CN115768966A - 具有金属前缘的涡轮机叶片 - Google Patents

具有金属前缘的涡轮机叶片 Download PDF

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CN115768966A
CN115768966A CN202180043648.5A CN202180043648A CN115768966A CN 115768966 A CN115768966 A CN 115768966A CN 202180043648 A CN202180043648 A CN 202180043648A CN 115768966 A CN115768966 A CN 115768966A
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blade
foil
extrados
intrados
leading edge
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A·莫拉蒂
B·本贝尔加克姆
C·伊格勒希亚斯卡诺
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
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    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
    • 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
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    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
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    • 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
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • 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
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
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    • 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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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
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    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract

一种用于涡轮机的叶片(200)，包括由纤维增强复合材料制成的叶片主体(240)和由金属箔(220)形成的金属前缘(250)，纤维增强复合材料由基质致密化，该箔具有分别在叶片主体的压力面(241)和吸引面(142)上延伸的压力面翼片(221)和吸引面翼片(222)，围绕叶片的气动轮廓卷绕，其特征在于，该叶片还包括由复合材料制成的至少一层单向织物(230)，其处于叶片主体和金属箔之间的前缘上，每层单向织物在叶片主体的压力面和吸引面的至少一部分上延伸。

Description

具有金属前缘的涡轮机叶片
技术领域
本发明涉及由复合材料制成的用于航空燃气涡轮发动机或航空涡轮机的叶片的一般领域，更具体地，涉及具有金属前缘的涡轮机叶片。
背景技术
为了保护叶片的复合叶片配列(blading)或主体免受磨损、侵蚀和/或异物冲击，叶片包括加强前缘，尤其是由钛制成的一体式前缘。
通过粘合在叶片配列上组装该钛前缘。尽管如此，这种类型的前缘在其整个生命周期中会产生巨大的材料及制造成本、以及不顺应性。
事实上，钛材料的成本很高，叶片的制造需要许多步骤以及材料废品。此外，在将钛前缘组装到叶片配列上期间，必须在粘合前缘之前准备叶片配列的表面，而后者需要预先通过长的高压釜循环。还需要调整叶片配列的接纳前缘的腔体，该腔体经常太宽或太窄，这导致叶片配列的翼片水平处的波纹和/或条纹。
在制造包括这种前缘的叶片的中间零件期间，也可以观察到安装开始时零件的不顺应性，而中间零件(钛前缘)是顺应的。
在不改变整个前缘的情况下，也很难修理这种损坏的前缘。
因此，希望有一种航空涡轮机叶片，其在制造和维护期间较便宜，且更易于修理。
发明内容
本发明涉及一种涡轮机叶片，包括由复合材料制成的叶片配列和由金属箔形成的金属前缘，该复合材料具有由基质致密化的纤维增强件，该箔具有通过符合该叶片的翼型而分别在叶片配列的内弧面和外弧面上延伸的内弧面翼片和外弧面翼片，其特征在于，该叶片还包括在叶片配列和金属箔之间的前缘上由复合材料制成的至少一个单向织物层，每个织物层至少部分地在叶片配列的内弧面和外弧面上延伸。
这种前缘可以容易地组装在叶片配列上，并且可以在不触碰或损坏叶片配列的复合结构的情况下修理，因为用仅与单向织物层接触的另一箔替换损坏和/或不顺应的箔就足够了。此外，本发明的前沿允许以较低的成本设计、生产和修理叶片。事实上，金属箔的厚度比单件式钛前缘的厚度小得多，因此在制造或修理叶片期间，材料的成本会降低。
使用这种类型的前缘也更容易适应特定的叶片几何约束，例如通过在叶片配列的内弧面或外弧面上延伸金属箔而不改变叶片配列的内部结构来加强叶片的面部之一。
根据本发明的一个实施例，金属箔在叶片配列的内弧面上延伸第一长度，在叶片配列的外弧面上延伸第二长度。
这允许设计一种叶片，其由箔所提供的金属加强件在叶片配列的内弧面(或外弧面)上延伸的长度大于叶片配列的外弧面(或内弧面)。
根据本发明的另一实施例，第一长度和第二长度相等。
这允许获得相对于连接叶片的前缘和后缘的轴线对称的前缘。
根据本发明的一个特定特征，每个单向织物层在箔的内弧面翼片和外弧面翼片的整个内表面上延伸。
这允许金属箔与叶片配列之间不直接接触。因此，金属箔的更换将被简化，因为它不会影响叶片配列的内部结构，并且在铺设新箔之前不需要准备叶片配列的表面。
根据本发明的一个实施例，叶片包括在金属箔和叶片配列之间的前缘上由复合材料制成的多个单向织物层，多个织物层的层彼此覆盖，并且至少部分地在叶片配列的内弧面和外弧面上延伸。
单向织物层允许在前缘损坏和更换金属箔的情况下保护叶片配列的内部结构。此外，由于这些层彼此覆盖，因此避免了在叶片的制造、使用或修理期间在多个层的各层之间可能发生的波纹或条纹现象。
根据本发明的一个特定特征，在所述至少一个单向织物层与金属箔之间存在粘合膜。
根据本发明的另一特定特征，一旦完成了单向织物层的覆盖，就共同注射金属箔和其余叶片。
根据本发明的另一特定特征，在所述至少一个单向织物层与叶片配列之间存在粘合膜。
这些不同的特性(粘合膜、共同注射和覆盖)允许将金属箔固定就位在单向织物层上，并将单向层保持就位在叶片配列上。
根据本发明的另一特定特征，每个单向织物层的复合材料包括Kevlar纤维。
根据本发明的另一特定特征，叶片配列是用玻璃纤维编织的三维零件，编织可以是部分的或全部的。
根据本发明的另一特定特征，金属箔在内弧面和外弧面上的厚度包括在0.1mm到0.5mm之间。
根据本发明的另一特定特征，所述至少一个单向织物层的厚度包括在0.15mm到0.25mm之间。
根据本发明的另一特定特征，该组单向织物层的厚道包括在0.2mm到1mm之间。
根据本发明的另一特定特征，叶片构成出口导叶、入口导叶、风扇叶片或变桨距叶片。
本发明的另一目的是一种用于修复根据本发明的涡轮机叶片的方法，包括移除金属箔、准备新金属箔的表面以及将所述新金属箔定位在至少一个单向织物层上。
附图说明
通过参考附图给出的以下描述，本发明的其它特征和优点会变得明显，这些附图示出不具有限制性的示例性实施例。
[图1]图1示意性且部分地示出了根据本发明一实施例的叶片的视图。
[图2]图2示意性且部分地示出了根据本发明一实施例的叶片的剖视图。
[图3]图3示意性且部分地示出了根据本发明一实施例的叶片的剖视图。
[图4]图4示出了表示根据本发明一实施例的叶片修理方法的不同步骤的流程图。
具体实施方式
图1至3中所示的叶片例如可以是固定叶片或流量矫直器。
图1示意性且部分地示出了根据本发明的叶片100。叶片100包括叶片配列140，该叶片配列140沿纵向方向L在内平台141和外平台142之间延伸，该纵向方向L对应于当叶片100安装在涡轮机中时的径向方向。叶片配列140沿横向方向T在前缘150和后缘151之间延伸。
叶片配列140由三维复合材料制成，更具体地，由具有由基质致密化的纤维增强件的复合材料制成。纤维增强件可以包括碳纤维，基质可以是有机类型的并且由致密化树脂获得。替代地，纤维增强件可以包括编织玻璃纤维。
放置在叶片配列140上的金属箔120通过符合叶片配列140的翼型来覆盖叶片配列140的前缘150。
由复合材料制成的至少一个单向织物层(图1中未示出)放置在前缘150上的叶片配列140和箔120之间。
图2示意性且部分地示出了根据本发明一实施例的叶片200的叶片配列240沿着图1的平面II的剖视图。
金属箔220包括分别在叶片配列240的内弧面241的部分和外弧面242的部分上延伸的内弧面翼片221和外弧面翼片222。翼片221和222集成到叶片配列240中，使得它们通过限定叶片200的翼型的部分而符合该翼型。
根据本发明，叶片200还包括放置在金属箔220和叶片配列240之间的由复合材料230制成的至少一个单向织物层。在图2的示例中示出了单个层230。该织物层230允许箔220和叶片配列240的纤维结构之间不直接接触。
在图2的示例中，箔220和织物层230在叶片配列240的内弧面241和外弧面242上延伸相同的长度。因此，织物层230在箔220的内弧面翼片221和外弧面翼片222的整个内表面上延伸。箔220还关于在叶片200的前缘250和后缘之间延伸的轴线对称。
织物层230具有包括在0.15mm到0.25mm之间的厚度。织物层220具有包括在0.1mm到0.5mm之间的厚度。
图3示意性且部分地示出了根据本发明另一实施例的叶片300的叶片配列340的剖视图。
金属箔320总是包括分别在叶片配列340的内弧面341的部分和外弧面342的部分上延伸的内弧面翼片和外弧面翼片。翼片总是集成到叶片配列340中，以符合叶片300的翼型。
在所示出的示例中，叶片300包括多个单向织物层330。具体地，图3的示例包括三层331、332和333。层331、332和333彼此覆盖。例如，该覆盖可以由预浸渍有环氧树脂的单个单向层形成。
在该示例中，箔320在叶片配列340的内弧面341上延伸第一长度L1，在叶片配列340的外弧面342上延伸第二长度L2。因此，箔320相对于在叶片300的前缘350和后缘之间延伸的轴线对称。在该示例中，层331、332、333在叶片配列340的内弧面341和外弧面342上延伸相同的长度L1和L2。但是它们也可以延伸对于叶片配列340的内弧面341而言大于L1的长度、对于叶片配列340的外弧面342而言大于L2的长度，这允许在叶片300的制造或修理期间在组装和/或移除箔320的过程中保护叶片配列340。长度L1和L2也可以在叶片300的高度上变化，并且在比例方面可以对换，即L1可以大于L2，且反之亦然。
多个层330的厚度例如包括在0.2mm到1mm之间，金属箔320的厚度在0.1mm到0.5mm之间。
无论实施例如何，为了将箔固定在叶片配列上，在金属箔和单向织物层之间也可以存在粘合膜。
无论实施例如何，为了将箔固定在叶片配列上，金属箔可以在覆盖织物层之后与包括叶片配列和单向织物层的叶片配列共烧(co-fired)。
无论实施例如何，为了将织物层固定在叶片配列上，可以将预浸渍有树脂的层覆盖在一起。在烧制期间，预浸渍层的树脂将聚合并固化。
无论本发明的实施例如何，形成金属箔的材料可以包括钛和/或铝的合金。
无论本发明的实施例如何，单向织物层的复合材料包括Kevlar纤维。Kevlar的优点是具有高抗冲击性，其允许保护叶片，例如在与鸟类碰撞时。
无论本发明的实施例如何，叶片配列可以是三维零件，其可以从三维纤维编织得到。其可以例如由诸如碳纤维之类的有机纤维或玻璃纤维编织而成。然后，纤维被可以是有机类型的基质致密化。
无论实施例如何，叶片可以构成出口导叶、入口导叶、风扇叶片或变桨距叶片。更具体地，叶片可以在涡轮机的低压压缩机的水平面处构成任何风扇叶片。
本发明还涉及根据本发明的修理叶片的方法。图4示出了根据本发明的修理方法的示例的不同步骤。
该方法的第一步骤401包括从叶片移除金属箔。该箔可能例如在使用叶片之后被损坏。为了移除箔，例如可以将其剥离。
在第二步骤402中，准备新金属箔的表面。
在第三步骤403中，将新箔定位并组装在叶片的前缘上。可以通过粘结或通过新箔、织物层与叶片配列的共烧而将新箔组装在单向织物层上。例如在高压釜中执行共烧，使树脂在整个零件中聚合。
表述“包括在…和(到)…之间”必须理解为包含边界。

Claims (10)

1.一种涡轮机叶片(100、200、300)，包括由复合材料制成的叶片配列(140、240、340)和由金属箔(120、220、320)形成的金属前缘(150、250、350)，所述复合材料具有由基质致密化的纤维增强件，所述箔具有通过符合所述叶片的翼型而分别在所述叶片配列的内弧面(241、341)和外弧面(242、342)上延伸的内弧面翼片(221)和外弧面翼片(222)，其特征在于，所述叶片还包括在所述叶片配列和所述金属箔之间的前缘上由复合材料制成的至少一个单向织物层(230、331、332、333)，每个织物层至少部分地在所述叶片配列的内弧面和外弧面上延伸。
2.根据权利要求1所述的涡轮机叶片，其特征在于，所述金属箔在所述叶片配列的内弧面上延伸第一长度(L1)，并且在所述叶片配列的外弧面上延伸第二长度(L2)。
3.根据权利要求2所述的涡轮机叶片，其特征在于，所述第一长度和所述第二长度相等。
4.根据权利要求1至3中任一项所述的涡轮机叶片，其特征在于，每个所述单向织物层在所述箔的内弧面翼片和外弧面翼片的整个内表面上延伸。
5.根据权利要求1至4中任一项所述的涡轮机叶片(300)，其特征在于，所述叶片包括在所述金属箔和所述叶片配列之间的前缘上由复合材料制成的多个(330)单向织物层(331、332、333)，所述多个织物层的层彼此覆盖，并通过符合所述叶片的翼型而在所述叶片配列(340)的内弧面(341)和外弧面(342)上延伸。
6.根据权利要求1至5中任一项所述的涡轮机叶片，其特征在于，在所述至少一个单向织物层与所述金属箔之间存在粘合膜。
7.根据权利要求1至6中任一项所述的涡轮机叶片，其特征在于，所述金属箔在所述内弧面和所述外弧面上的厚度包括在0.1mm到0.5mm之间。
8.根据权利要求1至7中任一项所述的涡轮机叶片，其特征在于，所述至少一个单向织物层的厚度包括在0.15mm到0.25mm之间。
9.根据权利要求1至8中任一项所述的涡轮机叶片，其特征在于，所述涡轮机叶片构成出口导叶、入口导叶、风扇叶片或变桨距叶片。
10.一种用于修理根据权利要求1至9中任一项所述的涡轮机叶片的方法，包括移除金属箔(401)、准备新金属箔的表面(402)以及将所述新金属箔定位在至少一个单向织物层(403)上。
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