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1. 发明授权

US4410385A Method of making a composite article 失效
标题翻译：复合制品的制作方法
公开(公告)号：US4410385A
公开(公告)日：1983-10-18
申请号：US366410
申请日：1982-04-07
申请人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
发明人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
IPC分类号： B29C70/22 , D06M23/06
CPC分类号： B29C70/22 , D06M23/06
摘要： A composite fabric preform and article made of both structural and thermoplastic fibrous materials and a method of making such preform and article, the method improving the handling properties of the composite. A plurality of layers of fabric made from structural fibrous material are disposed in a stacked assembly with layers sequentially adjacent each other. At least each of alternate layers of the alternate layers of fabric include within its weave thermoplastic fibrous material intermixed with the structural fibrous material. The layers of fabric, preferably under pressure, are heated at a temperature sufficient to promote bonding action by the thermoplastic fibers at junctures between fibrous materials.
摘要翻译：复合织物预制件和由结构和热塑性纤维材料制成的制品以及制备这种预成型件和制品的方法，该方法提高了复合材料的处理性能。由结构纤维材料制成的多层织物布置在层叠的组件中，其中层彼此顺序相邻。织物的交替层的至少每个替代层包括在其结构纤维材料中混合的其编织热塑性纤维材料内。优选在压力下的织物层在足以促进热塑性纤维在纤维材料之间的接合处的粘合作用的温度下被加热。

2. 发明授权

US4047840A Impact absorbing blade mounts for variable pitch blades 失效
标题翻译：用于变桨距叶片的冲击吸收刀片安装座
公开(公告)号：US4047840A
公开(公告)日：1977-09-13
申请号：US581751
申请日：1975-05-29
申请人： Richard Ravenhall , Charles T. Salemme , Arthur P. Adamson
发明人： Richard Ravenhall , Charles T. Salemme , Arthur P. Adamson
IPC分类号： F04D29/36 , B64C11/02 , F02C9/22 , F04D29/32 , F01D5/32
CPC分类号： F04D29/323 , F01D5/3007 , F01D5/3053 , F01D7/00 , F02K3/06 , F05D2260/36 , F05D2260/4031 , F05D2260/74 , F05D2260/79
摘要： A variable pitch blade and blade mount which is suitable for propellers, fans and the like and which has improved impact resistance. The invention is particularly directed to composite fan blades and blade mounting arrangements wherein the blades are permitted to pivot relative to a turbine hub about an axis generally parallel to the centerline of the engine upon impact of a large foreign object, such as a bird. By thus providing for the pivoting of the blades upon impact, centrifugal force recovery becomes the principal energy absorbing mechanism and a blade having improved impact strength is obtained.
摘要翻译：适用于螺旋桨，风扇等的变桨距叶片和叶片座，具有改善的抗冲击性。本发明特别涉及复合风扇叶片和叶片安装装置，其中当大型异物（例如鸟）撞击时，叶片允许相对于涡轮机枢轴围绕大致平行于发动机的中心线的轴线枢转。通过这样提供叶片在冲击时的枢转，离心力恢复成为主要的能量吸收机构，并获得具有改善的冲击强度的叶片。

3. 发明授权

US4594761A Method of fabricating hollow composite airfoils 失效
标题翻译：中空复合翼型件的制造方法
公开(公告)号：US4594761A
公开(公告)日：1986-06-17
申请号：US579631
申请日：1984-02-13
申请人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
发明人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
IPC分类号： F01D5/14 , B23P15/02 , B23P15/04 , B29D99/00 , B32B3/10 , B64C3/18 , B64C11/26 , F01D5/18 , F01D5/28 , F01D9/04
CPC分类号： B29D99/0028 , B23P15/04 , B64C11/26 , F01D5/282 , F01D9/042 , Y02T50/672 , Y02T50/673 , Y10T29/49337 , Y10T29/49339 , Y10T29/49799 , Y10T29/49867 , Y10T29/49893
摘要： A hollow composite airfoil with an integral internal support rib of fluoroelastomer rubber is formed by bracketing the rib between two silicone rubber mandrels to form a core assembly having a desired aerodynamic shape, then building up on opposite sides of the core assembly separate stacks of laminae of a composite material of graphite (or carbon) and glass fibers impregnated with an epoxy resin, with the two stacks overlapping adjacent to the leading and trailing edges of the core assembly. Heat and pressure are then applied to the core assembly with the laminae thereon to bond together the laminae of each stack, then to bond the two stacks together along the overlapping portions thereof and to bond the two stacks to the rib to form a continuous shell around the core assembly. The mandrels are then removed. One open end of the resulting hollow airfoil is plugged and that end is inserted into a recess in a mounting platform with a predetermined clearance space therebetween. An elastomeric material is then injected into the clearance space for filling it, the elastomer then being cured to bond the platform to the airfoil. A polyurethane sheath is wrapped around the airfoil and cured. Airfoils with plural ribs are also disclosed.
摘要翻译：具有含氟弹性体橡胶的整体内部支撑肋的中空复合翼片通过在两个硅橡胶心轴之间包围肋而形成，以形成具有所需空气动力学形状的芯组件，然后在芯组件的相对侧上建立分离的层叠层石墨（或碳）和浸渍有环氧树脂的玻璃纤维的复合材料，其中两个堆叠重叠在芯组件的前缘和后缘附近。然后将热和压力施加到具有其上的薄片的芯组件上以将每个叠层的薄片粘合在一起，然后沿着其重叠部分将两个叠层结合在一起，并将两个叠层结合到肋以形成围绕核心装配。然后将心轴移除。所形成的中空翼型件的一个开口端被堵塞，并且该端部以其间具有预定的间隙空间插入到安装平台中的凹部中。然后将弹性体材料注入到间隙空间中以便填充弹性材料，然后将弹性体固化以将平台粘合到翼型件上。将聚氨酯护套缠绕在翼型上并固化。还公开了具有多个肋的翼型。

4. 发明授权

US4407885A Composite article 失效
标题翻译：综合文章
公开(公告)号：US4407885A
公开(公告)日：1983-10-04
申请号：US229047
申请日：1981-01-28
申请人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
发明人： Guy C. Murphy , Jackie D. Jones , Charles T. Salemme
IPC分类号： D03D1/00 , B32B5/08 , B32B5/26 , D06M23/06 , B32B7/00
CPC分类号： D06M23/06 , Y10T428/2982 , Y10T428/30 , Y10T442/3252 , Y10T442/3309
摘要： A composite fabric preform and article made of both structural and thermoplastic fibrous materials and a method of making such preform and article, the method improving the handling properties of the composite. A plurality of layers of fabric made from structural fibrous material are disposed in a stacked assembly with layers sequentially adjacent each other. At least each of alternate layers of the alternate layers of fabric include within its weave thermoplastic fibrous material intermixed with the structural fibrous material. The layers of fabric, preferably under pressure, are heated at a temperature sufficient to promote bonding action by the thermoplastic fibers at junctures between fibrous materials.
摘要翻译：复合织物预制件和由结构和热塑性纤维材料制成的制品以及制备这种预成型件和制品的方法，该方法提高了复合材料的处理性能。由结构纤维材料制成的多层织物布置在层叠的组件中，其中层彼此顺序相邻。织物的交替层的至少每个替代层包括在其结构纤维材料中混合的其编织热塑性纤维材料内。优选在压力下的织物层在足以促进热塑性纤维在纤维材料之间的接合处的粘合作用的温度下被加热。

5. 发明授权

US4019832A Platform for a turbomachinery blade 失效
标题翻译：涡轮机叶片平台
公开(公告)号：US4019832A
公开(公告)日：1977-04-26
申请号：US661968
申请日：1976-02-27
申请人： Charles T. Salemme , Richard Ravenhall , David J. Harris
发明人： Charles T. Salemme , Richard Ravenhall , David J. Harris
IPC分类号： F01D5/30 , F01D11/00 , B64C11/06 , F01D7/00
CPC分类号： F01D11/008 , F01D5/30
摘要： A turbomachinery blade platform comprising a pair of complementary platform halves, each having an outer flow path defining shroud adapted to extend generally laterally of the blade. An inner flange on each platform half, also extending generally laterally of the blade, is retained in a cooperating slot formed within the support structure retaining the blade. A structural member extending between the shroud and the flange is contoured to conform to an overlapping wedging surface disposed about the blade airfoil surface. The platform is thus provided with redundant retention by both the blade and by the blade support structure.
摘要翻译：一种涡轮机械刀片平台，包括一对互补的平台半部，每个具有限定护罩的外部流动路径，所述外部流动路径适于大致横向延伸。每个平台一半上的内凸缘也大致横向延伸，保持在形成在保持叶片的支撑结构内的配合槽中。在护罩和凸缘之间延伸的结构构件成形为符合设置在叶片翼面表面周围的重叠楔形表面。因此，该平台由叶片和叶片支撑结构两者提供冗余的保持。

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