公开(公告)号：US5314309A

公开(公告)日：1994-05-24

申请号：US804391

申请日：1991-12-10

申请人： Anthony Blakeley ,  Gregory E. Horihan ,  Timothy S. Konicek ,  Patrick J. O'Callaghan ,  Martin W. Carrington ,  Jeffrey A. Brown

发明人： Anthony Blakeley ,  Gregory E. Horihan ,  Timothy S. Konicek ,  Patrick J. O'Callaghan ,  Martin W. Carrington ,  Jeffrey A. Brown

IPC分类号： B29C70/08 ,  B29C70/14 ,  B29C70/76 ,  B29C70/86 ,  B29C70/88 ,  B29D99/00 ,  F01D5/28 ,  F01D5/14 ,  B32B17/04

CPC分类号： B29D99/0025 ,  B29C70/081 ,  B29C70/14 ,  B29C70/46 ,  B29C70/76 ,  B29C70/86 ,  B29C70/885 ,  F01D5/282 ,  B29K2063/00 ,  B29K2105/0845 ,  B29K2105/12 ,  B29K2305/02 ,  B29K2705/00 ,  B29L2031/082 ,  F05D2220/50 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49337

摘要： A turbine blade (1), for example, for a ram air turbine engine, and method of making the turbine blade, wherein the turbine blade (1) includes a blade retention insert member (2) having a hub connector (3). The turbine blade (1) is fabricated by using sheet molding compound consisting essentially of discontinuous short fibers (7) initially random spaced within a polymer matrix sheet. A plurality of sheets of sheet molding compound are precut to a desired configuration or shape and placed in a heated blade mold. Heat and pressure are applied to the mold causing the sheet molding compound to flow around the blade retention insert member (2) and fill the mold cavity. The flow of the sheet molding compound causes the initially randomly oriented short fibers (7) to preferentially align in the direction of flow to rigidify the turbine blade (1). Fiber woven cloth skins (8) may integrally molded with the sheet molding compound during the compression molding process to accommodate high loads, and an aluminum chopped strand veil cloth (9) may also be integrally molded into the blade (1) or layers of conductive material may be deposited on at least portions of the surface of the turbine blade (1) during a secondary operation. At least one woven cloth material (6) may also be integrally molded into the turbine blade (1) to react to bending loads and to provide additional load transfer capabilities.

摘要翻译： 例如，用于冲压式空气涡轮发动机的涡轮机叶片（1）和制造涡轮机叶片的方法，其中所述涡轮叶片（1）包括具有轮毂连接器（3）的叶片保持插入构件（2）。 涡轮叶片（1）通过使用基本上由不连续短纤维（7）组成的片状模塑料制成，其最初在聚合物基质片材内随机间隔开。 多片片状模塑料切割成所需的构造或形状，并放置在加热的刀片模具中。 将加热和压力施加到模具上，使得片状模塑料围绕刀片保持插入件（2）流动并填充模腔。 片状模塑料的流动使最初随机取向的短纤维（7）在流动方向上优先对准以使透平叶片（1）硬化。 纤维编织布表面（8）可以在压缩成型过程中与片状模塑料整体模制，以适应高负荷，而铝短切纤维布（9）也可以整体模制在叶片（1）或导电层 在二次操作期间，材料可以沉积在涡轮叶片（1）的表面的至少部分上。 至少一种织布材料（6）也可以一体地模制到涡轮叶片（1）中以对弯曲载荷作出反应并提供额外的载荷传递能力。

公开(公告)号：US5118257A

公开(公告)日：1992-06-02

申请号：US528477

申请日：1990-05-25

申请人： Anthony Blakeley ,  Gregory E. Horihan ,  Timothy S. Konicek ,  Patrick J. O'Callaghan ,  Martin W. Carrington ,  Jeffrey A. Brown

发明人： Anthony Blakeley ,  Gregory E. Horihan ,  Timothy S. Konicek ,  Patrick J. O'Callaghan ,  Martin W. Carrington ,  Jeffrey A. Brown

IPC分类号： B64C11/04 ,  F01D5/30

CPC分类号： F01D5/30 ,  B64C11/04 ,  Y10T29/49321 ,  Y10T29/49337

摘要： A root attachment for a turbine blade is integrally molded with a composite turbine blade for a ram air turbine. The root attachment includes an insert at the one end of the root attachment for integrally molding within the blade and a hub connector at an opposite end for connecting the blade to a rotor hub. The insert has a geometry and surface area such that a dual load carrying capability is achieved during molding by the formation of an adhesive bond between the material of the blade and the insert and also a mechanical locking which resists failure in bearing. Each of the adhesive bond and the mechanical locking is designed to fail above an ultimate design load.

摘要翻译： 用于涡轮叶片的根部附件与用于冲压式空气涡轮机的复合涡轮机叶片一体地模制。 根部附件包括在根部附件的一端处的用于在叶片内整体模制的插入件和在相对端处的毂连接器，用于将叶片连接到转子毂。 插入件具有几何形状和表面积，使得在模制期间通过在叶片的材料和插入件之间形成粘合剂结合以及抵抗轴承故障的机械锁定来实现双承载能力。 每个粘合剂粘合剂和机械锁定被设计成超过最终设计负载。