CN110248912A - 一种制造复合材料部件的方法 - Google Patents
一种制造复合材料部件的方法 Download PDFInfo
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- CN110248912A CN110248912A CN201880010136.7A CN201880010136A CN110248912A CN 110248912 A CN110248912 A CN 110248912A CN 201880010136 A CN201880010136 A CN 201880010136A CN 110248912 A CN110248912 A CN 110248912A
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- Prior art keywords
- thermoplastic polymer
- fiber
- matrix
- fibre
- component
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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
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- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
- B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
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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
- B29C70/003—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised by the matrix material, e.g. material composition or physical properties
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- 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
- B29C70/30—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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
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Abstract
本发明涉及一种用复合材料制造部件的方法,所述方法包括以下步骤:形成待制造部件的纤维预制件,涉及浸渍有热塑性聚合物的多个纤维结构(3)的表面沉积,所述沉积借助于自动纤维布置进行;借助于溶剂溶解从预制件中除去热塑性聚合物;以及在除去热塑性聚合物之后,将液体浸渍组合物注入纤维预制件的多孔结构中,以在纤维预制件的多孔结构中形成基质。
Description
背景技术
本发明涉及一种使用自动纤维布置(AFP)技术制造复合材料部件的方法。
已知通过以层的形式覆盖预浸渍的纤维增强材料来制造复合材料部件。在某些现有技术中,覆盖由操作者手动执行。这些技术可能导致相对较高的部件的生产成本以及层定位中的错误的风险。这导致所获得的部件的机械性能在一定程度上的可变性,并且还导致具有可以改进的机械性能的部件。
已经开发了其他解决方案,诸如自动纤维布置技术。该机械技术具有降低制造由复合材料制成的部件的成本的优点。在现有技术中,将浸渍有含陶瓷颗粒的水悬浮液的纤维层覆盖在表面上,以获得待获得部件的预制件。然后干燥所得的预制件,然后烧结陶瓷颗粒,以便在预制件的孔隙中形成基质。然而,通过现有技术的自动纤维布置技术获得的部件的机械性能仍然可以得到改善,特别是因为基质内存在残留的孔隙。
还已知US5188782,其公开了由陶瓷或金属纤维制造预制件;FR3033729,其公开了一种带有红外线加热器系统的光纤敷料器头;EP1472060,其公开了一种具有短效粘合剂的碳带和相关的使用方法;US5439627,其公开了一种制造增强复合材料的方法;以及US2013/0149491,其公开了一种由纤维带制成的复合制品。
因此,需要一种方法,该方法能够以低生产成本以获得具有改进的机械性能的复合材料部件。
发明内容
为此,在第一方面,本发明提供了一种制造复合部件的方法,该方法包括以下步骤:
-通过将浸渍有热塑性聚合物的多个纤维结构沉积到表面上来形成用于待获得部件的纤维预制件,通过自动纤维布置进行沉积;
-通过溶剂溶解除去预制件中存在的热塑性聚合物;和
-在除去热塑性聚合物之后,将液体浸渍组合物注入纤维预制件的孔隙中,以在纤维预制件的孔隙中形成基质。
出于简洁的原因,自动纤维布置技术在下文称为“AFP技术”。
热塑性聚合物涂布纤维结构的全部或部分纤维赋予其内聚力和粘合能力,其足以与通过AFP技术制造纤维预制件相容。在本发明中,热塑性聚合物用作短效粘合剂,其可用于构造预制件,但随后在形成基质之前除去而不留下任何有害残留物。这种除去可以释放预制件中的孔隙,从而可以通过注入将用于形成基质的材料引入纤维之间和纤维内的孔隙中。本发明的方法与现有技术的AFP技术的不同之处在于,用于形成基质的成分在形成预制件时不与纤维一起输送,而是相反在形成预制件和除去热塑性聚合物的步骤之后通过注入浸渍组合物来输送。与现有技术的AFP技术相比,通过这种注入技术输送基质有利地通过显著减少大孔隙的体积来改善所形成的基质的质量,其中大孔隙形成是预先浸渍基质成分的覆盖层的技术所固有的。因此,本发明可以以降低的生产成本来制造具有改进的机械性能的复合材料部件,从而尤其可以获得由这些部件制成的更轻的元件,同时保持所需的机械性能。
在一种实施方式中,热塑性聚合物的玻璃化转变温度高于或等于50℃。
这种特性有助于改善由热塑性聚合物浸渍的纤维随时间的稳定性,并限制纤维在环境温度(20℃)下的粘性,从而使其在通过AFP技术沉积之前更容易储存并使它们更容易输送到AFP沉积头的压紧元件。
在一种实施方式中,热塑性聚合物的熔融温度高于或等于50℃,例如在50℃至250℃的范围内,或实际上在150℃至200℃的范围内。
这种特性有助于限制纤维在环境温度下的粘性,从而使它们在通过AFP技术沉积之前更容易储存并使它们更容易输送到沉积头中。然后可以通过AFP技术在沉积期间加热来获得所需的粘合能力,以软化或实际上熔化热塑性聚合物。
在一种实施方式中,热塑性聚合物选自:聚亚烷基碳酸酯;聚酯;聚甲基丙烯酸甲酯(PMMA);聚乙烯醇(PVA);聚乙烯吡咯烷酮(PVP);聚乙二醇(PEGs);麦芽糊精;纤维素聚合物;蜡;及其混合物。
在一种实施方式中,热塑性聚合物是水溶性的。然后溶剂是含水的。特别地,水溶性热塑性聚合物可选自:聚乙烯醇(PVA)、聚乙烯吡咯烷酮(PVP)、聚乙二醇(PEG)及其混合物。溶剂可以是水,例如在高于或等于60℃的温度下,或实际上在60℃至90℃的温度范围内。无论其化学性质如何,溶剂可以是液体。
在一种实施方式中,纤维结构由氧化物或非氧化物陶瓷纤维、玻璃纤维、金属纤维、聚合物纤维诸如芳族聚酰胺纤维硼纤维或碳纤维、或这些纤维的混合物制成。
在一种实施方式中,在加热注入纤维预制件的孔隙中的浸渍组合物之后获得基质。
在这种情况下,浸渍组合物可包含多个陶瓷颗粒的悬浮液,并且可通过烧结颗粒形成基质。
在一个变型中,浸渍组合物可以包括树脂,并且可以通过固化树脂或通过固化然后热解树脂来形成基质。
在一种实施方式中,通过将熔融金属组合物注入预制件的孔隙中来形成基质。
基质可以部分地或实际上完全由陶瓷材料制成。在一个变型中,基质可包括至少一种碳相和至少一种陶瓷材料相。形成基质的全部或部分的陶瓷材料可以是氧化物材料,诸如氧化铝,或非氧化物材料,诸如碳化硅。当基质包括陶瓷氧化物材料时,纤维结构可以由陶瓷氧化物纤维形成,诸如氧化铝纤维或硅酸铝盐纤维或这些纤维的混合物。当基质包括不是氧化物的陶瓷材料时,纤维结构可以由碳纤维或不是氧化物的陶瓷材料纤维,或这种纤维的混合物制成。
当基质完全由碳制成时,本发明也适用。这种类型的基质可以通过注入碳前体树脂诸如酚醛树脂或呋喃树脂,然后热解树脂来获得。
在另一个变型中,所得基质可以是有机基质。有机基质可以通过注入树脂并固化树脂来形成。当基质是有机的时,纤维结构可以由碳纤维、玻璃纤维、聚合物纤维、硼纤维或金属纤维,或这些纤维的混合物制成。
附图说明
本发明的其他特征和优点从作为非限制性实施例给出的本发明的特定实施方式的以下说明并参考附图显现,其中:
-图1示出了在本发明的示例性方法的背景下通过自动纤维布置形成的纤维预制件的局部图;和
-图2示出了可以在本发明的方法的背景下实现的系列步骤的流程图。
具体实施方式
图1以图解和局部的方式示出了在本发明的示例性方法的背景下通过自动纤维布置制造的纤维预制件。所得纤维预制件用于构成要获得的部件的纤维增强件。
图1示意性地示出了用于执行AFP技术的装置的沉积头1的结构。所示的沉积头1的结构本身是已知的。在沉积头1中加入浸渍有热塑性聚合物的纤维带3,以制造纤维预制件。
纤维带可以使用任何常规技术预先用热塑性聚合物浸渍,例如通过浸渍,通过用辊施加聚合物,或实际上通过喷涂聚合物。在进行AFP技术之前,可以用热塑性聚合物浸渍纤维带,在这种情况下,可以将纤维带储存直到进行该方法。在一个变型中,纤维带在沉积头1上游与沉积头1成一直线地浸渍,然后直接输送到沉积头1,以通过AFP技术形成预制件。
如上所述,浸渍纤维带3的热塑性聚合物可以是水溶性的。这种水溶性使得聚合物能够通过在高于或等于20℃或实际上50℃的温度下与含水介质接触而溶解。然而,热塑性聚合物不需要是水溶性的,在这种情况下,使用有机溶剂以在形成纤维预制件之后进行除去步骤。
如上所述,热塑性聚合物可以具有高于或等于50℃的玻璃化转变温度,例如在50℃至120℃的温度范围内,在60℃至80℃范围内,或实际上在60℃至70℃范围内。玻璃化转变温度可通过差示扫描量热法(DSC)测定。
热塑性聚合物的熔融温度可以在50℃至250℃的范围内,或在150℃至200℃的范围内。熔融温度可通过DSC测量。
纤维预制件形成在支撑件10的表面S上。为此,沉积头1被供给浸渍有热塑性聚合物的纤维带3。浸渍带3由输送元件5带到压紧元件7上,用于施加位于表面S旁边的压力。在这个例子中,输送元件5是一对反向辊5a和5b的形式,在它们之间带3通过。输送元件5用于使浸渍带3前进,直到其沿箭头F1所示的方向到达压紧元件7。
压紧元件7对浸渍带3施加压力,以便将其沉积在表面S上。在该实施例中,压紧元件7呈辊的形式。沉积头1还可包括位于压紧元件7附近的加热器元件9。必要时,加热器元件9用于在浸渍的带3沉积时加热浸渍的带3,以使热塑性聚合物流体化,从而赋予对沉积带的所需粘合能力。举例来说,加热器元件9可以使存在于压紧元件7上的浸渍带3承受高于或等于50℃的温度。在沉积过程中,热塑性聚合物可以处于软化状态,即聚合物可以加热到高于其软化点的温度。在沉积期间,热塑性聚合物因此可处于熔融状态或糊状。
在沉积期间,沉积头1是可移动的,以便将浸渍的带3施加到表面S的确定的第一区域上(箭头F2)。一旦在第一区域上进行施加,沉积头1的切割元件11切割浸渍的带3。在切割之后,由带3的第一段形成的第一浸渍纤维结构因此沉积在第一区域上。最初,在沉积第一纤维结构之前,可以在表面S的第一区域上沉积热塑性材料的初始层,并且随后可以将第一纤维结构沉积在该热塑性材料层上。沉积该初始热塑性层是可选的。
此后,通过推进浸渍带3在沉积头1中前进,直到它通过驱动输送元件5到达压紧元件7以继续形成预制件。沉积头1可以移动,以便将带3沉积在表面S的第二区域上,第二区域与第一区域不同。由带3的第二段形成的第二浸渍纤维结构因此以与上述类似的方式沉积在表面S的第二区域上。
然后通过以与上述相同的方式沉积一种或多种其它浸渍纤维结构来继续制备预制件。
如上所述,可以设想各种材料来构成纤维结构的纤维。特别地,纤维结构可以由陶瓷纤维或碳纤维制成。陶瓷纤维可以是非氧化物材料的纤维,诸如碳化硅SiC,或氧化物材料,诸如氧化铝。在一种实施方式中,所使用的纤维可以是由日本供应商Nippon Carbon以名称“Nicalon”,“Hi-Nicalon”或“Hi-Nicalon-S”供应的SiC纤维,或由供应商UBE以“Tyranno SA3”供应的。还可以使用供应商3M以名称“Nextel”提供的氧化铝纤维。供应商Toray以名称“Torayca T300”供应的纤维也构成适合使用的碳纤维的实例。
沉积的纤维结构可以是纤维粗纱或织物层的形式。特别地,沉积的纤维结构可以不含任何粉末组合物。特别地,浸渍这些结构的热塑性聚合物不需要包括任何固体填料。沉积的纤维结构可以仅用包括热塑性聚合物的有机相浸渍。因此,当通过AFP技术沉积纤维结构时,纤维结构不需要用液态水相浸渍。除了热塑性聚合物之外,沉积的纤维结构可包括增塑剂。
在一种实施方式中,在沉积时,每种纤维结构表现出热塑性聚合物的重量含量大于或等于1%,例如大于或等于3%,甚至5%。该重量含量可以例如在1%至12%的范围内,例如在3%至12%的范围内,例如在3%至8%的范围内,例如在5%至8%的范围内。在沉积时,每种纤维结构可以部分地用热塑性聚合物浸渍。换句话说,在这种情况下,纤维结构的孔隙被热塑性聚合物不完全填充。
热塑性聚合物可选自:聚亚烷基碳酸酯,诸如聚碳酸亚丙酯或聚碳酸亚乙酯;聚酯,例如脂族共聚酯,诸如聚丁二酸丁二醇酯或半芳族共聚酯,例如聚对苯二甲酸乙二醇酯或聚对苯二甲酸丁二醇酯;聚甲基丙烯酸甲酯;聚乙烯醇;聚乙烯吡咯烷酮;聚乙二醇;麦芽糊精;纤维素聚合物;蜡;及其混合物。特别地,热塑性聚合物可选自:聚乙烯醇;聚乙烯吡咯烷酮;聚乙二醇;及其混合物。
取决于要获得的部件所需的性能,还应观察到的是,在用热塑性聚合物浸渍之前,纤维带3的纤维本身可以涂布陶瓷材料涂层或碳材料涂层。
因此,纤维可以被中间层(interphase)覆盖。中间层可包括单层或多层。中间层可以包括至少一层热解碳(PyC)、氮化硼(BN)、硅掺杂氮化硼(BN(Si),硅的质量含量在5%至40%的范围内,并且余量为氮化硼)或硼掺杂碳(BC,硼的原子含量为5%至20%,余量为碳)。举例来说,中间层的厚度可以在10纳米(nm)至1000nm的范围内,例如在10nm至100nm的范围内。在该实施例中,中间层在所得部件中具有脆化-释放功能,用于阻止在传播通过基质后可能到达中间层的任何裂缝,从而防止或延迟由这种裂缝破坏纤维。中间层可选地通过涂布附加的碳化硅层,特别用于改善所得部件对氧化的抵抗力并在形成基质时保护中间层。能够形成中间层和SiC层的技术本身是已知的,并且不需要在此更详细地描述。举例来说,可以使用化学气相沉积或渗透(CVD或CVI)技术来制造这种涂层。
在执行AFP技术之后获得的预制件可以具有单个纤维层,或者在变型中,它可以具有多个纤维层的堆叠。
举例来说,预制件形成可包括沉积具有第一组浸渍纤维结构的第一纤维层。第一组的这些纤维结构可选地为边缘到边缘接触。预制件形成还可包括在第一层上沉积第二纤维层,第二层包括第二组浸渍纤维结构。第二组的这些纤维结构可选地边缘到边缘接触。不沉积边缘到边缘的纤维结构可有利地用于在预制件内提供额外的注入通道,以便于注入步骤,特别是在特定形状的区域中。第一组纤维可以在共同的第一方向(例如,彼此相互平行)上延伸。以类似的方式,第二组的纤维可以在共同的第二方向上延伸。第二方向可以平行于第一方向。在一个变型中,第二方向与第一方向形成非零角度。在第一和第二方向之间形成的角度是要获得的部件所需的机械性能的函数。在预制件包括单个纤维层的特定情况下,它可以由一组浸渍的纤维结构形成,所述纤维结构边缘到边缘接触或者边缘到边缘不接触。
其上沉积浸渍纤维结构的表面S可以是平面。在一个变型中,表面S可以是非平面的、是凸面的或凹面的。举例来说,表面S可呈现可展开的形状,诸如圆锥形、截头圆锥形或圆柱形,或者其可具有不可展开的形状。在通过AFP技术沉积浸渍结构的同时,表面S可以是静止的,或者在变型中它可以是移动的。如果它正在移动,则表面S可以例如在沉积期间被驱动旋转。
图2示出了本发明的示例性方法的各个步骤的流程图。
如上所述,通过在表面上覆盖多个浸渍纤维结构,首先通过AFP技术形成要形成待获得部件的纤维增强物的纤维预制件(步骤100)。
一旦在支撑件上获得预制件,就可以在承载预制件的支撑件上定位壁或背衬形状。以这种方式定位的支撑件和壁限定了其中预制件存在的处理室。一个或多个注入口和至少一个出口孔可以设置在壁中并通向处理室。
此后,通过将溶剂注入注入口并经由出口孔去除溶剂来除去热塑性聚合物(步骤200)。由于与溶剂接触,热塑性聚合物被除去。溶剂可以是液体,或者在变型中,溶剂可以是气体。根据热塑性聚合物的化学性质选择溶剂以便溶解它。举例来说,可以使用温度高于或等于50℃的水来除去聚乙烯醇或聚乙烯吡咯烷酮。在一个变型中,可以使用有机溶剂,诸如乙酸乙烯酯,其可以特别用于除去非水溶性聚合物,诸如聚碳酸亚丙酯。在与溶剂接触结束时,可以从纤维预制件中完全除去热塑性聚合物。
一旦实现了这种除去,可选地干燥纤维预制件,然后将浸渍组合物注入处理室中存在的纤维预制件的孔隙中(步骤300)。然而,这种干燥是可选的,特别是当浸渍组合物是悬浮液形式时,悬浮液可以直接注入而无需预先干燥纤维预制品。当然,选择构成支撑件和壁的材料以便与形成基质时使用的操作条件相容。
浸渍组合物可以在高于或等于1巴的注入压力下注入。出口孔处的压力可选地小于1巴。例如,可以在出口孔处施加30毫巴(mbar)至50mbar的压力,然后可以在没有任何施加压力(即,在注入压力等于1巴)的情况下注入浸渍组合物。在一个变型中,浸渍组合物可以在压力下注入,例如,在3巴至10巴的压力范围内。
图2的流程图涉及通过将浸渍组合物注入预制件中然后通过加热浸渍组合物获得基质的情况(步骤400)。如下所述,注入后进行后续加热是可选的。
在第一个实施例中,浸渍组合物可以是陶瓷颗粒在液体介质中的悬浮液形式。液体介质可以是含水的或有机的。举例来说,陶瓷颗粒可以是碳化硅、碳化硼、莫来石、二氧化硅或氧化铝的颗粒。将悬浮液注入纤维预制件的孔隙中,然后进行加热。该加热包括第一阶段的干燥,在此期间悬浮液的液体介质被蒸发,接着是第二阶段,其中通过烧结陶瓷颗粒形成陶瓷基质。
在第二个实施例中,浸渍组合物可以是树脂的形式。在注入树脂之后,进行加热以使树脂固化并获得有机基质。树脂可选地填充有颗粒。颗粒可以是陶瓷颗粒或碳颗粒,诸如二氧化硅颗粒或碳纳米管。颗粒的平均尺寸(D50)可以小于或等于5微米(μm),优选1μm。
在第三个实施例中,浸渍组合物可以是树脂的形式,其是陶瓷的前体或碳的前体。举例来说,碳前体树脂可以是酚醛树脂或呋喃树脂。举例来说,陶瓷前体树脂可以是聚硅氧烷、聚硅氮烷或聚碳硅烷树脂。在这种情况下,在注入树脂后,将其加热以使树脂固化然后热解,从而获得陶瓷或碳的基质相。由于在该热解阶段期间发生的收缩,可以重复注入和热解过程以填充纤维预制件的任何可进入的孔隙。陶瓷前体树脂或碳前体树脂可选地填充有陶瓷颗粒或碳颗粒。
可以组合用于形成基质的各种不同技术。因此,可以通过热解前体树脂形成碳的第一基质相,然后形成陶瓷的第二基质相,例如通过烧结陶瓷颗粒。
如上所述,注入后的加热步骤(步骤400)在本发明的上下文中是可选的。具体地,在第四个实施例中,浸渍组合物可以是熔融金属组合物的形式,例如熔融硅或熔融硅合金。在这种情况下,可以在注入熔融金属之前将陶瓷颗粒或碳颗粒的粉末引入纤维预制件的孔隙中。此后,将熔融金属注入纤维预制件的孔隙中以获得基质。在该实施例中,基质可以在注入熔融金属组合物之后直接获得,并且可能在冷却其(没有任何后续加热步骤)之后获得。
通过执行本发明的方法获得的部件可以是用于机舱或排气锥的部件。举例来说,该部件可以具有在两个蒙皮部分之间存在芯部的结构。
术语“在…至…范围”应理解为包括边界。
Claims (13)
1.一种制造复合部件的方法,该方法包括以下步骤:
-通过将浸渍有热塑性聚合物的多个纤维结构沉积到表面上来形成用于待获得部件的纤维预制件,通过自动纤维布置进行沉积;
-通过溶剂溶解除去预制件中存在的热塑性聚合物;和
-在除去热塑性聚合物之后,将液体浸渍组合物注入纤维预制件的孔隙中,以在纤维预制件的孔隙中形成基质。
2.根据权利要求1所述的方法,其中热塑性聚合物的玻璃化转变温度高于或等于50℃。
3.根据权利要求1或2所述的方法,其中热塑性聚合物的熔融温度高于或等于50℃。
4.根据权利要求1至3中任一项所述的方法,其中热塑性聚合物选自:聚亚烷基碳酸酯;聚酯;聚甲基丙烯酸甲酯;聚乙烯醇;聚乙烯吡咯烷酮;聚乙二醇;麦芽糊精;纤维素聚合物;蜡;及其混合物。
5.根据权利要求1至4中任一项所述的方法,其中热塑性聚合物是水溶性的。
6.根据权利要求1至5中任一项所述的方法,其中溶剂是含水的。
7.根据权利要求6所述的方法,其中溶剂是水。
8.根据权利要求1至7中任一项所述的方法,其中溶剂的温度高于或等于60℃。
9.根据权利要求1至8中任一项所述的方法,其中在加热注入纤维预制件孔隙中的浸渍组合物之后获得基质。
10.根据权利要求9所述的方法,其中浸渍组合物包括多个陶瓷颗粒的悬浮液,并且其中通过烧结颗粒形成基质。
11.根据权利要求9所述的方法,其中浸渍组合物包括树脂,并且其中通过固化树脂或通过固化然后热解树脂来形成基质。
12.根据权利要求1至8中任一项所述的方法,其中通过将熔融金属组合物注入预制件的孔隙中来形成基质。
13.根据权利要求1至12中任一项所述的方法,其中纤维结构由氧化物或非氧化物陶瓷纤维、玻璃纤维、金属纤维、聚合物纤维、硼纤维或碳纤维、或者这些纤维的混合物形成。
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CN114000069A (zh) * | 2021-10-09 | 2022-02-01 | 中国航发北京航空材料研究院 | 一种连续SiC纤维增强金属基复合材料点阵结构的制备方法 |
CN114195525A (zh) * | 2022-01-11 | 2022-03-18 | 成都成维精密机械制造有限公司 | 一种低氧含量陶瓷基复合材料的制备方法 |
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FR3131706A1 (fr) * | 2022-01-12 | 2023-07-14 | Safran | Tête d’application pour le placement automatique de fibres |
FR3133334B1 (fr) | 2022-03-09 | 2024-03-15 | Safran | Rouleau pour le dépôt par placement automatique de fibres |
BE1030742B1 (fr) | 2022-08-01 | 2024-02-26 | Safran Aero Boosters | Géométrie d'une surface de drapage |
BE1030752B1 (fr) | 2022-08-04 | 2024-03-04 | Safran Aero Boosters | Outillage de déformation d'une ébauche fibreuse |
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- 2018-02-01 US US16/481,199 patent/US10994446B2/en active Active
- 2018-02-01 BR BR112019015821-9A patent/BR112019015821B1/pt active IP Right Grant
- 2018-02-01 CN CN201880010136.7A patent/CN110248912A/zh active Pending
- 2018-02-01 RU RU2019127052A patent/RU2771306C2/ru active
- 2018-02-01 JP JP2019542108A patent/JP6963017B2/ja active Active
- 2018-02-01 EP EP18713301.2A patent/EP3577092B1/fr active Active
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CN115515914A (zh) * | 2020-02-05 | 2022-12-23 | 莱昂内尔·范登布尔克 | 一种包含特定界面相的陶瓷基体复合材料的制造方法 |
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CN114000069A (zh) * | 2021-10-09 | 2022-02-01 | 中国航发北京航空材料研究院 | 一种连续SiC纤维增强金属基复合材料点阵结构的制备方法 |
CN114000069B (zh) * | 2021-10-09 | 2022-09-20 | 中国航发北京航空材料研究院 | 一种连续SiC纤维增强金属基复合材料点阵结构的制备方法 |
CN114195525A (zh) * | 2022-01-11 | 2022-03-18 | 成都成维精密机械制造有限公司 | 一种低氧含量陶瓷基复合材料的制备方法 |
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RU2019127052A (ru) | 2021-03-02 |
WO2018142080A1 (fr) | 2018-08-09 |
JP6963017B2 (ja) | 2021-11-05 |
EP3577092A1 (fr) | 2019-12-11 |
FR3062336A1 (fr) | 2018-08-03 |
US10994446B2 (en) | 2021-05-04 |
RU2019127052A3 (zh) | 2021-04-28 |
FR3062336B1 (fr) | 2019-04-12 |
CA3051884A1 (fr) | 2018-08-09 |
RU2771306C2 (ru) | 2022-04-29 |
JP2020506091A (ja) | 2020-02-27 |
EP3577092B1 (fr) | 2021-03-31 |
BR112019015821A2 (pt) | 2020-03-31 |
BR112019015821B1 (pt) | 2023-10-31 |
US20200001504A1 (en) | 2020-01-02 |
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