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1. 发明授权

US06929453B2 Locking spacer assembly for slotted turbine component 失效
标题翻译：用于开槽涡轮机部件的锁定间隔件组件
公开(公告)号：US06929453B2
公开(公告)日：2005-08-16
申请号：US10733737
申请日：2003-12-11
申请人： Edwin L. Kite , Brian Potter , Paul Matheny
发明人： Edwin L. Kite , Brian Potter , Paul Matheny
IPC分类号： F01D5/30 , F01D5/32
CPC分类号： F01D5/32 , F01D5/3038
摘要： Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.
摘要翻译：根据本发明的方面涉及一种用于开槽涡轮发动机部件的锁定间隔件组件。在一个实施例中，本发明的各方面可以用于组装和拆卸承载一排翼型件的盘，如可以在涡轮发动机的压缩机或涡轮机部分中发现的那样。根据本发明的间隔件是多部件组件。在一个实施例中，间隔件包括至少三个子部件：第一和第二端部支撑件和填料。这些部件中的每一个的内表面和外表面可以具有各种特征，以便于操作中离合负载的组装和分配的接合。这些部件可以通过保持器保持在一起，该保持器可以容纳在设置在端部支撑件和填料中的切口中。

2. 发明授权

US07008170B2 Compressor diaphragm with axial preload 失效
标题翻译：压缩机轴向轴向预压
公开(公告)号：US07008170B2
公开(公告)日：2006-03-07
申请号：US10811257
申请日：2004-03-26
申请人： Sanford B. Proveaux , Edwin L. Kite
发明人： Sanford B. Proveaux , Edwin L. Kite
IPC分类号： F01D25/24
CPC分类号： F04D29/542 , F01D25/246 , F05D2230/644
摘要： Aspects of the invention relate to a system for reducing relative movement between the outer shroud of a compressor diaphragm and the compressor cylinder of a turbine engine, thereby minimizing the wearing of these parts. Embodiments of the invention include a system for applying an axial preload on the outer shroud of a compressor diaphragm, preferably in the same direction as the gas load in the compressor. The system can be installed at or near the horizontal joint such that the axial preload can be applied substantially at the horizontal joint, which is the location of the largest relative movement. In one embodiment, the axial preload system can include a two-piece wedge block and pin. As the pin is driven between the two wedge blocks, the force applied to the pin can be converted to an axial load by the spreading apart of the two wedge block sections.
摘要翻译：本发明的方面涉及一种用于减小压缩机隔膜的外护罩和涡轮发动机的压缩机气缸之间的相对运动的系统，从而使这些部件的磨损最小化。本发明的实施例包括一种用于在压缩机隔膜的外护罩上施加轴向预载的系统，优选地与压缩机中的气体负载相同的方向。该系统可以安装在水平接头处或附近，使得轴向预载荷可以基本上施加在作为最大相对运动的位置的水平接头处。在一个实施例中，轴向预加载系统可以包括两件式楔块和销。当销在两个楔形块之间被驱动时，施加到销的力可以通过两个楔形块部分的扩张而转换成轴向载荷。

3. 发明授权

US07780419B1 Replaceable leading edge insert for an IBR 有权
标题翻译：可更换IBR的前缘插入
公开(公告)号：US07780419B1
公开(公告)日：2010-08-24
申请号：US11715044
申请日：2007-03-06
申请人： Alfred P. Matheny , Edwin L. Kite
发明人： Alfred P. Matheny , Edwin L. Kite
IPC分类号： F01D5/30
CPC分类号： F01D5/34 , F01D5/005 , F04D29/023 , F04D29/324 , F05D2230/64 , F05D2240/121 , F05D2240/303 , F05D2300/133 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a damaged insert from an integrally bladed disk. One or more of the fastener pins provides for an electrical conductive path that bypasses the disbondable composition during a lightening strike so that the insert does not release. Each replaceable insert includes a root portion that fits within a slot of the rotor disk, with each insert being secured against radial displacement by two shear pins secured within two shear pin slots formed in both the insert root portion and the rotor disk slot. The shear pin slots are curved and follow the curvature of the airfoil at the junction to the rotor disk. A retaining and balancing ring is secured within an annular groove and functions to retain the shear pins within the slots and to balance the rotor disk. The combination of the fastener pins, the electrochemically disbondable composition, and the shear pins in the slot provide for three methods of securing an insert to the blade so that a damaged insert can be easily replaced.
摘要翻译：一种用于燃气涡轮发动机的压缩机叶片，其包括通过一排紧固件销沿着插入件的后边缘附接到钛刀片的复合前缘插入件，以防止解锁。每个插入物也通过电化学脱粘组合物固定，以便容易地从一体式叶片的盘中移除损坏的插入物。一个或多个紧固销提供了在减轻击打期间绕过不可分散组合物的导电路径，使得插入物不释放。每个可替换的插入件包括装配在转子盘的槽内的根部，每个插入件通过固定在形成在插入件根部和转子盘槽中的两个剪切销槽内的两个剪切销抵抗径向位移。剪切销槽是弯曲的，并且在与转子盘的连接处跟随翼型的曲率。保持和平衡环固定在环形槽内，并且用于将剪切销保持在槽内并平衡转子盘。紧固件销钉，电化学脱粘组合物和槽中的剪切销的组合提供了将插入件固定到刀片上的三种方法，使得可以容易地更换损坏的刀片。

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