CN113623016A - 具有燕尾根部的编织动叶和静叶 - Google Patents
具有燕尾根部的编织动叶和静叶 Download PDFInfo
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Abstract
本发明涉及具有燕尾根部的编织动叶和静叶。一种燃气涡轮发动机复合物品,其具有复合物品翼型件,该复合物品翼型件向外延伸到物品根部直到物品翼型件末梢。在该物品翼型件内的是芯,该芯包括芯翼型件,该芯翼型件附接于包括芯燕尾件的芯根部。包括编织复合材料丝束的连续外三维编织层编织在该芯上且该编织层覆盖整个芯翼型件和芯根部。该芯可以是可膨胀芯棒或由复合材料制成的复合芯。该芯可以包括加强件,诸如工字梁或中空矩形截面箱形梁。用于制造此种物品的方法包括在芯上编织包含编织复合材料丝束的连续外三维编织层,包括用该连续外三维编织层覆盖整个芯翼型件和芯根部。
Description
技术领域
本发明涉及燃气涡轮发动机复合动叶和静叶,且具体而言,涉及用于制造具有翼型件和燕尾根部的此种动叶和静叶及由此的物品的方法。
背景技术
涡轮风扇型的旁通燃气涡轮发动机通常包括前部风扇和增压压缩机、中间核心发动机和尾部低压动力涡轮。低压涡轮通过低压轴可旋转地驱动风扇和增压压缩机,这些都形成低压转子。已经为此种风扇和增压器或低压压缩机中的动叶和固定静叶研发了复合翼型件且已用在其中。此种动叶和静叶通常具有连接到燕尾根部的翼型件以分别安装到燃气涡轮发动机的转子或定子部分。
三维(3D)编织是一种用于通过纤维的连续编结形成纤维预制件的已知工艺。在3D编织工艺期间,处于矩阵阵列形式的多个纤维搬运器同时移动跨过搬运器表面。在它们同时移动时,纤维从各搬运器部件伸出且与来自其他搬运器部件的纤维编结。通过合适的方法在搬运器表面上方聚集这些纤维。3D编织工艺的特征在于,当预制件浸渍有树脂(例如环氧树脂)、金属或其他已知基质材料时,在预制件中没有分层平面,且得到坚韧的、抗裂缝生长的复合物品。1969年2月11日出版的Bluck的美国专利号No. 3,426,804和1982年1月26日出版的Florentine的美国专利号No. 4,312,761例示了用于以矩形、行列矩阵或圆形、同轴环矩阵形式使用纤维搬运器编织3D物品预制件的机器。
已知由复合材料制造飞行器燃气涡轮发动机动叶和静叶,它们具有连接到燕尾根部的翼型件。复合动叶和静叶提供了重量的减轻,这是极其合乎需要的。期望通过用于制造3D编织预制件的工艺来具有坚固的动叶或静叶,它们具有翼型件和一体的燕尾根部。
极其期望具有一种带有至少一个一体的复合翼型件的复合动叶或静叶和包括编织材料外层的静叶。极其期望具有一种带有编织材料外层的复合动叶或静叶预制件。极其期望具有一种方法,其用于制造在翼型件和燕尾件上具有编织材料连续外层的复合动叶或静叶预制件,其中,该编织工艺是自动的,并且,该燕尾件通过用于高应力应用的附加特征。
发明内容
一种燃气涡轮发动机复合物品包括复合物品翼型件,所述复合物品翼型件附接于物品根部且具有沿翼展方向向外从物品翼型件基部或物品根部延伸到物品翼型件末梢的物品动叶压力侧和吸力侧。复合物品翼型件在弦向间隔开的物品前缘与后缘之间眼神,且物品根部包括一体的物品燕尾件。芯包括芯翼型件,该芯翼型件附接于包括芯燕尾件的芯根部,且该芯翼型件包括沿翼展方向向外从芯翼型件基部或芯根部延伸到芯末梢的芯压力侧和吸力侧,且位于复合物品翼型件内。包含编织复合材料丝束的连续外三维(3D)编织层编织在芯上且覆盖整个芯翼型件和芯根部。
该芯可包括可膨胀芯棒。该芯可以是由复合材料制成的复合芯。衬垫或插入层片可配置在编织层的内侧。该芯可包括加强件,加强件具有工字梁或中空矩形截面箱形梁。梁与动叶复合芯的壳之间的中空空间可以填充有轻质填料或泡沫。
该复合物品翼型件可沿翼展方向向外从物品内根部延伸到物品翼型件末梢处的物品外根部,该芯可以包括与芯翼型件一体地形成的芯内和外根部,且该连续外三维(3D)编织层可覆盖整个芯翼型件和芯内和外根部。
一种用于制造燃气涡轮发动机复合物品的方法包括在芯上编织包含编织复合材料丝束的连续外三维(3D)编织层,该芯包括附接于芯根部的芯翼型件,且该芯根部包括芯燕尾件。该芯翼型件包括沿翼展方向向外从芯翼型件基部或芯根部延伸到芯末梢的芯压力和吸力侧,且位于复合物品翼型件内。该编织包括用连续外三维(3D)编织层覆盖整个芯翼型件和芯根部。
该编织可包括过编织(over-braiding),以用于制造连续外编织层的顶部和底部过编织部分。该方法还可包括修剪掉顶部和底部过编织部分,然后在编织层中注入树脂,且然后使该复合物品固化。该芯可在固化之前或之后移除,或者保留在零件内。
技术方案1:一种燃气涡轮发动机复合物品,其包括:
复合物品翼型件,其附接于物品根部,
复合物品翼型件包括沿翼展方向向外从物品翼型件基部或物品根部延伸到物品翼型件末梢的物品动叶压力和吸力侧,
复合物品翼型件在弦向间隔开的物品前缘与后缘之间延伸,
物品根部包括一体的物品燕尾件,
芯,其包括芯翼型件,该芯翼型件附接于包括芯燕尾件的芯根部,
该芯翼型件包括沿翼展方向向外从芯翼型件基部或芯根部延伸到芯末梢的芯压力和吸力侧,且位于该复合物品翼型件内,
连续外三维编织层,其包括编织在芯上的编织复合材料丝束,且
该连续外三维编织层覆盖整个芯翼型件和芯根部。
技术方案2:根据技术方案1所述的物品,其特征在于,还包括该芯包括可膨胀芯棒。
技术方案3:根据技术方案1所述的物品,其特征在于,还包括该芯是由复合材料制成的复合芯。
技术方案4:根据技术方案3所述的物品,其特征在于,还包括衬垫或者插入层片配置在该编织层的内侧。
技术方案5:根据技术方案3所述的物品,其特征在于,还包括该芯包括加强件。
技术方案6:根据技术方案5所述的物品,其特征在于,还包括加强件,所述加强件包括工字梁或中空矩形截面箱形梁。
技术方案7:根据技术方案6所述的物品,其特征在于,还包括梁与动叶复合芯的壳之间的填充有填料或泡沫的中空空间。
技术方案8:根据技术方案6所述的物品,其特征在于,还包括:
该复合物品翼型件,其附接于物品内和外根部,其中,物品内根部是物品根部,
该复合物品翼型件沿翼展方向向外从物品内根部延伸到物品翼型件末梢处的物品外根部,
该芯包括与该芯翼型件一体地形成的芯内和外根部,其中,芯内根部是芯根部,且
该连续外三维编织层覆盖整个芯翼型件和内和外根部。
技术方案9:根据技术方案8所述的物品,其特征在于,还包括:
该芯是由复合材料制成的复合芯,
该芯包括加强件,且
该加强件包括工字梁或中空矩形截面箱形梁。
技术方案10:根据技术方案9所述的物品,其特征在于,还包括梁与动叶复合芯的壳之间的填充有填料或泡沫的中空空间。
技术方案11:一种用于制造燃气涡轮发动机复合物品的方法,该方法包括:
在芯上编织包括编织复合材料丝束的连续外三维编织层,
该芯包括附接于芯根部的芯翼型件,且该芯根部包括芯燕尾件,
该芯翼型件包括沿翼展方向向外从芯翼型件基部或芯根部延伸到芯末梢的芯压力和吸力侧,且位于复合物品翼型件内,且
该编织包括用该连续外三维编织层覆盖整个芯翼型件和芯根部。
技术方案12:根据技术方案11所述的方法,其特征在于,还包括该编织包括过编织,以用于制造连续外编织层的顶部和底部过编织部分。
技术方案13:根据技术方案11所述的方法,其特征在于,还包括修剪掉该顶部和底部过编织部分,然后在编织层中注入树脂,且然后使该复合物品固化。
技术方案14:根据技术方案13所述的方法,其特征在于,还包括在固化之前或之后移除芯。
附图说明
下面描述中解释本发明的前述方面和其他特征,参考附图,其中:
图1是复合动叶的立体图例示,该复合动叶具有带连续外编织层的一体翼型件和燕尾根部。
图2是用于编织用于图1所示的一体翼型件和燕尾根部的连续外编织层的复合芯或芯棒的剖视图例示。
图3是用于制造图1所示的复合动叶的预制件的剖视图例示。
图4是沿图3的4-4截取的预制件的翼型件区段的剖视图例示。
图5是沿图3的5-5截取的预制件的根部区段的剖视图例示。
图6是编织芯棒以形成图3所示的预制件的编织机和方法的概略立体图例示。
图6A是图6所示的纤维丝束的三轴向织物的放大概略立体图例示。
图7是预制件的剖视图例示,该预制件具有用于制造图1所示的复合动叶的第一备选芯。
图8是预制件的剖视图例示,该预制件具有用于制造图1所示的复合动叶的第二备选芯。
图9是复合动叶或静叶的立体图例示,其带有内和外燕尾根部。
图10是用于制造图9所示复合静叶或动叶的芯的剖视图例示。
具体实施方式
图1中示出的是一种燃气涡轮发动机可旋转动叶10,其具有与动叶根部20一体地形成的复合动叶翼型件12。动叶根部20可包括复合动叶翼型件12与动叶根部20之间的动叶柄部21。动叶10具有连续的外三维(3D)编织层14,该编织层14至少部分地通过在芯24上编织复合材料丝束126而制成,该芯24可为可膨胀的芯棒18或动叶复合芯30,如图6所示。在图6中例示编织。注意,在本文中描述了动叶和用于制造该动叶的方法,然而物品和用于制造该物品的方法也适用于具有与根部一体地形成的复合翼型件的静叶。
参照图1,动叶翼型件12包括动叶压力和吸力侧41、43,它们沿翼展方向S向外从动叶翼型件基部19或动叶根部20沿翼展S延伸到动叶翼型件末梢47。本文中例示出的示范动叶压力和吸力侧41、43分别是凹形和凸形的。动叶翼型件12沿弦C在弦向间隔开的动叶前缘和后缘LE、TE之间延伸。动叶翼型件12的厚度T在弦向和翼展方向C、S二者上变化,且在动叶压力和吸力侧41、43之间延伸。动叶根部20包括一体的动叶燕尾件28,其用于将动叶10安装到燃气涡轮发动机转子盘或鼓。
动叶燕尾件28包括燕尾件压力和吸力侧141、143,它们对应于动叶压力和吸力侧41、43。动叶燕尾件28还包括燕尾件前缘和后缘DLE、DTE,它们分别对应于动叶前缘和后缘LE、TE。
图2-4中示出的是芯24(其可为动叶复合芯30),该芯24在用在制造动叶的方法期间操作为芯棒18且代表芯棒18。在动叶复合芯30的情况下,当过程或方法完成时,其可以保留在动叶10内侧。在此种实施例中,在图6示出的编织过程期间,动叶复合芯30用作芯棒18。芯24包括芯翼型件22,芯翼型件22具有芯压力和吸力侧31、33,芯压力和吸力侧31、33沿翼展方向向外从芯翼型件基部39或芯根部40沿芯翼展S延伸到芯末梢36。芯根部40包括芯燕尾形件38。本文中例示的示范芯压力和吸力侧31、33分别是凹形和凸形的。芯翼型件22沿弦C在弦向间隔开的芯前缘和后缘MLE、MTE之间延伸。芯翼型件22的厚度T在弦向和翼展方向C、S二者上变化,且在芯压力和吸力侧31、33之间延伸。
参照图2-5,芯燕尾件38包括芯燕尾件压力和吸力侧131、133,它们分别对应于芯压力和吸力侧31、33。芯燕尾件38还包括芯燕尾件前缘和后缘CDLE、CDTE,它们分别对应于芯前缘和后缘MLE、MTE。芯燕尾件38包括芯燕尾件底部42。
图3-5中例示出的是通过图6例示的编织过程形成的预制件80。芯24(其可以是芯棒18或动叶复合芯30)以虚线示为配置在预制件80内以用于对比。预制件80包括预制件翼型件82,其具有预制件压力和吸力侧81、83,预制件压力和吸力侧81、83沿翼展方向向外从预制件翼型件基部89或预制件根部90沿预制件翼展S延伸到预制件末梢86。预制件根部90包括预制件燕尾件98。本文中例示出的示范预制件压力和吸力侧81、83分别是凹形和凸形的。预制件翼型件82沿弦C在弦向间隔开的预制件前缘和后缘PLE、PTE之间延伸。预制件翼型件82的厚度T在弦向和翼展方向C、S二者上变化,且在预制件压力和吸力侧81、83之间延伸。编织工艺包括过编织,以用于制造连续外编织层14的顶部和底部过编织部分100、102,它们可在利用树脂注入之前从预制件80的其余部分修剪掉。两个示范注入过程可以是树脂传递模制RTM或真空辅助树脂传递模制VARTM或其他树脂注入过程。在注入之后,诸如通过压煮、热压或另一固化工艺使预制件80固化。
图4-5中示出的是预制件80,其中实心动叶复合芯30配置在预制件80内且由连续的外编织层14包围。图4是沿动叶翼型件12和复合芯翼型件22的弦向延伸平面截取的,其在图4-5中示为实心的。图5示出预制件根部90为实心的且实心动叶复合芯30的一部分配置在预制件80内且由连续的外编织层14包围。图5还示出底部过编织部分102和预制件根部90和预制件燕尾件98。实心动叶复合芯30可由单向带(unitape)或fabrix制成。
单向带是单向的带材料和环氧树脂基质。该材料和其他合适的材料的论述可以在ASM INTERNATIONAL,1987 1989或更新版本的“Engineering Materials Handbook”中找到。本文中论述的复合材料是由非金属类型制成的,由包含埋在树脂材料(例如Epoxy、PMR15、BMI、PEEU、Silicon等)中的纤维(例如含碳、石英、金属、金属氧化物或陶瓷纤维)的材料制成。这些纤维在带中单向地对齐,该带浸渍有树脂且形成为零件形状。随后,其通过热煮过程或冲压模制而固化,以形成轻质、刚性、相对均质的物品,其内具有叠层或层片。这些层片通常都由单向纤维细丝层片材料制成,优选为带,因为它通常被认为按照翼展次序布置且用于形成芯翼型件22。5,375,978中公开的层片铺叠被认为是标准准各向同性的铺叠顺序,其为0度、+45度、0度、45度纤维定向,其中层片具有多种层片形状。
图7-8中分别例示出用于动叶复合芯30的第一和第二备选构造。图7-8例示的动叶复合芯30是中空的且具有加强件110。图7例示的加强件是工字梁112,且图8所示的加强件包括中空方形或矩形截面箱形梁114。梁与动叶复合芯30的壳120之间的中空空间118可填充填料,诸如通常用在复合物品(诸如动叶和静叶)中的泡沫。
动叶复合芯30可包括但不限于清洗材料或飞离复合材料、或预固化复合材料。清洗材料从动叶或预制件化学地移除。飞离材料当动叶制造完成且安装在发动机中时保留在动叶中,在发动机处,其在发动机操作期间保留。如果芯24是可膨胀的芯棒,那么该可膨胀的芯棒可在固化之前或之后被移除。动叶可包括附加的非编织特征,诸如,衬垫或插入层片或加强元件,它们配置在编织层的内侧。插入层片可用来增大芯与编织层之间的根部面积。
图6和6A例示出编织设备104和用于制造非均匀厚度复合动叶预制件(例如图3-5所示的预制件80)的方法。编织设备在Wybrow的美国专利号No. 8,061,253中公开,其于2011年11月22日出版,题为“Composite Spars”,且其通过引用而整体并入本文中。设备104包括编织机121、可变位置梭142和非圆柱形芯棒140,诸如上述可膨胀芯棒或芯。示范编织机是能够从Herzog Maschinenfabrik GmbH & Co. KG,Am Alexanderhaus 160, D-26127,Oldenburg, Germany [9]获得的Herzog.TM. RF1/192-100编织机。
编织机121包括可旋转鼓122,在该可旋转鼓122上安装有多个线轴124。为了清楚起见,仅示出8个此种线轴124。然而在实践中,可提供许多更多的此种线轴。在操作中,可旋转鼓122被控制器/驱动器装置130驱动以绕圆柱形轴线144旋转,控制器/驱动器装置130可包括在计算机化控制系统(未示出)的控制下操作的电动马达。线轴124在搬运器上以S形样式围绕芯24的周围从一个搬运器到下一个独立地移动。线轴124装载有各种含纤维的丝束126,这些丝束被编织以制成非均匀厚度复合构件152,诸如图3-5中例示的复合预制件80。
纤维丝束126被贯穿通过编织引导件128且临时地附于非圆柱形芯棒140或芯24。非圆柱形芯棒140或芯24联接到可变位置梭142,使得当可变位置梭142被操作时,非圆柱形芯棒140或芯的相对位置相对于编织机121沿轴线144的方向侧向地移动。梭142附接于芯燕尾件底部42。非圆柱形芯棒140或芯由适当地轻且刚性的材料制成,使得它能够可在各端部受到支撑而不弯曲。
在操作期间,在可旋转鼓122旋转时,非圆柱形芯棒140或芯24沿圆柱形轴线144侧向地移动,且纤维丝束126在非圆柱形芯棒140或芯24的表面上方编织在一起,以形成编织层片150而形成编织层14。该过程可通过过编织动叶编织层片层的一个或更多个附加层而重复,例如,同时沿相反方向移动非圆柱形芯棒140或芯24。通过移动非圆柱形芯棒,例如以恒定速度沿圆柱形轴线144,同时也以恒定速度堆积纤维丝束126,由于非圆柱形芯棒的径向尺寸的变化,动叶编织层片150在圆柱形轴线144的方向上沿其长度被赋予变化的厚度。这允许制造非均匀厚度动叶编织层片150。
编织层片可包括三轴向织物156,如图6A所示,其中,纤维丝束126相对于圆柱形轴线144以编织角度+P、0和-P度(诸如+45度,0度和-45度)布置,以提供最优的抗扭强度。
连续的外三维(3D)编织层14通过在芯24上编织复合材料丝束126而敷设,芯24包括整个芯翼型件22及其芯压力和吸力侧31、33,下至芯根部40且涵盖芯燕尾件压力和吸力侧131、133和芯燕尾件前缘和后缘CDLE、CDTE。该编织包括在顶部和底部上过编织,以形成顶部和底部过编织部分100和102。
图9示出复合飞行器燃气涡轮发动机静叶或可旋转动叶210,其具有与动叶内和外根部220、222一体地形成的复合动叶翼型件212。静叶或动叶210具有连续的外三维(3D)编织层214,该连续的外三维(3D)编织层214部分地通过在复合芯上编织复合材料丝束来形成,如图6所示。动叶翼型件212包括动叶压力和吸力侧241、243,它们沿翼展方向向外从动叶翼型件基部219或动叶内根部220沿翼展S延伸到动叶翼型件末梢247或动叶翼型件末梢247处的动叶外根部222。本文中例示出的示范动叶压力和吸力侧241、243分别是凹形和凸形的。翼型件212沿弦C在弦向间隔开的静叶或动叶前缘和后缘LE、TE之间延伸。翼型件212的厚度T在弦向和翼展方向C、S二者上变化,且在压力和吸力侧241、243之间延伸。内和外根部220、222中的各个包括一体的动叶燕尾件28,其使静叶或动叶能够安装到燃气涡轮发动机转子盘或鼓,或者在静叶的情况下安装到发动机的静止结构。
参照图10,复合飞行器燃气涡轮发动机静叶或可旋转动叶210包括芯24和芯翼型件22,如上所述,但是具有与芯翼型件22一体地形成或附接于其的芯内和外根部230、232。芯内和外根部230、232中的各个包括芯燕尾件38。芯外根部232的芯燕尾件38位于动叶翼型件末梢247处。芯内根部220的芯燕尾件38位于基部芯翼型件22的芯翼型件基部39处且包括芯燕尾件底部42,梭可连接到该芯燕尾件底部42。
已经以例示的方式描述了本发明。应理解的是,已使用的术语意图具有说明而非限制的词语的意思。虽然在本文中已描述了视为本发明的优选和示范实施例的那些实施例,但对于本领域技术人员来说,根据本文的教导,本发明的其他改型应是显而易见的,因此,期望在所附权利要求中保护落入本发明的真实精神和范围内的所有此种改型。
因此,期望通过美国专利证书来保护的是在下列权利要求中限定和推断的发明。
Claims (10)
1.一种燃气涡轮发动机复合物品,其包括:
复合物品翼型件,其附接于物品内根部和物品外根部,
复合物品翼型件包括沿翼展方向向外从物品翼型件基部或物品内根部延伸到物品翼型件末梢处的物品外根部的物品动叶压力和吸力侧,
复合物品翼型件在弦向间隔开的物品前缘与后缘之间延伸,
所述物品内根部或所述物品外根部中的至少一者包括一体的物品燕尾件,
芯,其包括一体地形成至芯内根部和芯外根部的芯翼型件,所述芯内根部或所述芯外根部中的至少一者包括芯燕尾件,
该芯翼型件包括沿翼展方向向外从所述芯内根部延伸到芯末梢处的所述芯外根部的芯压力和吸力侧,且位于该复合物品翼型件内,
连续外三维编织层,其包括编织在芯上的编织复合材料丝束,且
该连续外三维编织层覆盖整个芯翼型件、所述芯内根部和所述芯外根部。
2.根据权利要求1所述的物品,其特征在于,所述芯包括可移除的可膨胀芯棒。
3.根据权利要求1所述的物品,其特征在于,所述芯是由复合材料制成的复合芯,或者所述芯包括清洗材料并且该清洗材料可从所述复合物品中化学地移除。
4.根据权利要求3所述的物品,其特征在于,还包括衬垫或者插入层片配置在该编织层的内侧。
5.根据权利要求3所述的物品,其特征在于,还包括该芯包括加强件。
6.根据权利要求5所述的物品,其特征在于,所述加强件包括工字梁或中空矩形截面箱形梁。
7.根据权利要求1所述的物品,其特征在于,所述芯包括加强件,所述物品还包括加强件与动叶复合芯的壳之间的填充有填料或泡沫的中空空间。
8.根据权利要求1所述的物品,其特征在于,还包括:
该芯是由复合材料制成的复合芯,
该芯包括加强件,且
该加强件包括工字梁或中空矩形截面箱形梁。
9.根据权利要求8所述的物品,其特征在于,还包括梁与动叶复合芯的壳之间的填充有填料或泡沫的中空空间。
10.一种用于制造燃气涡轮发动机复合物品的方法,该方法包括:
在芯上编织包括编织复合材料丝束的连续外三维编织层,
该芯包括一体地形成至芯内根部和芯外根部的芯翼型件,所述芯内根部或所述芯外根部中的至少一者包括芯燕尾件,
该芯翼型件包括沿翼展方向向外从所述芯内根部延伸到芯末梢处的所述芯外根部的芯压力和吸力侧,且位于复合物品翼型件内,且
该编织包括用该连续外三维编织层覆盖整个芯翼型件、所述芯内根部和所述芯外根部。
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US201462053835P | 2014-09-23 | 2014-09-23 | |
US62/053835 | 2014-09-23 | ||
US14/860132 | 2015-09-21 | ||
US14/860,132 US10589475B2 (en) | 2014-09-23 | 2015-09-21 | Braided blades and vanes having dovetail roots |
CN202110870469.0A CN113623016B (zh) | 2014-09-23 | 2015-09-23 | 具有燕尾根部的编织动叶和静叶 |
CN201510859750.9A CN105937412A (zh) | 2014-09-23 | 2015-09-23 | 具有燕尾根部的编织动叶和静叶 |
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DE102014112311A1 (de) * | 2014-08-27 | 2016-03-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Verfahren und Formwerkzeug zur Infusion eines Matrixmaterials |
EP3708347B1 (en) * | 2016-04-06 | 2022-01-05 | Rolls-Royce plc | A method of manufacturing a composite component |
DE102017221665A1 (de) * | 2017-12-01 | 2019-06-06 | MTU Aero Engines AG | Verfahren zur herstellung von faserverstärkten bauteilen von strömungsmaschinen und entsprechend hergestelltes bauteil |
EP3556544B1 (en) | 2018-04-17 | 2021-07-28 | Ratier-Figeac SAS | Propeller blade spar |
FR3085417B1 (fr) * | 2018-08-29 | 2020-12-04 | Safran Aircraft Engines | Aube comprenant une structure en materiau composite et procede de fabrication associe |
US11213995B2 (en) * | 2018-11-02 | 2022-01-04 | The Boeing Company | Composite structures constructed of wound tubular braiding |
US11534986B2 (en) | 2018-11-02 | 2022-12-27 | The Boeing Company | Composite structures constructed of wound tubular braiding |
US11345099B2 (en) | 2018-11-02 | 2022-05-31 | The Boeing Company | Composite structures constructed of wound tubular braiding |
EP3848488A1 (en) * | 2020-01-08 | 2021-07-14 | Ratier-Figeac SAS | Braiding |
US11834964B2 (en) | 2021-11-24 | 2023-12-05 | General Electric Company | Low radius ratio fan blade for a gas turbine engine |
US11920493B2 (en) | 2022-02-25 | 2024-03-05 | General Electric Company | Airfoil having a structural cell and method of forming |
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Also Published As
Publication number | Publication date |
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EP3002111A1 (en) | 2016-04-06 |
CN105937412A (zh) | 2016-09-14 |
US10589475B2 (en) | 2020-03-17 |
US20160201478A1 (en) | 2016-07-14 |
BR102015024374A2 (pt) | 2016-10-04 |
CN113623016B (zh) | 2023-09-12 |
EP3002111A8 (en) | 2016-05-18 |
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