas spraying is preferably carried out at a gas temperature between 300 and 950 ° C and at a pressure between 30 and 40 bar , As the process gas in particular nitrogen is used.
  • the heating of the particles takes place by preheating the gas before receiving the particles and by a heat exchanger just before exiting the spray gun.
  • the cold-kinetic compaction or kinetic cold gas spraying is carried out at a speed between 500 and 1500 m / sec, which is the speed with the aid of these contained in a carrier gas particles of the material of the armor for making the armor 11 are directed to the blade 10.
  • Nitrogen is preferably used as carrier gas for cold-kinetic compaction or kinetic cold gas spraying.
  • particles of the material of the armor 11 are applied to the rotor-side blade via the carrier gas, wherein the particles contained in the carrier gas have a particle size between 5 and 80 microns.
  • the maximum of a Gaussian distribution for the particle size of the particles contained in the carrier gas is preferably about 30 ⁇ m.
  • the over cold-kinetic compaction or kinetic cold gas spraying applied to the blade 10 armor 11 preferably has a thickness between 0.05 and 1.5 mm. Furthermore, the armor 11 preferably has an extremely low porosity with a density between in particular 98 and 100%.
  • the sealing system according to the invention has been described with reference to FIG. 1 using the example of a rotor blade 10 and a housing 12 for sealing a gap between the rotor blade 10 and the housing 12, the sealing system according to the invention is not limited to this application, but can be combined with the sealing system according to the invention also other gaps between rotating and stationary components are sealed.
  • the armor 11 may also be applied to a rotor-side Dichtfin, which enters an inlet lining in the region stator-side vanes.
  • the production of armor by cold-kinetic compaction or kinetic cold gas spraying has the advantage that on the one hand the armor can be produced with high precision by means of a thin spray jet and furthermore relatively inexpensively.
  • the sealing system according to the invention it is possible to use in compressors blades made of a relatively soft material, namely a titanium-based alloy or aluminum-based alloy or magnesium-based alloy, wherein the applied over kinetic cold gas spraying or cold-kinetic compaction armor consists of a nickel-based alloy or iron-based alloy, and accordingly is relatively hard.
  • the armored blades thus enter into the inlet lining, which is formed of an erosion-resistant material having a greater hardness than the relatively soft material of the blades and having a lower hardness than the relatively hard material of the armor of the blades.
  • the sealing system according to the invention is characterized by a permanently lower wear.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08169608A 2007-11-23 2008-11-21 Dispositif d'étanchéité d'une turbomachine et procédé d'application d'un revêtement protecteur sur un composant de cette turbomachine Withdrawn EP2063072A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200710056452 DE102007056452A1 (de) 2007-11-23 2007-11-23 Dichtsystem einer Turbomaschine

Publications (2)

Publication Number Publication Date
EP2063072A2 true EP2063072A2 (fr) 2009-05-27
EP2063072A3 EP2063072A3 (fr) 2011-03-09

Family

ID=40191089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08169608A Withdrawn EP2063072A3 (fr) 2007-11-23 2008-11-21 Dispositif d'étanchéité d'une turbomachine et procédé d'application d'un revêtement protecteur sur un composant de cette turbomachine

Country Status (2)

Country Link
EP (1) EP2063072A3 (fr)
DE (1) DE102007056452A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011141017A3 (fr) * 2010-05-08 2012-03-01 Mtu Aero Engines Gmbh Revêtement d'usure d'une turbomachine et son procédé de fabrication
EP2574727A1 (fr) * 2011-09-27 2013-04-03 United Technologies Corporation Joint d'extrémité d'aube avec barrière thermique intégrante, moteur à turbine à gaz et procédé de fabrication associés
CN106148879A (zh) * 2016-08-18 2016-11-23 沈阳理工大学 一种镍Ni60基含钴和铬金属等离子喷涂轴类零件耐磨涂层的制备方法
EP3239467A1 (fr) * 2016-04-27 2017-11-01 Siemens Aktiengesellschaft Aube mobile et turbomachine et carter

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010052729B4 (de) 2010-11-26 2016-01-21 MTU Aero Engines AG Oxidationsbeständige Panzerung von Schaufelspitzen
DE102011084990A1 (de) * 2011-10-21 2013-04-25 Mahle International Gmbh Kolben sowie tribologisches System aus einem Kolben und einer Zylinderlauffläche eines Zylinderkurbelgehäuses für einen Verbrennungsmotor
DE102014213911A1 (de) 2014-07-17 2016-01-21 MTU Aero Engines AG Aerogel-Auskleidungselement für Strömungsmaschinen
EP3216980A1 (fr) 2016-03-08 2017-09-13 Siemens Aktiengesellschaft Procede de fabrication ou de reparation d'une aube et/ou d'un carter d'une turbomachine
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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6194086B1 (en) 1997-11-06 2001-02-27 Chromalloy Gas Turbine Corporation Method for producing abrasive tips for gas turbine blades

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US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
US5476363A (en) * 1993-10-15 1995-12-19 Charles E. Sohl Method and apparatus for reducing stress on the tips of turbine or compressor blades
EP1391537B1 (fr) * 2001-05-31 2012-02-22 Mitsubishi Heavy Industries, Ltd. Procede et materiau de formage de revetement, et feuille de formage de revetement abrasif
FR2829524B1 (fr) * 2001-09-11 2004-03-05 Snecma Moteurs Procede de realisation de parties d'extremite radiales de pieces mobiles de turbomachines
US6916529B2 (en) * 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
DE10356953B4 (de) * 2003-12-05 2016-01-21 MTU Aero Engines AG Einlaufbelag für Gasturbinen sowie Verfahren zur Herstellung desselben
US20060134321A1 (en) * 2004-12-22 2006-06-22 United Technologies Corporation Blade platform restoration using cold spray
US7836591B2 (en) * 2005-03-17 2010-11-23 Siemens Energy, Inc. Method for forming turbine seal by cold spray process

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6194086B1 (en) 1997-11-06 2001-02-27 Chromalloy Gas Turbine Corporation Method for producing abrasive tips for gas turbine blades

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011141017A3 (fr) * 2010-05-08 2012-03-01 Mtu Aero Engines Gmbh Revêtement d'usure d'une turbomachine et son procédé de fabrication
DE102010019958B4 (de) * 2010-05-08 2016-05-04 MTU Aero Engines AG Verfahren zur Herstellung eines Einlaufbelags
EP2574727A1 (fr) * 2011-09-27 2013-04-03 United Technologies Corporation Joint d'extrémité d'aube avec barrière thermique intégrante, moteur à turbine à gaz et procédé de fabrication associés
US8777562B2 (en) 2011-09-27 2014-07-15 United Techologies Corporation Blade air seal with integral barrier
EP3239467A1 (fr) * 2016-04-27 2017-11-01 Siemens Aktiengesellschaft Aube mobile et turbomachine et carter
CN106148879A (zh) * 2016-08-18 2016-11-23 沈阳理工大学 一种镍Ni60基含钴和铬金属等离子喷涂轴类零件耐磨涂层的制备方法

Also Published As

Publication number Publication date
EP2063072A3 (fr) 2011-03-09
DE102007056452A1 (de) 2009-05-28

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