CN104718349B - 用于燃气涡轮发动机的转子定子组件 - Google Patents
用于燃气涡轮发动机的转子定子组件 Download PDFInfo
- Publication number
- CN104718349B CN104718349B CN201380053033.6A CN201380053033A CN104718349B CN 104718349 B CN104718349 B CN 104718349B CN 201380053033 A CN201380053033 A CN 201380053033A CN 104718349 B CN104718349 B CN 104718349B
- Authority
- CN
- China
- Prior art keywords
- coating
- rotor
- stator
- abrasion
- component according
- 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.)
- Active
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
- 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
- F01D5/284—Selection of ceramic materials
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/48—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on zirconium or hafnium oxides, zirconates, zircon or hafnates
- C04B35/486—Fine ceramics
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/48—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on zirconium or hafnium oxides, zirconates, zircon or hafnates
- C04B35/486—Fine ceramics
- C04B35/488—Composites
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—Oxides
-
- 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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- 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
- 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
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
- C04B2235/3225—Yttrium oxide or oxide-forming salts thereof
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3852—Nitrides, e.g. oxynitrides, carbonitrides, oxycarbonitrides, lithium nitride, magnesium nitride
- C04B2235/386—Boron nitrides
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/74—Physical characteristics
- C04B2235/76—Crystal structural characteristics, e.g. symmetry
- C04B2235/767—Hexagonal symmetry, e.g. beta-Si3N4, beta-Sialon, alpha-SiC or hexa-ferrites
-
- 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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- 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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F05C2203/00—Non-metallic inorganic materials
- F05C2203/08—Ceramics; Oxides
- F05C2203/0865—Oxide ceramics
- F05C2203/0895—Zirconium oxide
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/15—Heat shield
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
-
- 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
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/228—Nitrides
- F05D2300/2285—Nitrides of zirconium
-
- 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
- F05D2300/502—Thermal properties
-
- 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
- F05D2300/516—Surface roughness
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- 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
Abstract
用于燃气涡轮发动机的转子‑定子组件。本发明涉及一种用于燃气涡轮发动机的转子‑定子组件,所述组件包括:转子(2),所述转子具有陶瓷材料层(8),所述陶瓷材料层形成沉积在所述转子末端上的研磨涂层,所述层主要由氧化锆构成并且其空隙率小于或者等于15%;和定子(4),所述定子布置在所述转子周围并且面向所述转子的所述末端设置有陶瓷材料层(6),所述陶瓷材料层形成磨耗涂层,所述涂层主要由氧化锆构成并且空隙率处于20%至50%的范围内,其中,孔的尺寸小于或者等于50μm。
Description
技术领域
本发明涉及用于燃气涡轮发动机的转子-定子组件的总领域。本发明更加具体地涉及优化研磨涂层和磨耗涂层的微观结构,所述研磨涂层和所述磨耗涂层分别沉积在转子的末端和包围转子的定子的内表面上。
能够应用本发明的特定领域是用于飞机涡轮机(特别地用于飞机发动机或直升机发动机)的压缩机。
背景技术
航空发动机压缩机包括压缩机壳体,所述压缩机壳体由一个或者多个环形结构构成,所述环形结构面对一组或者多组叶片,所述叶片在叶片和环形结构之间相对旋转运动。类似地,航空发动机涡轮机包括涡轮环,所述涡轮环由环形结构构成,所述环形结构构成单个或者多个碰触环扇形件,所述碰触环扇形件包围一组旋转叶片,由燃烧气体驱动所述一组旋转叶片。
为了向航空发动机提供可行最佳效率,必须避免或者至少最小化叶片的末端和压缩机壳体的饰面之间或者涡轮环的饰面之间的气体泄漏,原因在于这种泄漏无助于发动机操作。寻求无间隙或者最小化间隙表示在叶片末端和覆面材料之间将存在不可避免的接触。由于这种材料常有的硬度,这种接触能够损坏叶片的末端。
为了解决这个问题,已经建议优化面向叶片的材料的耐磨性,即,优化其由叶片的末端物理磨损的性能而同时又不会显著磨损末端的能力。为了这个目的的一种已知技术是为压缩机壳体的内表面或者涡轮环的内表面设置形成由多孔材料制成的磨耗涂层的层,而且同时为叶片的末端设置形成研磨涂层的致密材料的层。
对于沉积在叶片末端的研磨涂层而言,因此已知依赖于这样的材料,所述材料包含立方碳化硼(cBN)颗粒或者氧化物、碳化钨或者氮化物类型的其它硬颗粒。这种涂层在它们与磨耗涂层相关时呈现令人满意的研磨行为,所述磨耗涂层由金属或者陶瓷制成。然而,当在高温条件下使用它们时,它们呈现欠佳的耐用性(这些涂层承受氧化并且分散到涂层基底中),并且它们还呈现有限的、与期望的使用寿命不相配的热机械行为。而且,沉积这种涂层相对昂贵。
对于沉积在定子的内表面上的多孔磨耗涂层而言,已知使用MCrAlY类型的金属合金或者使用基于氧化锆的陶瓷。金属合金具有易于以低成本制造的优势。相比之下,其耐磨性能相对欠佳并且其使用受到温度限制。相反,基于氧化锆的陶瓷能够用于实施磨耗涂层功能和隔热功能。基于氧化物的涂层的性质使得能够在高温条件(高于1100℃)下使用所述基于氧化物的涂层,这是因为其保存其物理性质。这种涂层还已知易于制造、具有成本效益(通过热喷涂沉积)并且对于特定水平的多孔结构而言其呈现良好的耐磨性能。然而,这种多孔涂层因难以使得层中的孔和颗粒成形并且难以控制孔以及颗粒的尺寸,因而在机械加工之后存在这样的表面状态问题。不幸的是,气流中的这种表面状态有损发动机的性能。
通常,尽管在现有技术中已知磨耗/研磨涂层对,所述已知磨耗/研磨涂层对展示了主要预期性能(即,系统关于解除、承受腐蚀的能力、承受热循环的能力和良好的表面状态的行为)中的尤为良好性能,但所述已知磨耗/研磨涂层均不能独自优化所有预期性能。
因此,需要能够具有一种涂层对,使得能够最小化上述缺陷,所述涂层对可用于磨耗材料和研磨材料,所述磨耗材料和所述研磨材料分别沉积在定子的内表面和转子的末端。
发明内容
本发明的目的因此是提供涂层对,所述涂层尤其在高温条件下对于所有上述主要性能皆具有一致并且高的性能,而同时制造成本低廉。
通过用于燃气涡轮机发动机的转子-定子组件实现这个目的,所述组件包括:
转子,所述转子具有陶瓷材料层,所诉陶瓷材料层形成沉积在转子末端上的研磨涂层,所述层主要由氧化锆构成并且拥有小于或者等于15%的空隙率;和
定子,所述定子布置在转子周围并且设置成面向转子的具有形成磨耗涂层的陶瓷材料层的转子的末端,所述层主要由氧化锆构成并且空隙率处于20%至50%的范围内,其中,孔的尺寸小于或者等于50微米(μm)。
这种研磨/磨耗涂层对具有多个优势。特别地,本申请人已经发现的是:由基于氧化锆的陶瓷材料制成的研磨涂层在其与由基于陶瓷的氧化锆材料制成的磨耗涂层相关时具有尤为高性能的磨损性能,所述磨耗涂层的空隙率介于20%至50%的范围内,其中,孔的尺寸小于或者等于50微米(μm)。同样,本申请人还已经发现的是,由根据本发明的基于氧化锆的陶瓷材料制成的磨耗涂层在其与由基于氧化锆的陶瓷材料制成的研磨涂层相关时具有令人满意的耐磨性能。
而且,磨耗涂层显示出在所有接触条件(即,切向速度、入侵速度和温度)下均一致的性能并且在能够在高温条件(高于1100℃)下使用。其还是这样的材料,所述材料实施隔热层的功能和磨耗涂层的功能,并且机械加工之后的其表面状态令人满意。
而且,这种研磨/磨耗涂层对易于制造和维修并且制造成本较低。能够通过热喷涂、溶胶-凝胶方法或者针对磨耗涂层烧结的方法沉积主要基于氧化锆的材料,并且这些沉积方法易于实施。
优选地,在所述层内磨耗涂层的多孔结构一致。
磨耗涂层的多孔结构可以呈现单模式分布,其中孔尺寸小于或者等于5μm。替代地,磨耗涂层的多孔结构可以呈现双模式分布,其中,小孔尺寸小于或者等于5μm,中孔尺寸处于15μm至50μm之间。
而且,磨耗涂层由至少两层部分构成,所述至少两层部分具有不同的空隙率。通过使得磨耗涂层中的多孔结构随着深度变化增强了涂层热震阻力,增强了其热循环阻力并且增加了涂层的隔热能力(这提供了更有效的隔热)。磨耗涂层还可以包括直裂纹。
而且优选地,磨耗涂层具有处于4GPa至10GPa之间的弹性模量以及处于70HRC至95HRC之间的硬度。这种性能使得磨耗涂层在保存良好的耐磨特征的同时赋予其更好的热震阻力以及充分抗腐蚀性。
类似地,磨耗涂层有利地具有大于或者等于30GPa的弹性模量和大于600维氏硬度(HV)的硬度。
同样优选地,构成磨耗涂层和研磨涂层的氧化锆掺杂有钇、钆、镝或者任何其它正方相或者立方相的氧化锆的稳定剂。
磨耗涂层可以通过热喷涂、烧结或者溶胶-凝胶方法沉积在定子上。类似地,研磨涂层可以通过热喷涂、烧结或者电解方法、通过汽相沉淀方法或者通过溶胶-凝胶方法沉积在转子的末端上。
本发明还提供了一种具有如上所述的至少一个转子-定子组件的燃气涡轮机发动机。
附图说明
从参照附图描写的以下描述中本发明的其它特征和优势将变得显而易见,所述附图示出了具有非限制性特征的实施例。在所述附图中:
图1是根据本发明的转子-定子组件的示例的示意图;
图2A-2C、3A-3C和4A-4B示出了适于用作图1组件的定子的磨耗涂层的材料的各个实施例;和
图5和图6是示出了分别针对现有技术转子-定子组件和根据本发明的转子-定子组件的测试期间的研磨涂层和磨耗涂层的性能的照片。
具体实施方式
本发明应用于用于燃气涡轮发动机的任何转子-定子组件,其中,转子的末端接触定子的包围转子的部分的内表面。
图1是本发明的应用的示例的简图,其中,转子由涡轮喷气飞机中的高压涡轮机的旋转叶片2构成而定子是涡轮环4,所述涡轮环4制成为一体或者由多个环绕所述叶片的接触环部段构成。
在这个组件中,涡轮环4的内表面和叶片2的末端之间的间隙是零或者近似为零。在内部,涡轮环承载有磨耗涂层6,沉积在叶片2的末端上的研磨涂层8能够部分穿入到所述磨耗涂层中而同时又没有承受大量磨损。
根据本发明,形成研磨涂层8的层由这样的陶瓷材料制成,所述陶瓷材料主要由氧化锆构成并且空隙率小于或者等于15%,而形成磨耗涂层6的材料由这样的陶瓷制成,所述陶瓷主要由氧化锆构成且空隙率介于20%至50%之间,其中,孔尺寸小于或者等于50μm。
在此使用的术语“主要”表示磨耗涂层和研磨涂层的氧化锆代表这些层的成分的至少80%。
因此使用相同的陶瓷,即,氧化锆制造根据本发明的转子-定子组件的磨耗涂层6和研磨涂层8,但是微观结构不同。构成研磨涂层的氧化锆层拥有相对低的多孔结构,以便确保最佳的可行机械性能(硬度和热震阻力),而构成磨耗涂层的氧化锆层具有微小的微观结构(即,孔尺寸小于或者等于50μm),其多孔结构被控制来增强涂层的抗腐蚀性能并确保高耐磨性能。
对于两个涂层而言,所使用的氧化锆有利地掺杂有钇、钆、镝或者任何其它正方相或者立方相的氧化锆的稳定剂。然而,对于两个涂层而言,形成这些涂层的氧化锆粉末的成分不必完全相同。因此,举例说明,能够向粉末中的一种或者另一种粉末添加稳定剂。
沉积在叶片2的末端上的研磨涂层8还优选地拥有大于或者等于30GPa的弹性模量和大于600HV的硬度。
研磨涂层可以通过已知的方法沉积在叶片的末端上,诸如,热喷涂、烧结或者电解方法、汽相沉淀方法或者溶胶-凝胶方法
也可以借助于底层10,以便有助于将研磨涂层沉积在由金属制成的叶片的末端上。例如,可以由MCrAlY(其中,M可以是镍、钴、或者氧化钴)或者通过涂覆铂铝化合物构成粘合底层10。
参照图2A-2C、3A-3C和4A-4B,描述了形成本发明的转子-定子组件的磨耗涂层的材料的层的微观结构的多个实施例。
图2A和2B分别以照片(比例:1μm)形式和简图形式示出了对于主要由氧化锆构成且沉积在基底14上的层12的第一实施例。在这个实施例中,多孔结构(由黑点16表示孔)微小,即,其由小于或者等于5μm的孔构成并且在层的厚度上均匀分布。在这个示例中,多孔结构在层中的分布是单一模式的。
应当注意,这个层12可以经由例如通过沉积MCrAlY型的合金(其中M是镍、钴或者镍钴合金)或者沉积铂铝涂层等形成的粘合底层18沉积在基底上。
而且,在图2C中示出的第一实施例的变形方案中,氧化锆的层12还包括固体润滑剂的颗粒17,诸如,六方碳化硼的颗粒。这种颗粒使得叶片更加易于在转子-定子接触期间运动并且它们限制了转子和定子之间的力。
图3A至图3C示出了沉积在基底14上并且适于构成转子-定子组件的磨耗涂层的层20的第二实施例。
在这个第二实施例中,由氧化锆的两层20a和20b构成层20,所述氧化锆的层20a和20b具有不同的微观结构。因此,沉积在研磨区域旁边的层20a具有较高的多孔结构(即,具有处于20%至50%范围内的空隙率),而沉积在基底14旁边的层20b具有低多孔结构(大约介于10%至20%范围内)。
由此获得的层在表面处具有高多孔结构,以便作为磨耗涂层,并且获得基底旁边的更加致密的底层,以便作为隔热层。多孔结构随着磨耗涂层深度的变化用于提高涂层的热震阻力,提高其抵抗热循环并且增加涂层的隔热能力(其提供了更加有效的隔热层)。
应当注意,这个层20可以经由中间粘合底层18沉积在基底上。
还应当注意,在两层20a和20b中的每一层中,孔优选地以均匀的方式分布在层的厚度上。
而且,在这个第二实施例的变形方案中,如图3C所示,沉积在研磨层旁边的层20a可以具有一个阵列的直裂纹22(每隔一毫米至少两条裂纹),以便提高涂层的热机械性能。
图4A-4B示出了沉积在基底14上并且适于构成转子-定子组件的磨耗涂层的层24的第三实施例。
在这个第三实施例中,通过具有高多孔结构(即,具有介于20%至50%范围内的空隙率)的氧化锆层形成层24。
与第一实施例相比,这个示例中的层中的多孔结构的分布是双模式,即,孔包括“细”孔(即,尺寸小于或者等于5μm)和“中等”孔(即,尺寸处于15μm至50μm之间)。
在图4A的照片中,用黑色区域26表示具有微小尺寸的孔,而用黑色区域28表示具有中等尺寸的孔。应当注意,不受孔尺寸影响,孔均以均匀的方式分布在层24上。
下文描述形成转子-定子组件的磨耗涂层的层的各个实施例所共有的特征。
磨耗涂层优选地具有介于4GPa至10GPa之间的弹性模量。这种值赋予涂层更好的热震阻力。
而且优选地,磨耗涂层的硬度介于70至90罗氏硬度(HR15Y)之间,从而使得能够在存在良好耐磨特征的同时确保充分的抗腐蚀性能。
而且,可以通过热喷涂团聚粉末来沉积磨耗涂层,所述团聚粉末优选地包含孔生成剂和固体润滑剂。还能够采用热喷涂悬浮纳米粉末,所述悬浮纳米粉末有助于获得更细小的微观结构。同样,能够修改喷涂参数,以便获得具有直裂纹和大约20%的空隙率的微观结构。
还可以在具有孔生成剂或者固体润滑剂或者不存在孔生成剂或者固体润滑剂的情况下通过烧结粉末来实施沉积,所述粉末具有亚微米微观结构。烧结通过在低于陶瓷熔融温度的温度条件下使得沉积物成形而提供了针对微观结构的加强控制。特别地,微观结构可以保持细小并且可以在一致性和尺寸以及分布方面来控制多孔结构。
还可以使用溶胶-凝胶方法来沉积磨耗涂层。
参照图5和图6,描述了针对现有技术研磨/磨耗涂层(图5)和针对根据本发明的研磨/磨耗涂层的测试耐磨性和磨损的结果。
使用由供应商Sulzer Innotec制造的测试台来实施这些测试。以已知方式,这种测试台包括:承载叶片的转子,所述叶片在其自由端部处设置有研磨涂层;和板,所述板承载磨耗涂层的样本,所述测试台能够使得板向转子运功,以便使得研磨材料能够侵入到磨耗材料中。测试台还具有高速火焰发生器,用于在测试期间加热磨耗涂层。
在同样条件下实施测试,其中,转子的旋转速度为410m/s,将磨耗涂层加热到大约1100℃的温度,研磨涂层侵入到磨耗涂层的侵入速度为50μm/s。
图5示出了测试现有技术磨耗涂层30之后的表面状态和在接触涂层之后叶片32的末端(无涂层)的平面图,由致密氧化锆(空隙率为10%)构成所述现有技术磨耗涂层30。
在这个视图中,在沉积在定子上的磨耗涂层中的接触状况欠佳的情形下,并且在存在材料从叶片转移定子的情形下,能够在叶片的末端处发现高度磨损。
图6示出了在测试根据本发明的磨耗涂层34之后的表面状态和根据本发明的研磨涂层36的截面图。特别地,在这个测试中,磨耗涂层34由细孔和中孔(双模式分布)构成,所述磨耗涂层34的空隙率处于25%至28%的范围内,所述细孔和所述中孔如参照图3A和3B所述的那样均匀分布。类似地,由氧化锆部分制成的研磨涂层36因钇而稳定,所述研磨涂层具有大约10%的空隙率。
与图5相比,能够在图6中发现,沉积在转子上的研磨涂层的磨损较低,而沉积在定子上的磨耗涂层的接触良好。这导致就根据本发明的转子-定子组件的研磨/磨耗涂层对的耐磨性和磨损而言的良好性能。
Claims (9)
1.一种用于燃气涡轮发动机的转子-定子组件,所述组件包括:
转子(2),所述转子具有由陶瓷材料形成的沉积在所述转子末端上的研磨涂层(8),所述研磨涂层主要由氧化锆构成并且其空隙率小于或者等于15%;和
定子(4),所述定子布置在所述转子周围并且面向所述转子的所述末端设置有由陶瓷材料形成的磨耗涂层(6;12;20;24),所述磨耗涂层主要由氧化锆构成并且空隙率处于20%至50%的范围内,其中,孔的尺寸小于或者等于50μm,
其中,所述磨耗涂层的多孔结构具有双模式分布,小孔尺寸小于或者等于5μm,中孔尺寸处于15μm至50μm的范围内,所述小孔和所述中孔都均匀分布在所述磨耗涂层中。
2.根据权利要求1所述的组件,其中,所述磨耗涂层(20)包括直裂纹(22)。
3.根据权利要求1所述的组件,其中,所述磨耗涂层的弹性模量介于4GPa至10GPa之间并且硬度介于70HR15Y至95HR15Y之间。
4.根据权利要求1所述的组件,其中,所述研磨涂层的弹性模量大于或者等于30GPa并且硬度大于600HV。
5.根据权利要求1所述的组件,其中,构成所述磨耗涂层和所述研磨涂层的所述氧化锆掺杂有钇、钆、镝或者任何其它正方相或者立方相的氧化锆的稳定剂。
6.根据权利要求1所述的组件,其中,通过热喷涂、烧结或者溶胶-凝胶方法将所述磨耗涂层沉积在所述定子上。
7.根据权利要求1所述的组件,其中,通过热喷涂、烧结、电解方法、汽相沉积方法或者溶胶-凝胶方法将所述研磨涂层沉积在所述转子的所述末端上。
8.根据权利要求1所述的组件,其中,所述转子是涡轮机叶片并且所述定子是涡轮机壳体。
9.一种燃气涡轮发动机,其包括根据权利要求1所述的至少一个转子-定子组件。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1259704 | 2012-10-11 | ||
FR1259704A FR2996874B1 (fr) | 2012-10-11 | 2012-10-11 | Ensemble rotor-stator pour moteur a turbine a gaz |
PCT/FR2013/052370 WO2014057194A1 (fr) | 2012-10-11 | 2013-10-07 | Ensemble rotor-stator pour moteur a turbine a gaz |
Publications (2)
Publication Number | Publication Date |
---|---|
CN104718349A CN104718349A (zh) | 2015-06-17 |
CN104718349B true CN104718349B (zh) | 2018-03-30 |
Family
ID=47714219
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201380053033.6A Active CN104718349B (zh) | 2012-10-11 | 2013-10-07 | 用于燃气涡轮发动机的转子定子组件 |
Country Status (11)
Country | Link |
---|---|
US (1) | US10329928B2 (zh) |
EP (1) | EP2917502B1 (zh) |
JP (1) | JP6290224B2 (zh) |
KR (1) | KR102139395B1 (zh) |
CN (1) | CN104718349B (zh) |
CA (1) | CA2887901C (zh) |
FR (1) | FR2996874B1 (zh) |
IN (1) | IN2015DN03013A (zh) |
PL (1) | PL2917502T3 (zh) |
RU (1) | RU2647007C2 (zh) |
WO (1) | WO2014057194A1 (zh) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20160305319A1 (en) * | 2015-04-17 | 2016-10-20 | General Electric Company | Variable coating porosity to influence shroud and rotor durability |
EP3332894A1 (de) * | 2016-12-08 | 2018-06-13 | Siemens Aktiengesellschaft | Verfahren zur herstellung eines gasturbinenbauteils |
GB2557679A (en) * | 2016-12-15 | 2018-06-27 | Edwards Ltd | Stator blade unit for a turbomolecular pump |
DE102017207238A1 (de) * | 2017-04-28 | 2018-10-31 | Siemens Aktiengesellschaft | Dichtungssystem für Laufschaufel und Gehäuse |
US10294962B2 (en) * | 2017-06-30 | 2019-05-21 | United Technologies Corporation | Turbine engine seal for high erosion environment |
FR3074448B1 (fr) * | 2017-12-06 | 2019-12-20 | Safran Aircraft Engines | Revetement a gradient de propriete pour paroi interne de turbomachine |
US11111808B2 (en) | 2017-12-06 | 2021-09-07 | Safran Aircraft Engines | Coating with property gradient for inner wall of turbomachine |
US10662799B2 (en) | 2018-02-02 | 2020-05-26 | Raytheon Technologies Corporation | Wear resistant airfoil tip |
US10662788B2 (en) | 2018-02-02 | 2020-05-26 | Raytheon Technologies Corporation | Wear resistant turbine blade tip |
US11203942B2 (en) | 2018-03-14 | 2021-12-21 | Raytheon Technologies Corporation | Wear resistant airfoil tip |
US10995623B2 (en) | 2018-04-23 | 2021-05-04 | Rolls-Royce Corporation | Ceramic matrix composite turbine blade with abrasive tip |
US11346232B2 (en) | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
EP3683406B1 (en) * | 2019-01-18 | 2023-11-29 | Ansaldo Energia Switzerland AG | Abradable hybrid material, particularly for seal elements in gas turbines, and manufacturing method thereof |
IT201900001173A1 (it) * | 2019-01-25 | 2020-07-25 | Nuovo Pignone Tecnologie Srl | Turbina con un anello avvolgente attorno a pale rotoriche e metodo per limitare la perdita di fluido di lavoro in una turbina |
CN113623022A (zh) * | 2021-07-30 | 2021-11-09 | 中国航发沈阳发动机研究所 | 一种具有易磨涂层的涡轮外环 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2226050A (en) * | 1988-12-16 | 1990-06-20 | United Technologies Corp | Thin abradable ceramic air seal |
US5743013A (en) * | 1994-09-16 | 1998-04-28 | Praxair S.T. Technology, Inc. | Zirconia-based tipped blades having macrocracked structure and process for producing it |
CN1182459A (zh) * | 1995-04-25 | 1998-05-20 | 西门子公司 | 带有保护性涂层体系的高温合金元件 |
EP1593757A1 (en) * | 2004-05-06 | 2005-11-09 | United Technologies Corporation | Integrated ceramic/metallic components and methods of making same |
CN101204863A (zh) * | 2006-12-19 | 2008-06-25 | 通用电气公司 | 热障涂层系统及用于涂层部件的方法 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4289446A (en) * | 1979-06-27 | 1981-09-15 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
JP2870778B2 (ja) * | 1989-01-25 | 1999-03-17 | 石川島播磨重工業株式会社 | ガスタービンのシュラウド構造 |
US6190124B1 (en) * | 1997-11-26 | 2001-02-20 | United Technologies Corporation | Columnar zirconium oxide abrasive coating for a gas turbine engine seal system |
US20050129511A1 (en) * | 2003-12-11 | 2005-06-16 | Siemens Westinghouse Power Corporation | Turbine blade tip with optimized abrasive |
JP2006104577A (ja) | 2004-10-04 | 2006-04-20 | United Technol Corp <Utc> | セグメント化ガドリニアジルコニア被膜およびその形成方法、セグメント化セラミック被覆システムならびに被膜部品 |
CA2585992C (en) * | 2006-06-08 | 2014-06-17 | Sulzer Metco (Us) Inc. | Dysprosia stabilized zirconia abradable |
US8038388B2 (en) | 2007-03-05 | 2011-10-18 | United Technologies Corporation | Abradable component for a gas turbine engine |
US9447503B2 (en) * | 2007-05-30 | 2016-09-20 | United Technologies Corporation | Closed pore ceramic composite article |
JP2009228018A (ja) * | 2008-03-19 | 2009-10-08 | Mitsubishi Heavy Ind Ltd | 遮熱コーティング材、これを備えたタービン部材及びガスタービン、並びに遮熱コーティング材の製造方法 |
-
2012
- 2012-10-11 FR FR1259704A patent/FR2996874B1/fr not_active Expired - Fee Related
-
2013
- 2013-10-07 WO PCT/FR2013/052370 patent/WO2014057194A1/fr active Application Filing
- 2013-10-07 JP JP2015536199A patent/JP6290224B2/ja not_active Expired - Fee Related
- 2013-10-07 US US14/434,461 patent/US10329928B2/en active Active
- 2013-10-07 PL PL13782804T patent/PL2917502T3/pl unknown
- 2013-10-07 CN CN201380053033.6A patent/CN104718349B/zh active Active
- 2013-10-07 CA CA2887901A patent/CA2887901C/fr active Active
- 2013-10-07 IN IN3013DEN2015 patent/IN2015DN03013A/en unknown
- 2013-10-07 KR KR1020157012319A patent/KR102139395B1/ko active IP Right Grant
- 2013-10-07 RU RU2015117610A patent/RU2647007C2/ru active
- 2013-10-07 EP EP13782804.2A patent/EP2917502B1/fr active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2226050A (en) * | 1988-12-16 | 1990-06-20 | United Technologies Corp | Thin abradable ceramic air seal |
US5743013A (en) * | 1994-09-16 | 1998-04-28 | Praxair S.T. Technology, Inc. | Zirconia-based tipped blades having macrocracked structure and process for producing it |
CN1182459A (zh) * | 1995-04-25 | 1998-05-20 | 西门子公司 | 带有保护性涂层体系的高温合金元件 |
EP1593757A1 (en) * | 2004-05-06 | 2005-11-09 | United Technologies Corporation | Integrated ceramic/metallic components and methods of making same |
CN101204863A (zh) * | 2006-12-19 | 2008-06-25 | 通用电气公司 | 热障涂层系统及用于涂层部件的方法 |
Also Published As
Publication number | Publication date |
---|---|
CN104718349A (zh) | 2015-06-17 |
IN2015DN03013A (zh) | 2015-10-02 |
KR20150067359A (ko) | 2015-06-17 |
US20150267544A1 (en) | 2015-09-24 |
JP6290224B2 (ja) | 2018-03-07 |
EP2917502A1 (fr) | 2015-09-16 |
CA2887901C (fr) | 2020-09-15 |
JP2015537139A (ja) | 2015-12-24 |
FR2996874B1 (fr) | 2014-12-19 |
WO2014057194A1 (fr) | 2014-04-17 |
US10329928B2 (en) | 2019-06-25 |
RU2015117610A (ru) | 2016-12-10 |
EP2917502B1 (fr) | 2019-08-07 |
RU2647007C2 (ru) | 2018-03-13 |
PL2917502T3 (pl) | 2019-12-31 |
FR2996874A1 (fr) | 2014-04-18 |
KR102139395B1 (ko) | 2020-07-29 |
CA2887901A1 (fr) | 2014-04-17 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN104718349B (zh) | 用于燃气涡轮发动机的转子定子组件 | |
CN101125753B (zh) | 可磨耗的氧化镝稳定的氧化锆 | |
KR100813544B1 (ko) | 연마성 밀봉 시스템 | |
US9598973B2 (en) | Seal systems for use in turbomachines and methods of fabricating the same | |
US5952110A (en) | Abrasive ceramic matrix turbine blade tip and method for forming | |
US9260784B2 (en) | Blade tip coating that can be rubbed off | |
CN105177392A (zh) | 燃气涡轮机部件和用于制造燃气涡轮机部件的方法 | |
EP3020931B1 (en) | Abrasive rotor coating with rub force limiting features | |
EP3318719B1 (en) | Turbomachine rotor with coated blades | |
US20210317584A1 (en) | Method for manufacturing an abradable layer | |
US20190054537A1 (en) | Method for manufacturing a turbine shroud for a turbomachine | |
EP3611350B1 (en) | Turbine abrasive blade tips with improved resistance to oxidation | |
US20200248577A1 (en) | Fusible bond for gas turbine engine coating system | |
CN103103473A (zh) | 一种基于热喷涂制备耐冲蚀高温可磨耗封严涂层的方法 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |