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EP0949410A2 - Conduit de transition revêtu pour une turbine à gaz - Google Patents

Conduit de transition revêtu pour une turbine à gaz Download PDF

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Publication number
EP0949410A2
EP0949410A2 EP99103176A EP99103176A EP0949410A2 EP 0949410 A2 EP0949410 A2 EP 0949410A2 EP 99103176 A EP99103176 A EP 99103176A EP 99103176 A EP99103176 A EP 99103176A EP 0949410 A2 EP0949410 A2 EP 0949410A2
Authority
EP
European Patent Office
Prior art keywords
layer
gas
mcraly
corrosion
oxidation
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
EP99103176A
Other languages
German (de)
English (en)
Other versions
EP0949410B1 (fr
EP0949410A3 (fr
Inventor
Sharad Dr.-Ing. Chandra
Bertold Dipl.-Ing. Ellermann
Heinz Dipl.-Ing. Gathmann
Werner Dipl.-Ing. Schnieders
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbomaschinen AG
GHH Borsig Turbomaschinen 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 MAN Turbomaschinen AG, GHH Borsig Turbomaschinen GmbH filed Critical MAN Turbomaschinen AG
Publication of EP0949410A2 publication Critical patent/EP0949410A2/fr
Publication of EP0949410A3 publication Critical patent/EP0949410A3/fr
Application granted granted Critical
Publication of EP0949410B1 publication Critical patent/EP0949410B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/325—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with layers graded in composition or in physical properties
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2300/15—Rare earth metals, i.e. Sc, Y, lanthanides

Definitions

  • the invention relates to a gas collection pipe carrying hot gas a gas turbine between the combustion chamber and the Turbine blade inlet flange from one highly warm and corrosion-resistant base metal M (Substrate) with one applied on the inside High temperature corrosion and oxidation layer.
  • the two-arm gas collection or Downpipe between the combustion chamber housing and the Inlet connection of the turbine blades in hot operation extreme stress and increased wear exposed to temperature, pressure and corrosion.
  • the combustion air is high in a compressor Pressure compresses, a substantial part of which two combustion chambers for combustion, a smaller one Share used to cool the hot metal parts becomes.
  • the substantial amount of O 2 in the air is oxidized by burning a carbon carrier, nitrogen remains in the exhaust gas as ballast and is also brought to high temperatures by the combustion process at high pressure and flows out of the combustion chambers into the downpipe and from there into the turbine on the turbine inlet blades and sets them in increased rotation.
  • the gas collection or downpipe is made of an iron-nickel base material. This is due to high pressure and especially due to an increased gas temperature attacked, leaving oxygen on the metal surface oxidized.
  • the alloying elements of the Ni-based alloy like Aluminum, chromium or the like reduce one further oxidation through the formation of solid oxide layers.
  • This passive oxide layer does not prevent Penetration of nitrogen, so that over time the nitrogen with the above-mentioned alloying elements Nitrides or carbon nitrides can form whose Formation thermodynamically due to the higher pressure of the gas is favored.
  • This mechanism does not only take place in the combustion chamber of the downpipe, but also in the cooling air applied external surface, which is not always so can be cooled far that the said gas metal reaction cannot take place.
  • the HKO layer develops through the increased Cr and Al contents in connection with yttrium have a large resistance potential against oxidation and nitriding and thus an increased high temperature corrosion and -oxidation resistance.
  • TBC Thermal Barrier Coating
  • the thermal barrier coating is a plasma spray coating system, consisting of an adhesive layer and a ceramic top layer, which is the thermal insulation of the Layer system causes.
  • the adhesive layer serves in addition to the liability of the Top layer also to avoid high temperature corrosion / oxidation of the material. To both functions To be able to optimally fulfill this adhesive layer from a two-layer MCrAlY layer, one so-called adhesive layers A and B.
  • the adhesive layer A is a ductile MCrAlY layer with lowered chrome and aluminum content to long term to ensure optimal adhesion to the substrate.
  • the adhesive layer B is a MCrAlY layer with an increased Chromium and aluminum content. This will next to the increased high temperature corrosion and oxidation resistance an embroidery of the base material prevented.
  • the top layer consists of a ZrO 2 -Y 2 -O 3 ceramic and, due to its lower thermal conductivity, provides thermal insulation for this layer.
  • WO 89/07159 describes multiple protective layers for Metal objects, in particular gas turbine blades, known. Based on the knowledge that there are two different Corrosion mechanisms exist for life such objects are important specified two superimposed protective layers, of which the inner against corrosion attacks Protects temperatures from 600 ° C to 800 ° C and the external against attacks at temperatures from 800 ° C to 900 ° C is optimized. In addition, can be as the extreme A thermal barrier layer is also present on the coating layer be. Preference is given to the first coating layer a diffusion layer with a chromium content greater than 50% and an iron and / or manganese content of more an MCrAlY layer as 10% and as a second coating layer with z. B. about 30% chromium, about 7% aluminum and about 0.7% yttrium by plasma spraying reduced pressure is applied.
  • a protective coating in particular, is known from WO 91/02108 known for gas turbine components, the good Corrosion properties in the temperature range of 600 up to about 1150 ° C.
  • the protective coating contains (in weight percent): 25 - 40% nickel, 28 - 32% Chromium, 7 - 9% aluminum, 1 - 2% silicon, 0.3 - 1% Yttrium; Balance cobalt, at least 5%; and inevitable Impurities. Different choice components can be added. By adding rhenium the properties of the protective coating be improved. This effect already occurs low additions. A range of is preferred 4 - 10% rhenium.
  • the coatings can be by plasma spraying or Evaporations (PVD) are applied and are special suitable for gas turbine blades made of a super alloy based on nickel or cobalt. Others too Gas turbine components, especially with gas turbines high inlet temperature of e.g. B. above 1200 ° C, can be provided with such protective coatings become.
  • WO 96/34128 is a nickel or cobalt metal alloy known to have a protective layer against increased temperature and corrosion attacks hot gases are applied from the combustion chamber of a gas turbine become.
  • the three-layer protective layer consists of one first binding layer made of an MCrAlY composition compared to the base metal to be protected and one second anchoring layer opposite the outer one Oxide layer.
  • a metal substrate is based on WO 96/34129 a nickel or cobalt alloy known to the one Protection system against increased temperature, corrosion and Erosion is applied.
  • the protection system consists of an intermediate layer, consisting of a binding layer against which Ni substrate and an anchoring layer opposite the outer ceramic layer based on zirconium oxide.
  • the outer ceramic layer serves as a thermal insulation layer.
  • the object of the invention is the gas metal reaction on the hot inner surface of the mixing tube prevent or delay so far that the life of this part is considerably extended and the gas metal reaction also on the cooled to prevent the outer surface of the mixing tube or delay so far that the lifespan of the Parts will be extended considerably.
  • the surfaces of the hot gas are therefore Gas collecting or downpipe between Combustion chamber housing and turbine both from the inside and also from the outside with a high temperature corrosion and -oxidation layer provided, which consists of a single layer MCrAlY layer exists, so that a gas metal reaction of nitrogen with the metal of the gas manifold is prevented or largely delayed.
  • the high temperature corrosion and oxidation layer containing 31% Cr, 11% Al, 0.6% Y and Residual nickel therefore has such high Cr and Al contents that a large resistance potential in the protective layer against oxidation and nitriding and thus an increased High temperature corrosion and oxidation resistance given is.
  • the coating of the complete downpipe - inside and outside - done manually or as program-controlled MCrAlY plasma coating in a layer thickness of 60 ⁇ 40 ⁇ m.
  • the inner cone of the gas manifold becomes at the transition the gas turbine also with a one-sided thermal insulation layer lined.
  • This insulation layer is known to consist of a two-layer MCrAlY layer - layers A and B - and one ceramic top layer.
  • the adhesive base layer A is a ductive MCrAlY layer with a reduced chromium and aluminum content by one Adhesion of this layer to the base material of the To ensure gas manifold.
  • the adhesive base layer B corresponds in the Composition of high temperature corrosion and -oxidation layer.
  • the thermal insulation layer is complemented by a Ceramic top layer (top coat) based on zirconia due to their low thermal conductivity, thermal insulation causes.
  • the thermal insulation layer exposes itself a layer thickness of 60/60/250 ⁇ m together.
  • the gas manifold is also on the two Entry openings with an anti-wear coating Mistake.
  • Fig. 1 shows a multidimensional view of the Gas collecting or downpipe (1) with in the upper area arranged inlet openings (2) for the hot gas the two combustion chambers, not shown.
  • the gas collecting tube (1) is both outside and inside with a high temperature corrosion and oxidation layer (4) lined.
  • the hot gas flows out of the two Combustion chambers through the inlet openings (2) in the Gas collecting tube (1), is in the lower gas collecting space (3) collected and leaves the gas manifold (1) direction Turbine, the gas collection tube (1) through a outer flange (5) and an inner flange (6) the counter flange of the turbine is connected.
  • Fig. 2 shows a section through the wall of the Down pipe with the high temperature corrosion and Oxidation (HKO) layer.
  • HKO high temperature corrosion and Oxidation
  • FIG 3 shows a section through the gas collecting tube (1), that between the combustion chamber housings, not shown and a downstream turbine is.
  • the hot and corrosive exhaust gas leaves the mixing tube of the Combustion chamber and flows through the inlet opening (2) into the gas collection tube (1), which is not within a shown housing between the flanges of the Combustion chamber housing and the flanges of the turbine is arranged.
  • Base metal (9) of the gas manifold (1) is outside cooled by a cooling medium.
  • the compressed hot gas is in the lower gas plenum (3) brought together between the flanges (5) and (6), before it flows into the turbine and the turbine runner set in rotation with the blades.
  • the inlet openings (2) of the gas collection tube (1) are with an anti-wear coating in the gas inlet area (7) provided.
  • the inner cone (13) is in the area of the flange instead of the HKO layer (4) with an additional Thermal insulation layer (8) lined.
  • thermal barrier coating (8) from a two-layer (A and B) MCrAlY layer, the A layer (10) opposite as an adhesive base layer the base metal (9) and the B layer (11) as an adhesive base layer opposite the ceramic layer (12) works.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99103176A 1998-04-07 1999-02-18 Conduit de transition revêtu pour une turbine à gaz Expired - Lifetime EP0949410B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19815473A DE19815473A1 (de) 1998-04-07 1998-04-07 Heißgasführendes Gassammelrohr einer Gasturbine
DE19815473 1998-04-07

Publications (3)

Publication Number Publication Date
EP0949410A2 true EP0949410A2 (fr) 1999-10-13
EP0949410A3 EP0949410A3 (fr) 2000-11-02
EP0949410B1 EP0949410B1 (fr) 2003-07-16

Family

ID=7863824

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99103176A Expired - Lifetime EP0949410B1 (fr) 1998-04-07 1999-02-18 Conduit de transition revêtu pour une turbine à gaz

Country Status (6)

Country Link
US (1) US6226978B1 (fr)
EP (1) EP0949410B1 (fr)
JP (1) JP3823282B2 (fr)
CN (1) CN1143056C (fr)
CA (1) CA2263834C (fr)
DE (2) DE19815473A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
EP2198064A1 (fr) * 2007-10-09 2010-06-23 Man Turbo Ag Composant traverse par du gaz chaud d'une turbomachine

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DE19934418A1 (de) * 1999-07-22 2001-01-25 Abb Alstom Power Ch Ag Verfahren zum Beschichten einer lokal unterschiedlich beanspruchten Komponente
DE10032454A1 (de) * 2000-07-04 2002-01-17 Man Turbomasch Ag Ghh Borsig Vorrichtung zum Kühlen eines ungleichmäßig stark temperaturbelasteten Bauteiles
US6673467B2 (en) 2001-10-01 2004-01-06 Alstom (Switzerland) Ltd Metallic component with protective coating
DE10163171A1 (de) * 2001-12-21 2003-07-03 Solvay Fluor & Derivate Neue Verwendung für Legierungen
DE10239534A1 (de) 2002-08-23 2004-04-22 Man Turbomaschinen Ag Heißgas führendes Gassammelrohr
US6983599B2 (en) * 2004-02-12 2006-01-10 General Electric Company Combustor member and method for making a combustor assembly
EP1798300A1 (fr) * 2005-12-16 2007-06-20 Siemens Aktiengesellschaft Alliage, couche protectrice pour proteger un élément de construction contre la corrosion et/ou l'oxidation aux températures élévées et élément de construction
EP2321383B1 (fr) * 2008-09-05 2013-07-03 Intercat Equipment, Inc. Appareil de retrait de matériau et procédé de régulation du stock de matériau dans une ou plusieurs unités
EP2224167A1 (fr) * 2009-02-25 2010-09-01 Siemens Aktiengesellschaft Carter de turbine à gaz
EP4130332A3 (fr) * 2013-03-15 2023-05-31 Raytheon Technologies Corporation Revêtement de barrière thermique résistant à l'éclatement
US10054008B2 (en) * 2015-02-09 2018-08-21 United Technologies Corporation Turbomachine accessory gearbox bracket
USD818502S1 (en) * 2015-12-17 2018-05-22 General Electric Company Turbocharger transition section
USD814522S1 (en) * 2016-06-21 2018-04-03 General Electric Company Transition section for a turbocharged engine

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WO1989007159A1 (fr) 1988-02-05 1989-08-10 Siemens Aktiengesellschaft Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection
WO1991002108A1 (fr) 1989-08-10 1991-02-21 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
DE4242099A1 (de) 1992-12-14 1994-06-16 Abb Patent Gmbh Vorrichtung, insbesondere Gasturbineneinrichtung, mit einer Beschichtung von Einrichtungsteilen
WO1996034129A1 (fr) 1995-04-25 1996-10-31 Siemens Aktiengesellschaft Composant de superalliage presentant un systeme de revetement protecteur
WO1996034128A1 (fr) 1995-04-25 1996-10-31 Siemens Aktiengesellschaft Substrat metallique presentant une couche d'oxyde ainsi qu'une couche d'ancrage

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1989007159A1 (fr) 1988-02-05 1989-08-10 Siemens Aktiengesellschaft Objet metallique, notamment aube de turbine a gaz pourvue d'un revetement de protection
WO1991002108A1 (fr) 1989-08-10 1991-02-21 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
DE4242099A1 (de) 1992-12-14 1994-06-16 Abb Patent Gmbh Vorrichtung, insbesondere Gasturbineneinrichtung, mit einer Beschichtung von Einrichtungsteilen
WO1996034129A1 (fr) 1995-04-25 1996-10-31 Siemens Aktiengesellschaft Composant de superalliage presentant un systeme de revetement protecteur
WO1996034128A1 (fr) 1995-04-25 1996-10-31 Siemens Aktiengesellschaft Substrat metallique presentant une couche d'oxyde ainsi qu'une couche d'ancrage

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007101465A1 (fr) * 2005-12-14 2007-09-13 Man Turbo Ag Procede de revetement d'une aube et aube d'une turbine a gaz
US9109279B2 (en) 2005-12-14 2015-08-18 Man Diesel & Turbo Se Method for coating a blade and blade of a gas turbine
EP2198064A1 (fr) * 2007-10-09 2010-06-23 Man Turbo Ag Composant traverse par du gaz chaud d'une turbomachine

Also Published As

Publication number Publication date
CN1231384A (zh) 1999-10-13
DE19815473A1 (de) 1999-10-14
CN1143056C (zh) 2004-03-24
DE59906280D1 (de) 2003-08-21
CA2263834A1 (fr) 1999-10-07
CA2263834C (fr) 2004-10-19
JPH11336563A (ja) 1999-12-07
EP0949410B1 (fr) 2003-07-16
JP3823282B2 (ja) 2006-09-20
EP0949410A3 (fr) 2000-11-02
US6226978B1 (en) 2001-05-08

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