EP2122009A1 - Dispositif pour protéger des éléments avec un alliage de titane combustible contre le feu de titane et procédé pour sa fabrication - Google Patents

Dispositif pour protéger des éléments avec un alliage de titane combustible contre le feu de titane et procédé pour sa fabrication

Info

Publication number
EP2122009A1
EP2122009A1 EP08706819A EP08706819A EP2122009A1 EP 2122009 A1 EP2122009 A1 EP 2122009A1 EP 08706819 A EP08706819 A EP 08706819A EP 08706819 A EP08706819 A EP 08706819A EP 2122009 A1 EP2122009 A1 EP 2122009A1
Authority
EP
European Patent Office
Prior art keywords
layer
titanium
layer system
components
ceramic
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.)
Ceased
Application number
EP08706819A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Wolfgang Eichmann
Falko Heutling
Markus Uecker
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 EP2122009A1 publication Critical patent/EP2122009A1/fr
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
    • 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
    • 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
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
    • C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10T428/12458—All metal or with adjacent metals having composition, density, or hardness gradient
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal

Definitions

  • the present invention is in the field of gas turbine technology, such as the power or power plant technology, settled, and in particular concerns occurring components.
  • the invention proposes a device for protecting combustible titanium alloys from titanium fire and / or damage by foreign objects.
  • the mass should be as small as possible, in particular the rotating, in mobile units and the static (non-rotating) elements in order to change the rotational speed or the overall speed engine to cause the least possible changes in kinetic energy.
  • a lower engine weight is desirable for the same performance, as this results in e.g. Fuel costs can be saved or a higher payload is enabled.
  • Titan fire Due to the weight saving in modern compressors more and more often found lightweight construction leads to an increased use of components made of titanium alloys. In order to achieve the desired high outputs and efficiencies, the operating pressures and temperatures must be further increased. From a certain temperature and pressure level, however, a so-called Titan fire can arise. Since titanium burns very easily due to its high affinity to oxygen, such a fire is then no longer extinguishable and can within a short time - 8 to 10 seconds - and at temperatures up to 2500 ° C to major damage to the components, in extreme cases even to Total loss of the engine, drove. Possible causes of a titanium fire may include damage to blades, severe rubbing of the turbine blades on the housing, or even bearing damage.
  • flammable (titanium-containing) mass can be removed from the critical area and replaced by steel or nickel alloys.
  • these coatings typically include anti-wear, anti-corrosion, hot gas corrosion and oxidation, titanium fire, and layers to minimize the rotor-stator gap, as well as thermal insulation layers.
  • these coatings typically include anti-wear, anti-corrosion, hot gas corrosion and oxidation, titanium fire, and layers to minimize the rotor-stator gap, as well as thermal insulation layers.
  • thermal insulation layers In the area of the compressor layers are mainly used for protection against titanium fire and erosion protection.
  • this can be coated with several millimeters thick layers.
  • These layers may include, for example, plasma sprayed oxide ceramic layers.
  • the blades in particular the guide vanes of the particularly heat-stressed high-pressure compressor themselves, are usually made of so-called "superalloys.”
  • Super alloys are high-alloy materials of complex composition (iron, nickel, platinum, chromium or cobalt-based with additions of the elements Co, Ni, Fe, Cr, Mo, W, Re, Ru, Ta, Nb, Al, Ti, Mn, Zr, C and B) for high-temperature applications. but in comparison with titanium, which is still used in forged form at least in low-pressure compressors, the density is approximately twice as high and therefore correspondingly heavy.
  • Another way to use titanium in high-stress parts of the engine is to alloy it with aluminum (TiAl). This option is used primarily in the manufacture of the blades.
  • US Pat. No. 5,114,797 Proposes a three-layer coating for protection against titanium fire, which comprises a metallic adhesion-promoting layer, a heat-insulating intermediate layer of an oxidic nature, and a titanium-fire-retardant metallic coating.
  • a nickel-aluminum alloy is proposed as the metallic adhesion-promoting layer, a zirconium oxide layer as the intermediate layer, and aluminum and / or aluminum oxide as the protective coating.
  • titanium Due to the high strength and the low specific gravity of titanium, it is desirable to use the material titanium as extensively as possible in the production of movable and fixed elements of gas turbines, especially in the area of the compressor, and especially in the area of the guide vanes. It would be particularly good, if care is taken to ensure that the material neither through so-called erosion and / or FODs (Foreign Object Damage, damage by foreign objects), nor by so-called Titanium fire, which occurs, for example, as a result of rubbing on moving parts that are stationary and made of titanium, can be damaged or best protected.
  • erosion and / or FODs Form Object Damage, damage by foreign objects
  • the outer layer of the layer system or the ceramic layer is preferably a titanium-free or Niedrigtitanlialtiges multicomponent system. It is particularly preferred that the underlying layer consists of a titanium-free or low titanium-containing metallic layer.
  • the device according to the invention serves to protect highly stressed components, in particular turbine components such as guide vanes or moving blades, from external influences, in particular from titanium fire and damage by foreign objects, by means of a layer system comprising at least two layers firmly connected to the component.
  • the layer system is preferably high-melting and / or non-combustible.
  • the layer system is also erosion-inhibiting, in particular as a supplement.
  • a significant advantage of the invention lies in the fact that it makes it possible to use lighter, titanium-based materials in the area of highly stressed components, in particular in the field of gas turbine construction, and above all in the area of the guide vanes of the compressor. This results in a significant reduction in the weight of compressors.
  • Due to the combination of metallic and ceramic layers provided in a preferred design an expansion-adapted adaptation of the ceramic layers to the metallic base material is achieved.
  • the metallic layers prevent propagation of cracks possibly occurring in the ceramic layers.
  • the ceramic layers in turn protect the entire system from damage caused by excessive temperatures. Also, these layers provide protection against metallic contact of the base material in FODs.
  • the possible removal volume that can be damaged in the event of damage can be further increased.
  • titan fire Even with complete, local removal of the protective layer, the remaining coated surfaces hinder propagation of heat-induced ignition or burn-up of titanium-based base material, i. a so-called titan fire.
  • the coating can be very thin, it does not or only insignificantly influences the weight, the aerodynamics and the vibration resistance of the components protected by it.
  • the invention relates to a device for protecting combustible titanium alloys from titanium fire and / or damage caused by foreign objects (FODs).
  • FODs foreign objects
  • a protective layer system which encloses the entire component or parts thereof and which consists of at least two layers.
  • the component may be a guide or moving blade of an axial turbomachine, for example a guide or moving blade of a compressor stage.
  • This outermost layer advantageously consists of a ceramic layer, in particular of a non-titanium-based multicomponent system.
  • Particularly preferred embodiments of the ceramic layer are a chromium nitride layer or an aluminum nitride layer, a chromium-aluminum nitride layer.
  • the layer following and concealing the ceramic layer consists in particular of a metallic layer, in particular of a non-titanium-based metal or metal alloy layer.
  • Particularly preferred embodiments of the metallic layer are, for example, a chromium or nickel or alumium layer, or alloys thereof.
  • basic composite
  • the layer system comprises a sequence of at least two base groups.
  • an adhesion-promoting layer is additionally present between the protective layer system and the base material.
  • a graded transition may be provided, for example in the form CrAl - (CrAl) N 1 -x-CrAlN.
  • the ceramic layer (s) is or are dimensioned such that they hinder the on and melting of the underlying titanium alloy of the base material for the duration of at least one titanium fire.
  • the layer thicknesses of the layers are dimensioned so that the total thickness of the layer system does not exceed some, in particular three, millimeters, and in a particularly preferred embodiment is less than one millimeter, particularly preferably less than 3 / 10 mm, more preferably less than 2/10 mm, more preferably less than 1/10 millimeter.
  • All versions of the layer system can cover either a component in its entirety or only parts of a component. Combinations of different designs, for example those of a basic composite with those of several base composites, with or without an adhesion-promoting layer, are likewise possible.
  • an entire assembly is in an area that requires protection from titanium fire and / or FODs, then all parts of the assembly, some parts, only a part, or only areas of a part can be protected with the device according to the invention. Any combination of protected parts or part areas is possible. If, for example, the assembly is a compressor, then either the guide vanes, the individual guide blade stages, the rotor blades, or the individual rotor blade stages and / or areas thereof can be protected by the device according to the invention.
  • this offers the possibility of being able to be renewed in case of repair.
  • the layer system by means of thermal spraying and / or by means of flame spraying and / or by means of vacuum plasma spraying and / or by means of EB-PVD (Electron Beam Physical Vapor Deposition, and / or by means of an electrochemical process and / or by sputtering and / or by vapor deposition (PVD) and / or by PVD (Physical Vapor Deposition) and / or by arc vapor deposition (CARC) is applied.
  • EB-PVD Electro Beam Physical Vapor Deposition, and / or by means of an electrochemical process and / or by sputtering and / or by vapor deposition (PVD) and / or by PVD (Physical Vapor Deposition) and / or by arc vapor deposition (CARC)
  • Figure 1 shows a structure of a layer system 1, which is composed of a ceramic outer layer Ia and an underlying metallic connection layer Ib ("basic composite"), which is located on a base material 2;
  • Figure 2 shows a structure of a layer system 1 of FIG. 1, which additionally a
  • Adhesive layer 3 which is located between the inner layer of the layer system of Figure 1 and the base material 2;
  • FIG. 3 shows a structure of a layer system 1 according to FIG. 1, which is composed of a plurality of mutually alternating ceramic layers Ia and metallic layers Ib (two basic composites); and
  • FIG. 4 shows a layer system according to FIG. 3, which has been damaged by the impact of foreign objects or by contact with liquid titanium on the outer layers and has cracks 4 and 5, but the innermost layer is undamaged and thus the base material is protected.
  • Figure 1 shows the cross section through a layer system 1, which is composed of an outer ceramic layer Ia and an underlying metallic layer Ib.
  • This composite which is referred to below as the "basic composite”
  • the base composite has the task of preventing the base material 2 from external influences, in particular from To protect high temperatures and FODs, as well as a risk of titanium fire to prevent or at least obstruct this, if titanium or a titanium alloy is used as base material 2.
  • the outer ceramic layer 1a has poor heat conduction and an extremely high melting point. It therefore keeps the heat from the underlying metallic layer Ib and prevents melting or melting of the same or of the base material 2 at least for the duration of a titanium fire. Furthermore it offers a particularly good erosion resistance. Finally, it prevents a first metallic contact with the base material 2 when metallic FODs occur.
  • the ceramic layer Ia may have a significantly different expansion coefficient from the base material 2, it is not directly on the base material 2, from where it could easily flake off, but it is by the metallic layer Ib, with which it is firmly connected, and which functions inter alia as a temperature expansion compensation layer held.
  • both layers Ia and Ib are non-flammable and high-melting according to the invention, they can not ignite and burn and / or melt at normal or elevated operating temperatures.
  • the thickness and composition of the layers can be dimensioned such that the layer composite offers effective protection against titanium fire and FODs, while at the same time not having a negative effect on the vibration resistance of the protected component.
  • Figure 2 shows an inventive layer system 1 of FIG. 1 consisting of a ceramic layer Ia and a metallic layer Ib, which is additionally underlaid with an adhesive layer 3 and firmly connected thereto.
  • the adhesion-promoting layer 3 has the task of improving the adhesion between the metallic layer 1b and the base material 2 if the metallic layer 1b otherwise does not adhere sufficiently firmly to the base material 2.
  • FIG. 3 shows a layer system 1 according to the invention, which is constructed from two base composites from FIG. It therefore consists of an outer ceramic layer Ia, followed by a metallic layer Ib, another ceramic layer Ia, and finally a last metallic layer Ib. All layers are according to the invention firmly together and connected to the base material 2. Such a multi-layer construction increases the protective effect by providing a correspondingly higher volume, which can be removed in case of damage or titanium fire.
  • FIG. 4 shows a layer system according to FIG. 3 and discloses a further object of the metallic layers 1b.
  • the present invention is not limited in its execution to the above-mentioned preferred embodiment. Rather, a number of variants is conceivable, which makes use of the illustrated solution even with fundamentally different types of use.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention permet d'utiliser des matériaux à base de titane dans la construction de turbines à gaz, spécialement dans la construction de moteurs de turbines à gaz et en particulier dans celle de compresseurs, de par la mise à disposition d'un dispositif qui protège les éléments soumis à l'action du feu titane et/ou à des détériorations par corps étrangers (FOD) (aubes directrices, étage d'aubes directrices, aubes mobiles, étage d'aubes mobiles), grâce à un système de couches comprenant au moins deux strates, qui se trouve sur la surface des éléments à protéger et est relié de manière fixe avec ceux-ci, éventuellement à l'aide d'une couche favorisant l'adhérence. La couche la plus extérieure est en outre de nature céramique, celle se situant en dessous est de nature métallique. D'autres couches peuvent éventuellement suivre, des couches céramiques et métalliques alternant les unes aux autres. Un procédé de fabrication du dispositif selon l'invention est par ailleurs fourni. Grâce à l'utilisation au moins partielle d'alliages de titane, en particulier pour des aubes directrices de turbines à gaz, l'invention permet une réduction significative du poids des compresseurs, du fait que l'on peut renoncer aux matériaux de construction à base de nickel ou d'acier utilisés dans la technique antérieure, au profit d'alliages de titane plus légers.
EP08706819A 2007-02-06 2008-01-29 Dispositif pour protéger des éléments avec un alliage de titane combustible contre le feu de titane et procédé pour sa fabrication Ceased EP2122009A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200710005755 DE102007005755A1 (de) 2007-02-06 2007-02-06 Vorrichtung zum Schutz von Bauteilen mit brennbarer Titanlegierung vor Titanfeuer und Verfahren zu deren Herstellung
PCT/DE2008/000152 WO2008095463A1 (fr) 2007-02-06 2008-01-29 Dispositif pour protéger des éléments avec un alliage de titane combustible contre le feu de titane et procédé pour sa fabrication

Publications (1)

Publication Number Publication Date
EP2122009A1 true EP2122009A1 (fr) 2009-11-25

Family

ID=39358152

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08706819A Ceased EP2122009A1 (fr) 2007-02-06 2008-01-29 Dispositif pour protéger des éléments avec un alliage de titane combustible contre le feu de titane et procédé pour sa fabrication

Country Status (5)

Country Link
US (1) US20100143108A1 (fr)
EP (1) EP2122009A1 (fr)
CA (1) CA2675107A1 (fr)
DE (1) DE102007005755A1 (fr)
WO (1) WO2008095463A1 (fr)

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FR2935764B1 (fr) * 2008-09-05 2014-06-13 Snecma Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur
FR2935623B1 (fr) * 2008-09-05 2011-12-09 Snecma Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
DE102009010110B4 (de) * 2009-02-21 2014-08-28 MTU Aero Engines AG Erosionsschutz-Beschichtungssystem für Gasturbinenbauteile
FR2978076B1 (fr) * 2011-07-22 2013-08-16 Snecma Assemblage d'une coque titane et d'une coque alliage resistant au feu titane par depot par cold-spray
US9834835B2 (en) * 2015-02-18 2017-12-05 United Technologies Corporation Fire containment coating system for titanium
RU182167U1 (ru) * 2017-08-22 2018-08-06 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Ротор компрессора газотурбинного двигателя
EP3470680A1 (fr) * 2017-10-16 2019-04-17 OneSubsea IP UK Limited Lames résistant à l'érosion pour compresseurs
US11982236B2 (en) 2017-12-22 2024-05-14 General Electric Company Titanium alloy compressor case
DE102018202726A1 (de) * 2018-02-22 2019-08-22 MTU Aero Engines AG Bauteil, insbesondere Laufschaufel, für eine Strömungsmaschine mit einer Panzerungsdoppelschicht
CN111765033B (zh) * 2019-04-02 2021-12-17 南京华电节能环保设备有限公司 一种高温熔渣回收发电用叶轮
CN114134371B (zh) * 2021-11-10 2022-09-06 中国科学院上海硅酸盐研究所 一种TiAl合金用双层抗氧化涂层及其制备方法
CN114635132B (zh) * 2022-05-17 2022-08-02 北京煜鼎增材制造研究院有限公司 钛合金防钛火涂层及其制备方法

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Also Published As

Publication number Publication date
WO2008095463A1 (fr) 2008-08-14
DE102007005755A1 (de) 2008-08-07
CA2675107A1 (fr) 2008-07-14
US20100143108A1 (en) 2010-06-10

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