公开(公告)号：US07516547B2

公开(公告)日：2009-04-14

申请号：US11314147

申请日：2005-12-21

申请人： Michael Edward McCann ,  Sang Y Park

发明人： Michael Edward McCann ,  Sang Y Park

IPC分类号： F01D5/14

CPC分类号： F01D5/3092 ,  C23C4/04 ,  C23C30/00 ,  F04D29/023 ,  F04D29/322 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2230/90 ,  F05D2300/1723 ,  F05D2300/509 ,  F05D2300/611 ,  Y02T50/673 ,  Y10T29/49327 ,  Y10T29/49336

摘要： A gas turbine engine blade having a dovetail with an enhanced surface for durability is disclosed. The blade includes an airfoil section and a dovetail section disposed opposite the airfoil section. The dovetail section has an outer surface, at least a portion of which has residual compressive stresses resulting from a plurality of peening operations. The dovetail section also includes a copper-nickel-indium wear coating layer disposed over the outer surface having residual compressive stresses and a lubricant coating layer disposed over the copper-nickel-indium wear coating layer, wherein the lubricant coating layer is lead-free.

摘要翻译： 公开了一种具有燕尾形的燃气涡轮发动机叶片，其具有增强的耐久性表面。 叶片包括翼型部分和与翼型部分相对设置的燕尾部分。 燕尾部分具有外表面，其至少一部分具有由多个喷丸操作产生的残余压应力。 燕尾部分还包括设置在具有残余压缩应力的外表面上的铜镍铟耐磨涂层和设置在铜 - 镍 - 铟耐磨涂层上的润滑剂涂层，其中润滑剂涂层是无铅的。

公开(公告)号：US5226784A

公开(公告)日：1993-07-13

申请号：US951929

申请日：1992-09-25

申请人： Peter W. Mueller ,  Joseph T. Stevenson ,  Josef Panovsky ,  Christopher C. Glynn ,  Sang Y. Park ,  Daniel E. Wines

发明人： Peter W. Mueller ,  Joseph T. Stevenson ,  Josef Panovsky ,  Christopher C. Glynn ,  Sang Y. Park ,  Daniel E. Wines

IPC分类号： F01D5/22 ,  F01D11/00

CPC分类号： F01D5/22 ,  F01D11/006 ,  Y10S416/50

摘要： The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.

摘要翻译： 本发明提供了一种相位独立的阻尼器和阻尼器组件，其能够在轴向，周向和径向上阻尼转子叶片的振动。 在飞行器燃气涡轮发动机压缩机转子中特别有用的一个实施例提供了一种阻尼器和阻尼器组件，其包括大致轴向延伸的叶片阻尼器，其可操作地虚拟地接合盘的大致轴向延伸的面向周向的表面并且在 刀片。 本发明提供了允许对现有发动机的简单和容易的修改以结合本发明的阻尼器的另外的优点。