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1. 发明申请

US20080089788A1 Part span shrouded fan blisk 有权
标题翻译：部分覆盖风扇叶片
公开(公告)号：US20080089788A1
公开(公告)日：2008-04-17
申请号：US11548745
申请日：2006-10-12
申请人： Kenneth Loehle , James A. Huffman , Charles K. Christopherson , Alan Glen Turner , Jeffrey F. Wessels , Gary Edward Trewiler , Peter J, Rock , Paul S. Manicke , Joseph Capozzi , Jeffrey Howard Nussbaum , Leslie M. Pommer
发明人： Kenneth Loehle , James A. Huffman , Charles K. Christopherson , Alan Glen Turner , Jeffrey F. Wessels , Gary Edward Trewiler , Peter J, Rock , Paul S. Manicke , Joseph Capozzi , Jeffrey Howard Nussbaum , Leslie M. Pommer
IPC分类号： F01D5/22
CPC分类号： F01D5/22 , F01D5/34 , F04D29/321 , F05B2230/239 , F05D2220/326 , F05D2220/327 , F05D2230/232 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.
摘要翻译：包括盘，多个从圆盘径向向外延伸的周向间隔开的翼型件，多个护罩段，其周向设置在多个翼型件之间，并且构造成附接到多个翼型件的相应翼面和多个磨损表面其中所述多个磨损表面中的至少一个磨损表面被构造和设置以防止相邻护罩段之间的过度磨损。多个护罩段的每个护罩区段可以通过焊接连接件附接到相应的翼型件，以允许间隙在翼型平移期间摩擦焊接到盘毂以避免高应力区域。

2. 发明授权

US07758311B2 Part span shrouded fan blisk 有权
标题翻译：部分覆盖风扇叶片
公开(公告)号：US07758311B2
公开(公告)日：2010-07-20
申请号：US11548745
申请日：2006-10-12
申请人： Kenneth Loehle , James A. Huffman , Charles K. Christopherson , Alan Glen Turner , Jeffrey F. Wessels , Gary Edward Trewiler , Peter J. Rock , Paul S. Manicke , Joseph Capozzi , Jeffrey Howard Nussbaum , Leslie M Pommer
发明人： Kenneth Loehle , James A. Huffman , Charles K. Christopherson , Alan Glen Turner , Jeffrey F. Wessels , Gary Edward Trewiler , Peter J. Rock , Paul S. Manicke , Joseph Capozzi , Jeffrey Howard Nussbaum , Leslie M Pommer
IPC分类号： F01D5/22
CPC分类号： F01D5/22 , F01D5/34 , F04D29/321 , F05B2230/239 , F05D2220/326 , F05D2220/327 , F05D2230/232 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.
摘要翻译：包括盘，多个从圆盘径向向外延伸的周向间隔开的翼型件，多个护罩段，其周向设置在多个翼型件之间，并且构造成附接到多个翼型件的相应翼面和多个磨损表面其中所述多个磨损表面中的至少一个磨损表面被构造和设置以防止相邻护罩段之间的过度磨损。多个护罩段的每个护罩区段可以通过焊接连接件附接到相应的翼型件，以允许间隙在翼型平移期间摩擦焊接到盘毂以避免高应力区域。

3. 发明授权

US06371725B1 Conforming platform guide vane 有权
标题翻译：符合平台导叶
公开(公告)号：US06371725B1
公开(公告)日：2002-04-16
申请号：US09607753
申请日：2000-06-30
申请人： John Alan Manteiga , Jeffrey Howard Nussbaum , Joseph Capozzi , John Lawrence Noon
发明人： John Alan Manteiga , Jeffrey Howard Nussbaum , Joseph Capozzi , John Lawrence Noon
IPC分类号： F01D102
CPC分类号： F01D5/14 , F01D9/042 , F02K3/06 , F05B2260/301 , F05D2220/327 , F05D2230/60 , F05D2240/80 , Y02T50/671 , Y02T50/673
摘要： A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.
摘要翻译：风扇出口导叶包括符合其弓形侧面的整体外部和内部平台，以及平台上的多个安装凸台。平台侧面弧形以符合叶片侧面，以提高空气动力学效率。多个安装凸台改善了叶片对相应支撑环的安装。

4. 发明授权

US06422820B1 Corner tang fan blade 有权
标题翻译：角柄风扇刀片
公开(公告)号：US06422820B1
公开(公告)日：2002-07-23
申请号：US09607490
申请日：2000-06-30
申请人： Bernard Joseph Anderson , Jeffrey Howard Nussbaum , Juan Mario Gomez
发明人： Bernard Joseph Anderson , Jeffrey Howard Nussbaum , Juan Mario Gomez
IPC分类号： F01D532
CPC分类号： F01D5/3053 , Y02T50/671 , Y10T29/49321
摘要： A fan blade includes perforated anchor tangs, one with inboard corners and the remainder without. The corners are disposed in a complementary seat in a rotor disk for limiting blade pivoting during assembly.
摘要翻译：风扇叶片包括穿孔的锚脚，一个具有内侧角，其余没有。角部设置在转子盘中的互补座中，以限制在组装期间的叶片枢转。

5. 发明授权

US06338611B1 Conforming platform fan blade 有权
标题翻译：符合平台风扇叶片
公开(公告)号：US06338611B1
公开(公告)日：2002-01-15
申请号：US09607491
申请日：2000-06-30
申请人： Bernard Joseph Anderson , Jeffrey Howard Nussbaum , Juan Mario Gomez
发明人： Bernard Joseph Anderson , Jeffrey Howard Nussbaum , Juan Mario Gomez
IPC分类号： F03B312
CPC分类号： F02K3/06 , F01D5/141 , F05D2220/327 , F05D2240/80 , F05D2250/34 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： A fan blade includes an airfoil having a root and an integral platform. The platform includes forward and aft ends and arcuate first and second sides therebetween. The airfoil root is laterally offset closer to the platform first side than the second side. Impact loads with a trailing blade during a blade-out failure are accordingly distributed for reducing peak loading in the trailing blade and damage thereto.
摘要翻译：风扇叶片包括具有根部和整体平台的翼型件。该平台包括前端和后端以及它们之间的弓形第一和第二侧。机翼根部比第二侧更侧向偏移到平台第一侧。因此，在叶片出故障期间与后叶片的冲击载荷相应地分布，以减少后叶片中的峰值负载并对其造成损坏。

6. 发明申请

US20130089421A1 GAS TURBINE ENGINE AIRFOIL TIP RECESSES 审中-公开
标题翻译：气体涡轮发动机气翼提示
公开(公告)号：US20130089421A1
公开(公告)日：2013-04-11
申请号：US13253328
申请日：2011-10-05
申请人： Jeffrey Howard Nussbaum , Andrea MacPherson Cox , Catherine Lee Pommer
发明人： Jeffrey Howard Nussbaum , Andrea MacPherson Cox , Leslie Martin Pommer
IPC分类号： F01D11/08
CPC分类号： F01D5/20 , F05D2240/125
摘要： A gas turbine engine airfoil extending from an airfoil base to an airfoil tip at a free end of the airfoil and from a leading edge to a trailing edge of the airfoil has at least one recess extending into and circumferentially completely through the airfoil tip and located inwardly of the leading and trailing edges. The recess is located in an area of the airfoil tip subject to high tip vibratory stress and or rubs and may be a circular scallop having a scallop radius and a maximum depth of a few mills in a range of about 0.005-0.01 inches as measured from a nominal tip edge without the recess. The airfoil may be on a radial blade, a stator vane, or an impeller blade. An annular tip seal may surround a plurality of such airfoil tips with an airfoil tip clearance therebetween.
摘要翻译：从机翼基座延伸到翼型件的自由端并且从翼型的前缘到后缘的燃气涡轮发动机翼型件具有至少一个延伸到其中并沿圆周完全穿过翼型件末端的凹部，并位于内侧的前缘和后缘。该凹部位于翼尖尖端的区域中，受到高尖端振动应力的摩擦，并且可以是圆形扇贝，扇形半径和最大深度为几毫米，范围为约0.005-0.01英寸，从无凹槽的公称顶端边缘。翼型件可以在径向叶片，定子叶片或叶轮叶片上。环形尖端密封件可以围绕多个这样的翼型件尖端，其间具有翼面顶端间隙。

7. 发明授权

US06905309B2 Methods and apparatus for reducing vibrations induced to compressor airfoils 有权
标题翻译：减少压缩机翼型振动的方法和装置
公开(公告)号：US06905309B2
公开(公告)日：2005-06-14
申请号：US10650288
申请日：2003-08-28
申请人： Jeffrey Howard Nussbaum , Xin Wei , Tara Chaidez , Michael Macrorie
发明人： Jeffrey Howard Nussbaum , Xin Wei , Tara Chaidez , Michael Macrorie
IPC分类号： F01D5/16 , F01D5/10 , F01D5/14 , F01D1/00
CPC分类号： F01D5/16 , F01D5/10 , F01D5/141 , F05D2230/11 , F05D2240/301 , F05D2250/71 , Y10T29/49318
摘要： A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.
摘要翻译：一种方法能够制造用于燃气涡轮发动机的转子叶片。该方法包括形成包括第一侧壁和第二侧壁的翼型件，每个翼型件在翼型件根部和翼型件顶端之间沿径向跨度延伸，并且其中第一和第二侧壁在前缘和后缘连接并且形成从所述翼型件第一侧壁和所述翼型件第二侧壁中的至少一个向外延伸的小翼，使得所述翼片与所述翼片和所述翼型件第一侧壁和所述第二侧壁中的至少一个之间延伸。

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