CN105623322B - 轴流式涡轮机组压缩机壳体的可磨耗合成物和密封件 - Google Patents
轴流式涡轮机组压缩机壳体的可磨耗合成物和密封件 Download PDFInfo
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Classifications
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- 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
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- C—CHEMISTRY; METALLURGY
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
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- 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
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- 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
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
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- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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- 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
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- F01D9/00—Stators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
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- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- 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
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- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- 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
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- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05D2300/121—Aluminium
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- 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
- F05D2300/16—Other metals not provided for in groups F05D2300/11 - F05D2300/15
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
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Abstract
本发明涉及一种用于轴流式涡轮机组的可磨耗密封件的合成物,该合成物包括铝基体、镍粉末、聚酯粉末。本发明还涉及一种具有围绕转子叶片(24)环形排的可磨耗密封件的轴流式涡轮机组的低压压缩机的外部壳体(28)。密封件包括覆盖有可磨耗材料(38)层的圆形支撑件(34),可磨耗材料层包括主要由铝构成并且具有较小比例的镍的金属相。可磨耗材料还包括25%至55%的添加剂,如聚酯、甲基丙烯酸甲酯、六方氮化硼、氟化钙。支撑件(34)是分段的,并且形成压缩机的有机基质复合外部壳体(28)。本发明还提出了一种通过等离子喷涂铝镍聚酯粉末来制造可磨耗密封件的方法。
Description
技术领域
本发明涉及由可磨耗(abradable)材料制成的轴流式涡轮机组密封件的领域。更明确地,本发明处理由铝基可磨耗材料制成的用于航空器的轴流式涡轮机组压缩机的密封件的主题。
背景技术
用于确保涡轮机组中,尤其是轴流式涡轮机组的压缩机中的动态密封的可磨耗材料是已知的。该材料作为层施加至外部壳体并且在与转子叶片的尖端接触的情况下,其能够腐蚀,而不会损坏它们。尽管旋转速度大于8000rpm,机械完整性任被保持,并且叶片尖端与其密封件之间的相对速度基本上等于声速。该材料还用于确保内部护罩下或驱动轴上的轴承的密封。
以这种方式,能够设计一种压缩机,同时减少转子叶片的尖端与壳体的内表面之间的操作间隙。优化还可以顾及扩展、离心力;以及诸如摄入和抽吸现象的一定的操作风险。形成壳体涂层的可磨耗材料通常包括铝、二氧化硅、聚酯。
专利文献EP1010861 A2公开了一种用于轴流式涡轮机组压缩机的可磨耗材料层的合成物。该合成物包括铝粉末和二氧化硅粉末的混合物,铝占大部分。此外,粉末具有有甲基丙烯酸甲酯的聚合物粉末。该合成物通过等离子喷涂施加在轴流式涡轮机组压缩机的壁上,该壁预先接收具有大量镍并且占较小比例铝的接合层。该合成物能够产生具有耐腐蚀性需求的可磨耗密封件;然而,该耐腐蚀性仍然保证被改善,以便优化涡轮机组的抗性和效率。
发明内容
技术问题
本发明的目的是解决现有技术所造成的问题中的至少一个。更明确地,本发明的一个目的是改善由可磨耗材料制成的轴流式涡轮机组密封件的耐腐蚀性。本发明的另一目的是优化可磨耗材料的耐用性、可磨耗材料的易碎性,以及由可磨耗材料所提供的密封。
技术方案
已经清晰地理解,本发明的一个主题是用于轴流式涡轮机组的密封件,尤其是用于轴流式涡轮机组的压缩机,可选地,低压压缩机;密封件包括:圆形支撑件;至少一个涂层,其由具有主要是金属相或者主要包括铝,尤其是铝粉末的可磨耗材料制成;金属相还包括镍,尤其是镍粉末;可磨耗涂层施加至圆形支撑件,并且通过磨损与轴流式涡轮机组的转子元件协作。
本发明的另一个主题是用于轴流式涡轮机组的密封件可磨耗涂层的合成物,尤其用于通过等离子喷涂施用于圆形支撑件的合成物,该合成物包括:主要是铝的金属,尤其是金属粉末;有机或矿物填充剂,尤其为粉末;值得注意的是,金属还包括镍,尤其是镍粉末。
根据本发明的一有利实施例,金属包括重量在20%至45%之间的镍,优选地35%至45%的镍,尤其是镍粉末。
根据本发明的一有利实施例,金属包括重量在55%至80%的铝,尤其是铝粉末。
根据本发明的一有利实施例,合成物包括重量在5%至50%的填充剂,优选地,15%至25%之间的填充剂;可选地,填充剂为诸如聚酯或甲基丙烯酸甲酯的聚合物;或者六方氮化硼;或者氟化钙;可选为粉末。
根据本发明的一有利实施例,铝和镍的合成物大于合成物的金属重量的80%,优选地,大于90%,更优选地,大于95%。
本发明的另一个主题是一种轴流式涡轮机组的密封件,尤其是轴流式涡轮机组的压缩机的密封件,该密封件包括:圆形支持件;至少一个涂层,其由覆盖圆形支撑件的可磨耗材料制成,并且其通过磨损与轴流式涡轮机组的转子元件协作;值得注意的是,可磨耗涂层的合成物依照本发明。
根据本发明的一有利实施例,在可磨耗涂层中,金属形成与填充剂结合的基质;可选地,在可磨耗涂层中,由金属基质所占的体积是大部分体积。
根据本发明的一有利实施例,圆形支撑件是外部护罩,可磨耗涂层在外部护罩的内侧;或者圆形支撑件是外部壳体,可磨耗涂层定位在外部壳体的内侧。
根据本发明的一有利实施例,支撑件由具有碳纤维和/或玻璃纤维的有机基质复合材料制成,所述纤维被布置成成堆的可选的编织纤维层片。
根据本发明的一有利实施例,支撑件包括附接装置,诸如孔和/或至少一个环形附接突片,所述装置被定位在可磨耗涂层的上游和/或下游。
根据本发明的一有利实施例,支撑件具有有上游边缘和下游边缘的环形凹槽,可磨耗涂层从上游边缘至下游边缘覆盖环形凹槽。
根据本发明的一有利实施例,可磨耗涂层形成具有厚度大于0.30mm的层,优选地,大于2.00mm,更优选地,大于5.00mm。
根据本发明的一有利实施例,涂层在其厚度上和/或其主要区域上形成均匀层。
根据本发明的一有利实施例,圆形支撑件形成圆或圆的一部分。表述“圆的一部分”可以理解为圆的一角部分。
根据本发明的一有利实施例,可磨耗涂层的致密度大于80%,优选地,大于95%,更优选地,大于99%。
根据本发明的一有利实施例,在可磨耗涂层的金属中,铝的体积是大部分体积。
根据本发明的一有利实施例,可磨耗涂层形成密闭的屏障,以便保护支撑件免受涡轮机组的化学侵蚀。
根据本发明的一有利实施例,密封件包括定位在支撑件与可磨耗涂层之间的夹层;优选地,夹层为金属条带。
本发明的另一个主题是一种生产轴流式涡轮机组的可磨耗密封件的方法,尤其是,轴流式涡轮机组的压缩机的可磨耗密封件,该密封件包括圆形支撑件和施加至支撑件的可磨耗涂层,该方法包括以下步骤:(a)圆形支撑件的供应和制造;(d)可磨耗合成物至圆形支撑件的可磨耗施用,该合成物包括金属粉末,其主要包括铝粉末;值得注意的是,在施用步骤(d)过程中,金属粉末还包括镍粉末;可选地,合成物依照本发明。
根据本发明的一有利实施例,在施用步骤(d)过程中,合成物是通过等离子喷涂施加至支撑件;优选地,合成物还包括诸如聚合物的有机粉末,或者矿物粉末。
本发明的另一个主题是一种包括根据一种方法生产的可磨耗密封件的涡轮机组,值得注意的是,可磨耗密封件依照本发明,和/或方法依照本发明。
根据本发明的一有利实施例,涡轮机组包括具有至少一排转子叶片的低压压缩机,密封件是围绕至少一排转子叶片的低压压缩机的密封件。
根据本发明的一有利实施例,涡轮机组包括具有附接至支撑件的平台的至少一环形排定子叶片,可磨耗涂层与叶片的平台接触;优选地,可磨耗涂层形成密闭的屏障,保护支撑件从平台轴向地起动。该密封件提供双重密封;即,动态密封和静态密封。
根据本发明的一有利实施例,支撑件是连接至定子叶片排的内部端部的内部护罩,可磨耗涂层施加至内部护罩的内侧。
根据本发明的一有利实施例,压缩机包括能够加热可磨耗材料涂层的加热元件,和/或压缩机包括流排放端口。
根据本发明的一有利实施例,可磨耗密封件的内表面引导涡轮机组的环形流,通常是轴向环形流。
通常,本发明的每个主题的有利实施例也适用于本发明的其它主题。
提供的优点
由本发明提供的性能限制了诸如聚合物的填充剂释放至涡轮机组中,以免在干扰此处的燃烧。阻碍管道和机构或者磨损机构的颗粒的释放被限制。这些优点落在提高安全性的上下文中。
本发明与低压压缩机的上下文尤其相关,因为进入其中的空气可能是-50℃,并且在压缩机出口处可能是+170℃。所提出的合成物是适用于低温的温度并且适用于中间温度,用于初级流的温度变化,作为大于200℃的温度范围中,航空器的飞行阶段的功能。本发明还能够保持可磨耗材料的耐热性。
铝镍聚酯合成物提供一定的耐腐蚀性,尤其是面临作为测试证明的盐雾。抵抗性可在温度的宽范围内观察,例如从-50℃至大于150℃。随着时间的推移,抵抗力也不妨碍密封,不会过早地降低转子叶片。这些优点隔开涡轮机组的维护操作,这能够进行大量的节省。
附图说明
图1表示根据本发明的轴流式涡轮机组。
图2是根据本发明的轴流式涡轮机组压缩机的图形。
图3略述了根据本发明的涡轮机组可磨耗密封件。
图4示出了用于制造根据本发明的涡轮机组可磨耗密封件的方法的流程图。
具体实施方式
在下面的描述中,术语内部的或内部以及外部的或外部涉及相对于轴流式涡轮机组的旋转轴线的位置。轴向方向对应于沿涡轮机组的旋转轴线的方向。
图1表示简化形式的轴流式涡轮机组。在这个特定例子中,其是涡轮风扇喷气发动机。该涡轮风扇喷气发动机2包括称为低压压缩机4的第一压缩级、称为高压压缩机6的第二压缩级、燃烧室8,以及一个或多个涡轮机级10。在操作中,由中心轴传输至转子12的涡轮机10的机械动力运转两个压缩机4和6。两个压缩机包括与定子叶片排结合的若干转子叶片排。因此,转子关于其旋转轴线14的旋转能够产生空气流并且逐渐地压缩该流直到燃烧室8的入口。齿轮减速装置可以增加传输至压缩机的转速。
通常由风扇或鼓风机16表示的入口风扇被联接至转子12,并且产生空气流,该空气流分成穿过涡轮机组的上述不同级的初级流18以及沿机器穿过环形管道(部分示出)以便随后在涡轮机的出口处与初级流再结合的次级流20。次级流可以被加速以便产生推进反应。初级流18和次级流20是环形流;其由涡轮机组的壳体来引导。为此,壳体具有可以是内部和外部壁或护罩的圆柱壁或护罩。
图2是如在图1中的轴流式涡轮机组的压缩机的横截面的视图。压缩机可以是低压压缩机4。此处,部分鼓风机16以及用于分离初级流18和次级流20的分流器22在此处可见。转子12包括若干转子叶片排24,在该特定例子中是三排。
低压压缩机4包括若干调直器,在该特定例子中是四个,其中每个调直器包括一排定子叶片26。调直器与鼓风机16结合或者与转子叶片排结合,以便使空气流变直,从而将流的速度转换成静态压力。定子叶片26从压缩机的外部壳体28基本上径向地延伸,并且在径向延伸的螺栓30的协助下,可以附接至定子叶片26的平台32。
壳体28可包括环形壁34和环形附接凸缘36,其轴向地限制壁34。外部壳体28可以由两个半壳形成。壁34形成套筒并且具有卵形(ogive)形状,并且其旋转轮廓是弯曲的并且主要轴向地延伸;其半径是变化的。壁34作为支撑件,用于附接至定子叶片26的附接平台32,并且作为支撑件,用于确保动态密封的可磨耗材料38的涂层的施用;以便形成围绕转子叶片24的可磨耗密封件39。可磨耗涂层38形成均匀的环形层,诸如厚度大于2.00mm的圆形条带。动态密封被理解为在涡轮机组的运行期间,可磨耗材料与转动的转子叶片之间的流的限制。
环状附接凸缘36径向向外延伸。壳体28上游和下游的环形凸缘36能够将压缩机4附接至中间鼓风机壳体40,但也能够附接分流器22。附接凸缘36可包括轴向附接孔(未示出)以及管状支座。可磨耗涂层38可轴向地定位在环形附接凸缘36之间。
壳体28,尤其是其壁34可以由有机基质复合材料制成。该复合材料可包括环氧树脂和具有成堆的三维编织碳纤维层片的预型体。可替换地,壳体可以由金属制成,诸如钛或铝合金。根据本发明的一替代方案,壳体可以由若干外部护罩形成,例如,使用径向环形凸缘轴向地添加和附接至彼此。
定子叶片26排可以支持连接至定子叶片26的内部端部的内部护罩42。内部护罩42的内表面可以支撑可磨耗材料44的层,以便形成围绕转子12的环形条带或唇部的密封件45,从而防止内部护罩42下的再流通。
术语“涂层”可以理解为密封件(39;45)的结构的外层,空气在其上流动并且其受到空气动力。涂层可形成密封件(39;45)的外表面或内表面。
图3表示如图2中的压缩机的可磨耗密封39。此处所表示的是壳体28的壁34,或支撑件28,施加至其上的可磨耗涂层38,以及两个定子叶片26之间的转子叶片24的尖端。
可磨耗涂层38从叶片26的平台32延伸至下一个叶片的平台,其属于位于上游或下游的相邻排。可磨耗涂层38与平台32的内表面齐平。定子叶片26的平台32形成轴向限制可磨耗涂层38的圆形轴肩46。可替代地,壁具有在其厚度中形成的径向环形凹槽,在其整个深度上由可磨耗涂层填充。可磨耗涂层覆盖定子叶片的平台之间的壁的整个内表面。可选地,除了平台32与相同环形排之间的凹槽,平台32和可磨耗涂层38的结合形成全部沿壳体28,或者至少壁34的大致密闭的屏障。
可磨耗涂层38可直接施加在其支撑件34上。否则,密封件39可以包括支撑件与可磨耗涂层之间的夹层。该夹层可以是诸如钢板或镍板的条带。该条带可以被穿孔和/或切割。
可磨耗涂层38具有与初级流18接触的内表面。在其压缩期间,其表面引导和限制初级流18。可磨耗涂层38可包括至少两个混合相,即金属相和可选的填充剂相,诸如矿物相和/或有机填充剂,以便形成复合材料。可磨耗涂层的材料可以是粒状,或者一些可以是粒状并且其它可以以其颗粒之间的空间来填充。
可磨耗涂层38的金属相主要包括铝。涂层的金属相是基于铝的。也就是说,可磨耗材料的金属中,具有最大权重的是铝。铝的优势优化了密封件39的重量。可磨耗涂层38的金属相还包括镍,重量比例低于铝的重量比例。金属相可包括20%至45%之间的镍;以及55%至80%之间的铝。此外,金属相可选择性地包括铁、铜、锌、锰、镁、杂质;这些组分中的每个在金属相的重量的1%至0.1%之间。
可磨耗涂层38的填充剂可以包括聚合物,诸如,聚酯或甲基丙烯酸甲酯。填充剂还可包括六方氮化硼或氟化钙。填充剂的重量可在涂层38的重量的5%至50%之间,优选地在15%至25%之间,可选为20%。金属相可占可磨耗涂层的大部分体积;从而金属相可以形成在其中接收填充剂或添加剂的基质。可选地,可磨耗涂层可以由金属粉末的颗粒形成,粒间空间(intergranular space)由填充剂填充。在可磨耗涂层中的空的空间小于1%,优选地小于0.1%。
图4表示产生如图3所示的轴流式涡轮机组的可磨耗密封件的方法的流程图。密封件可以使用在压缩机中,尤其是,低压压缩机。
该方法包括下列步骤,可选地,以下列顺序进行:
(a)诸如压缩机外部壳体的圆形支撑件的供应100,
(b)具有平台的定子叶片的供应102,
(c)通过其平台,叶片至形成环形排的圆形支撑件的附接104,
(d)用于平台的环形排之间的圆形支撑件的可磨耗合成物的施用106,以便覆盖叶片排平台之间的支撑件,
(e)围绕涡轮机组的转子,例如转子叶片的环形排,的支撑件的组装108。
在施用106步骤(d)开始时,合成物具有主要是铝的金属相,例如铝以粉末的形式。该金属相还可包括镍和填充剂;两者均为粉末。粉末的合成物可以对应于上面提出的可磨耗涂层的化学合成物。在施用106步骤(d)结束时,合成物的至少一个或每个化合物保持粉末形式,或者化合物中的至少一个熔化,或者每化合物熔化。
可选地,一些颗粒或每种类型的颗粒基本上是固体,并且其各自的空隙小于其材料的5%,优选地小于1%,更优选地小于0.20%。每个颗粒可以具有均匀的材料。可选地,一种类型的颗粒是中空的,例如铝或镍颗粒。
在施用106步骤(d)过程中,合成物可通过等离子喷涂施加至支撑件。对于本领域技术人员来说,该技术是公知的,并且其可以以类似于专利文献EP1010861 A2中公开的方式进行。填充剂粉末可以引入到金属粉末的下游的等离子射流中。可以设想其它技术。可替代地,该合成物可以通过可选地具有延长加热的烧结施加至支撑件。在该替代方案中,一定的颗粒可以保持其初始的形状。
步骤:(b)定子叶片的供应102;(c)叶片的附接104;(e)支撑件的组装108;根据本发明是完全可选的。事实上,可磨耗合成物可以施加至叶片的自由支撑件和其平台上。在这种情况下,施用106步骤(d)可以在护罩厚度中形成的凹槽中进行。
Claims (18)
1.一种轴流式涡轮机组(2)的压缩机(4;6)的密封件(39;45),所述密封件(39;45)包括:
圆形支撑件(34;42);
至少一个涂层,其由覆盖所述圆形支撑件(34;42)的可磨耗涂层(38;44)制成,并且其通过磨损与所述轴流式涡轮机组(2)的转子元件(24)协作;
其中,用于可磨耗涂层(38;44)的合成物包括:
金属,所述金属包括重量在55%至80%范围内的铝和在20%至45%范围内的镍;
有机或矿物填充剂。
2.根据权利要求1所述的密封件,其特征在于,所述金属为金属粉末。
3.根据权利要求1所述的密封件,其特征在于,所述有机或矿物填充剂为粉末。
4.根据权利要求1所述的密封件,其特征在于,其包括重量在5%至50%的填充剂;所述填充剂为聚酯或甲基丙烯酸甲酯的聚合物;或者六方氮化硼;或者氟化钙。
5.根据权利要求4所述的密封件,其特征在于,其包括重量在15%至25%之间的填充剂。
6.根据权利要求4所述的密封件,其特征在于,所述填充剂为粉末。
7.根据权利要求1所述的密封件(39;45),其特征在于,在所述可磨耗涂层中,所述金属形成与所述填充剂结合的金属基质。
8.根据权利要求1所述的密封件(39;45),其特征在于,所述圆形支撑件是外部护罩,所述可磨耗涂层在所述外部护罩的内侧;或者所述圆形支撑件是外部壳体(28),所述可磨耗涂层(38)定位在所述外部壳体(28)的内侧。
9.根据权利要求1所述的密封件(39;45),其特征在于,所述支撑件(34;42)由具有碳纤维和/或玻璃纤维的有机基质复合材料制成,所述纤维被布置成堆叠的编织纤维层片。
10.根据权利要求1所述的密封件(39;45),其特征在于,所述支撑件(34;42)包括附接装置(36),所述装置(36)被定位在所述可磨耗涂层(38;44)的上游和/或下游。
11.根据权利要求10所述的密封件(39;45),其特征在于,所述附接装置是孔和/或至少一个环形附接突片。
12.根据权利要求1所述的密封件(39;45),其特征在于,所述支撑件(34;42)具有带有上游边缘和下游边缘的环形凹槽,所述可磨耗涂层(38;44)从所述上游边缘至所述下游边缘覆盖所述环形凹槽。
13.一种用于生产轴流式涡轮机组(2)的压缩机(4;6)的密封件(39;45)的方法,所述密封件(39;45)包括圆形支撑件(34;42)和施加至所述支撑件的可磨耗涂层(38;44),所述方法包括以下步骤:
(a)圆形支撑件(34;42)的供应和制造(100);
(d)可磨耗合成物至所述圆形支撑件(34;42)的可磨耗施用(106),所述合成物包括金属粉末,其包括重量在55%至80%范围内的铝粉末和20%至45%范围内的镍粉末。
14.根据权利要求13所述的方法,其特征在于,在所述施用步骤(d)过程中,所述合成物是通过等离子喷涂施加至所述支撑件(34;42);所述合成物还包括有机粉末,或者矿物粉末。
15.根据权利要求14所述的方法,其特征在于,所述有机粉末是聚合物。
16.涡轮机组(2),包括根据一种方法生产的密封件(39;45),其特征在于,所述密封件(39;45)是根据权利要求1至7中的其中一项,和/或所述方法是根据权利要求8和9中的任一项。
17.根据权利要求16所述的涡轮机组(2),其特征在于,其包括具有至少一排转子叶片(24)的低压压缩机(4),所述密封件是围绕所述至少一排转子叶片(24)的所述低压压缩机(4)的密封件(39)。
18.根据权利要求16和17中任一项所述的涡轮机组(2),其特征在于,其包括具有附接至所述支撑件(34;42)的平台(32)的至少一环形排定子叶片(26),所述可磨耗涂层与叶片(26)的所述平台(32)接触;所述可磨耗涂层形成密闭的屏障,保护所述支撑件(34;42)轴向地所述平台(32)起动。
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EP14194526.1 | 2014-11-24 | ||
EP14194526.1A EP3023511B1 (fr) | 2014-11-24 | 2014-11-24 | Composition et joint abradable de carter de compresseur de turbomachine axiale |
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CN105623322A CN105623322A (zh) | 2016-06-01 |
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EP (1) | EP3023511B1 (zh) |
JP (1) | JP6640484B2 (zh) |
CN (1) | CN105623322B (zh) |
CA (1) | CA2899395C (zh) |
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DE102015202070A1 (de) * | 2015-02-05 | 2016-08-25 | MTU Aero Engines AG | Gasturbinenbauteil |
BE1024735B1 (fr) | 2016-11-15 | 2018-06-19 | Safran Aero Boosters Sa | Virole antigivre de compresseur de turbomachine axiale |
BE1025077B1 (fr) * | 2017-03-22 | 2018-10-23 | Safran Aero Boosters S.A. | Capot de turbomachine avec ecran |
US10900371B2 (en) | 2017-07-27 | 2021-01-26 | Rolls-Royce North American Technologies, Inc. | Abradable coatings for high-performance systems |
US10858950B2 (en) | 2017-07-27 | 2020-12-08 | Rolls-Royce North America Technologies, Inc. | Multilayer abradable coatings for high-performance systems |
BE1025469B1 (fr) * | 2017-08-14 | 2019-03-18 | Safran Aero Boosters S.A. | Composition de joint abradable pour compresseur de turbomachine |
US10808565B2 (en) * | 2018-05-22 | 2020-10-20 | Rolls-Royce Plc | Tapered abradable coatings |
FR3085172B1 (fr) * | 2018-08-22 | 2021-03-05 | Safran Aircraft Engines | Revetement abradable pour aubes tournantes d'une turbomachine |
FR3086348B1 (fr) * | 2018-09-21 | 2020-12-04 | Safran Aircraft Engines | Turboreacteur a reducteur |
BE1027280B1 (fr) * | 2019-05-16 | 2020-12-15 | Safran Aero Boosters Sa | Carter de compresseur pour turbomachine |
CN110564261A (zh) * | 2019-08-19 | 2019-12-13 | 安徽省含山县兴建铸造厂 | 一种提升防震锤强度和耐腐性的涂层的制备方法 |
CN111765248A (zh) * | 2020-05-12 | 2020-10-13 | 中国大唐集团科学技术研究院有限公司火力发电技术研究院 | 一种可磨涂层活动式密封油挡 |
CN111878583A (zh) * | 2020-07-30 | 2020-11-03 | 安徽日亮氟塑密封件有限公司 | 一种低摩擦油封结构 |
CN112648375B (zh) * | 2020-12-16 | 2023-03-24 | 天津包博特密封科技有限公司 | 泥泵密封水室用加强型聚醚型聚酯轴封组件 |
CN112646407B (zh) * | 2020-12-21 | 2021-10-22 | 武汉钢铁有限公司 | 一种用于压缩机级间密封装置的涂料 |
BE1031024B9 (fr) | 2022-11-09 | 2024-07-08 | Safran Aero Boosters | Composition pour joint abradable de turbomachine |
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US10001024B2 (en) | 2018-06-19 |
JP2016098810A (ja) | 2016-05-30 |
US20160146034A1 (en) | 2016-05-26 |
EP3023511A1 (fr) | 2016-05-25 |
CA2899395C (en) | 2020-02-11 |
EP3023511B1 (fr) | 2021-07-28 |
JP6640484B2 (ja) | 2020-02-05 |
CA2899395A1 (en) | 2016-05-24 |
CN105623322A (zh) | 2016-06-01 |
RU2015136394A3 (zh) | 2019-01-10 |
RU2015136394A (ru) | 2017-03-07 |
PL3023511T3 (pl) | 2021-12-20 |
RU2695090C2 (ru) | 2019-07-19 |
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