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1. 发明申请

US20070081887A1 COMPOSITE FAN CONTAINMENT CASE FOR TURBINE ENGINES 有权
标题翻译：用于涡轮发动机的复合风机容纳箱
公开(公告)号：US20070081887A1
公开(公告)日：2007-04-12
申请号：US11020483
申请日：2004-12-23
申请人： Ming Xie , Stephen Mitchell , Donald LaChapelle , Lee Blanton , Richard Price , David Crall , Frank Worthoff
发明人： Ming Xie , Stephen Mitchell , Donald LaChapelle , Lee Blanton , Richard Price , David Crall , Frank Worthoff
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , D04C1/02 , D10B2505/02 , F01D25/24 , F05D2300/44 , F05D2300/603 , F05D2300/702 , Y02T50/672
摘要： A composite fan casing for a gas turbine engine is provided includes, in an exemplary embodiment, a core having a plurality of core layers of reinforcing fiber bonded together with a thermosetting polymeric resin. Each core layer includes a plurality of braided reinforcing fibers with the braids of reinforcing fibers aligned in a circumferential direction.
摘要翻译：提供一种用于燃气涡轮发动机的复合风扇壳体，在示例性实施例中包括具有多个与热固性聚合物树脂结合在一起的增强纤维芯层的芯。每个芯层包括多个编织增强纤维，其中增强纤维的编织物沿圆周方向排列。

2. 发明申请

US20060130993A1 Method for fabricating reinforced composite materials 失效
标题翻译：制造增强复合材料的方法
公开(公告)号：US20060130993A1
公开(公告)日：2006-06-22
申请号：US11021804
申请日：2004-12-22
申请人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Matthew Buczek , Robert Fairbanks , Richard Price , Warren Ronk
发明人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Matthew Buczek , Robert Fairbanks , Richard Price , Warren Ronk
IPC分类号： B22D19/14
CPC分类号： B29C70/546 , B29C70/44 , B29C70/465 , B29L2031/7504 , F01D21/045 , F05D2300/614 , F05D2300/702 , Y02T50/672 , Y10T428/249928 , Y10T428/249933 , Y10T428/24994 , Y10T428/249944
摘要： A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.
摘要翻译：一种用于制造增强基质复合材料的方法，包括提供具有纤维结构的复合预成型件并将基体材料施加到预型件上的预型件沿着预制件的位置的步骤。将阻挡材料施加到涂覆预型件的至少一部分以将基体材料流引导到预成型件中。将复合预制件加热到足以使基质材料粘稠并且不足以固化基质材料的温度。对复合预制件内部的压力降低，同时对阻挡材料的压力增加。保持温度以使基质材料流入复合预制件并迫使来自纤维结构的气体。然后将复合预成型件固化并冷却以形成具有低空隙含量和基本均匀的基体分布的增强基质复合材料。

3. 发明申请

US20060134396A1 Reinforced matrix composite containment duct 有权
标题翻译：钢筋基复合材料防渗管
公开(公告)号：US20060134396A1
公开(公告)日：2006-06-22
申请号：US11021805
申请日：2004-12-22
申请人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Robert Fairbanks , Richard Price , Warren Ronk
发明人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Robert Fairbanks , Richard Price , Warren Ronk
IPC分类号： D04H13/00 , D04H5/00
CPC分类号： F01D21/045 , B29C70/465 , B29L2031/7504 , F05D2300/614 , F05D2300/702 , Y02T50/672 , Y10T428/249924
摘要： A reinforced matrix composite containment duct for gas turbine engines comprising a reinforced matrix composite containment duct having high strength integral flanges and pre-stressed reinforcing fibers, the reinforced matrix composite having uniform distribution of matrix material; and the reinforced matrix composite having less than or equal to 2.5% void space.
摘要翻译：一种用于燃气涡轮发动机的增强基体复合容纳管，其包括具有高强度整体凸缘和预应力增强纤维的增强基体复合容纳管，所述增强基体复合材料具有均匀的基体材料分布; 和具有小于或等于2.5％空隙空间的增强基质复合材料。

4. 发明申请

US20060134251A1 Apparatus for fabricating reinforced composite materials 有权
标题翻译：用于制造增强复合材料的装置
公开(公告)号：US20060134251A1
公开(公告)日：2006-06-22
申请号：US11021893
申请日：2004-12-22
申请人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Matthew Buczek , Robert Fairbanks , Richard Price
发明人： Lee Blanton , Gregory Meibers , Stephen Whiteker , Matthew Buczek , Robert Fairbanks , Richard Price
IPC分类号： B29C70/48
CPC分类号： B29C70/446 , B29C33/48 , B29C70/548 , B29L2031/7504
摘要： A mold tool for forming a reinforced matrix composite part for a gas turbine engine, comprising a body. The body comprises a body surface capable of receiving a first portion of a composite preform. A first endplate and second endplate are attached to the body and include a substantially planar surface disposed perpendicular to the body surface. A first and second set of plates are attached to the first and second endplate adjacent to the body surface and have a geometries that includes a first and second cavity bounded by the first and second plate and first and second endplate. The first and second cavities have a volume sufficient to receive a second portion of a composite preform. The second cavity is in fluid communication with the first cavity, which is in fluid communication with a vacuum source.
摘要翻译：一种用于形成用于燃气涡轮发动机的增强基体复合部件的模具，包括主体。主体包括能够接收复合预型件的第一部分的主体表面。第一端板和第二端板附接到主体并且包括垂直于主体表面设置的基本平坦的表面。第一组和第二组板邻近身体表面附接到第一和第二终板，并具有包括由第一和第二板以及第一和第二终板限定的第一和第二腔的几何形状。第一和第二空腔具有足以容纳复合预制件的第二部分的体积。第二腔与第一空腔流体连通，第一空腔与真空源流体连通。

5. 发明申请

US20070048140A1 Methods and apparatus for assembling gas turbine engines 审中-公开
标题翻译：燃气轮机发动机组装方法及装置
公开(公告)号：US20070048140A1
公开(公告)日：2007-03-01
申请号：US11210520
申请日：2005-08-24
申请人： Rachel Farr , Lee Blanton , Roger Barbe , Scott Pelletier
发明人： Rachel Farr , Lee Blanton , Roger Barbe , Scott Pelletier
IPC分类号： F01D11/00
CPC分类号： F01D5/3092 , F01D5/3015 , F01D11/006
摘要： A method for assembling a gas turbine engine compressor having a plurality of stages and a plurality of blades coupled to each respective stage includes depositing a silicone oxime sealant onto at least a portion of a compressor blade, and coupling the compressor blade to a compressor disk such that the silicone oxime sealant is between the compressor blade and the compressor disk.
摘要翻译：一种用于组装具有多个级的燃气涡轮发动机压缩机和耦合到每个相应的级的多个叶片的方法包括将硅酮肟密封剂沉积到压缩机叶片的至少一部分上，并将压缩机叶片耦合到压缩机盘硅酮肟密封剂在压缩机叶片和压缩机盘之间。

6. 发明申请

US20070086854A1 Methods and apparatus for assembling composite structures 有权
标题翻译：复合结构组装方法与装置
公开(公告)号：US20070086854A1
公开(公告)日：2007-04-19
申请号：US11252951
申请日：2005-10-18
申请人： Lee Blanton
发明人： Lee Blanton
IPC分类号： F16B5/06 , F01D25/00 , B23P15/00
CPC分类号： F01D25/243 , B29C65/562 , B29C66/1312 , B29C66/54 , B29C66/721 , B29L2031/7504 , F05D2300/603 , F16B2200/50 , F16B2200/506 , F16B2200/509 , F16L23/032 , F16L47/14 , F16L47/24 , Y10T29/49236 , Y10T403/27
摘要： A method facilitates assembling a turbine engine casing. A first casing section is positioned radially outward from a turbine engine. The first casing includes a first flange having an outer end portion, an inner end portion, and a body therebetween. At least a portion of the outer end portion has a partial frusto-conical cross-sectional profile. A second casing section including a second flange is positioned adjacent the first casing section such that a mating surface of the second flange is positioned substantially flush against a first flange mating surface. Each respective mating surface is opposite a respective load-bearing surface. A fastener is inserted through an opening in the first and second flanges to couple casing sections together such that a portion of a load-bearing surface extending over the first flange outer end portion facilitates distributing loading induced therein substantially equally across the load bearing surface.
摘要翻译：一种方法有利于组装涡轮发动机外壳。第一壳体部分从涡轮发动机径向向外定位。第一壳体包括具有外端部分，内端部分和与其之间的主体的第一凸缘。外端部的至少一部分具有局部截头圆锥形截面轮廓。包括第二凸缘的第二壳体部分定位成与第一壳体部分相邻，使得第二凸缘的配合表面基本上与第一凸缘配合表面齐平。每个相应的配合表面与相应的承载表面相对。紧固件插入通过第一和第二凸缘中的开口，以将壳体部分联接在一起，使得在第一凸缘外端部分上延伸的承载表面的一部分有助于在其中基本上均匀地分布载荷承载表面上的载荷。

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