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1. 发明授权

US06666017B2 Counterrotatable booster compressor assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的可逆增压压缩机组件
公开(公告)号：US06666017B2
公开(公告)日：2003-12-23
申请号：US10154584
申请日：2002-05-24
申请人： Ian Francis Prentice , David William Crall , Bruce Clark Busbey , Christopher Charles Glynn , Donald Ray Bond
发明人： Ian Francis Prentice , David William Crall , Bruce Clark Busbey , Christopher Charles Glynn , Donald Ray Bond
IPC分类号： F02K3072
CPC分类号： F01D5/022 , F02C3/067 , F02K3/072 , F04D19/024 , F04D25/04
摘要： A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft. The counterrotatable booster compressor assembly includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan shaft extension at a first location so as to form a portion of an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan shaft extension at a second location so as to form a portion of an outer flowpath for the counterrotatable booster compressor, where each compressor blade of the second compressor blade row is positioned between the first and second platform members.
摘要翻译：一种用于燃气涡轮发动机的可逆转增压压缩机组件，其具有可逆转风扇部分，其具有连接到第一驱动轴的第一风扇叶片排和与第一风扇叶片排轴向间隔开并连接到第二驱动轴的第二风扇叶片排。可逆转增压压缩机组件包括连接到第一驱动轴的第一压缩机叶片排，与驱动第二风扇叶片排的第二驱动轴连接的多个风扇轴延伸部，以及与每个风扇轴延伸部一体的至少一个压缩机叶片以形成与第一压缩机叶片排交叉的第二压缩机叶片排。可逆转增压压缩机还包括在第一位置处与每个风扇轴延伸部一体形成的第一平台构件，以便形成用于可逆转增压压缩机的内部流路的一部分，以及在第二位置处与每个风扇轴延伸部一体形成的第二平台构件以便形成用于可逆转增压压缩机的外部流路的一部分，其中第二压缩机叶片排的每个压缩机叶片位于第一和第二平台构件之间。

2. 发明授权

US06478545B2 Fluted blisk 有权
标题翻译：凹槽的叶片
公开(公告)号：US06478545B2
公开(公告)日：2002-11-12
申请号：US09801119
申请日：2001-03-07
申请人： David William Crall , John Robert Kelley , Ian Francis Prentice , Gregory Scott McNulty , Michael De Wayne Toye
发明人： David William Crall , John Robert Kelley , Ian Francis Prentice , Gregory Scott McNulty , Michael De Wayne Toye
IPC分类号： F01D530
CPC分类号： F01D5/34 , B23K20/129 , B23K2101/001 , F01D5/143 , F05D2230/23 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325
摘要： A blisk includes a disk having a rim. A row of blades extends outwardly from the rib in a unitary construction. The blades are spaced apart in the disk rim to define fluted inner flowpath channels extending axially between the blades to bound corresponding flow passages therebetween.
摘要翻译：叶片包括具有边缘的盘。一排叶片以一体式结构从肋部向外延伸。叶片在盘缘中间隔开，以限定在叶片之间轴向延伸的带槽的内部流道通道，以在其间结合相应的流动通道。

3. 发明授权

US07575417B2 Reinforced fan blade 有权
标题翻译：钢筋风扇叶片
公开(公告)号：US07575417B2
公开(公告)日：2009-08-18
申请号：US10656380
申请日：2003-09-05
申请人： Scott Roger Finn , Govindarajan Rengarajan , David William Crall , Ian Francis Prentice
发明人： Scott Roger Finn , Govindarajan Rengarajan , David William Crall , Ian Francis Prentice
IPC分类号： F03B3/12 , D04H1/00
CPC分类号： F01D5/147 , F01D5/282 , F04D29/324 , F05D2220/36 , F05D2240/303 , Y02T50/672 , Y02T50/673 , Y10T428/249924
摘要： A fan blade including a plurality of fiber composite layers and at least one high elongation fiber composite strip joining one of the fiber composite layers at a joint. A method of making a fan blade includes joining a plurality of fiber composite layers and joining at least one high elongation fiber composite strip to one of the plurality of fiber composite layers. An end of the high elongation fiber composite strip meets an end of the fiber composite layer at a joint.
摘要翻译：一种风扇叶片，包括多个纤维复合层，以及至少一个高伸长率的纤维复合带，其在接合处接合所述纤维复合层之一。一种制造风扇叶片的方法包括：接合多个纤维复合层，并将至少一个高伸长率纤维复合带接合到多个纤维复合层之一。高伸长率纤维复合带的端部在接头处与纤维复合层的端部相交。

4. 发明授权

US08939099B2 Methods and systems for stitching composite materials 有权
标题翻译：拼接复合材料的方法和系统
公开(公告)号：US08939099B2
公开(公告)日：2015-01-27
申请号：US13490284
申请日：2012-06-06
申请人： Dong-Jin Shim , Ian Francis Prentice , Julian O'Flynn , Ross Spoonire , Wendy Wen-Ling Lin
发明人： Dong-Jin Shim , Ian Francis Prentice , Julian O'Flynn , Ross Spoonire , Wendy Wen-Ling Lin
IPC分类号： D05B3/00 , B32B3/14
CPC分类号： D05B93/00 , B32B7/08 , B32B2307/54 , F05D2300/603 , Y10T428/24033
摘要： A composite material includes a composite body having a composite surface, and a reinforcing element extending through the composite body in a first plurality of stitches and a second plurality of stitches. The first plurality of stitches are aligned relative to the composite surface substantially similarly to each other. The second plurality of stitches are aligned relative to the composite surface substantially dissimilarly to each other.
摘要翻译：复合材料包括具有复合表面的复合体和以第一多个针迹和第二多个针迹延伸穿过复合体的加强元件。第一多个针脚相对于复合表面大致相似地对准。所述第二多个针脚相对于所述复合表面基本上彼此不同地对准。

5. 发明申请

US20130164140A1 AIRFOILS INCLUDING COMPLIANT TIP 有权
标题翻译：航空器包括合规提示
公开(公告)号：US20130164140A1
公开(公告)日：2013-06-27
申请号：US13336001
申请日：2011-12-23
申请人： Pranav Dhoj Shah , Scott Roger Finn , Nicholas Joseph Kray , Ian Francis Prentice , Dong-Jin Shim , Bo Wang
发明人： Pranav Dhoj Shah , Scott Roger Finn , Nicholas Joseph Kray , Ian Francis Prentice , Dong-Jin Shim , Bo Wang
IPC分类号： F01D5/14
CPC分类号： F01D5/20 , F01D21/045 , F05D2300/43 , F05D2300/431 , F05D2300/432 , Y02T50/672 , Y02T50/673
摘要： An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact.
摘要翻译：翼型件，风扇组件和发动机包括至少一个包括根部，主体部分和顶端部分的翼型件。主体部分被配置为从根部径向向外延伸，并且尖端部分被构造成从根部部分和主体部分径向向外延伸。所述翼型件包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。所述翼型件在尖端部分包括柔性尖端。柔性尖端沿着顶端部分的至少一部分沿着弦向和跨度方向延伸。柔性尖端构造成沿着尖端部分提供波传播，使得在异物冲击期间，靠近尖端部分和后缘的临界应变减小。

6. 发明授权

US08308435B2 Methods and system for balancing turbine rotor assemblies 有权
标题翻译：平衡涡轮转子组件的方法和系统
公开(公告)号：US08308435B2
公开(公告)日：2012-11-13
申请号：US11965042
申请日：2007-12-27
申请人： Albert Frank Storace , Ian Francis Prentice
发明人： Albert Frank Storace , Ian Francis Prentice
IPC分类号： F01D25/04
CPC分类号： G01M15/14 , F01D5/027 , G01M1/22 , G01M1/36
摘要： A balancing system and method for reducing imbalance in a rotatable member of a machine is provided. The system includes a plurality of vibration sensors positioned about a stationary portion of the machine, a controller assembly communitively coupled to the plurality of vibration sensors, and a balancing assembly coupled to the rotatable member, said balancing assembly configured to wirelessly communicate with said controller assembly, said balancing assembly configured to modify the weight distribution of the rotatable member in response to a command wirelessly transmitted from the controller assembly. The controller assembly is configured to receive data from the plurality of vibration sensors and determine an imbalance in the rotatable member using the received data.
摘要翻译：提供了一种用于减少机器的可旋转构件的不平衡的平衡系统和方法。该系统包括围绕机器的固定部分定位的多个振动传感器，与多个振动传感器共同耦合的控制器组件，以及耦合到可旋转构件的平衡组件，所述平衡组件配置成与所述控制器组件无线地连通所述平衡组件被配置为响应于从控制器组件无线传送的命令来修改可旋转构件的重量分布。控制器组件被配置为从多个振动传感器接收数据，并使用接收的数据确定可旋转构件的不平衡。

7. 发明申请

US20110008156A1 COMPOSITE TURBINE NOZZLE 有权
标题翻译：复合涡轮喷嘴
公开(公告)号：US20110008156A1
公开(公告)日：2011-01-13
申请号：US12499329
申请日：2009-07-08
申请人： Ian Francis Prentice , Mark Eugene Noe
发明人： Ian Francis Prentice , Mark Eugene Noe
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D9/042 , F01D11/005 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes.
摘要翻译：复合喷嘴段包括在弓形径向外段和内带段之间径向延伸的一个或多个翼型件，其具有围绕中心线轴线弯曲的带状帘布层，外带段的外后缘上的外弦密封线，外侧翼缘沿着外带段的压力和吸力侧边缘。增厚区域在压力和吸力侧边缘处可以是最厚的，并且在外带段的中间附近最薄。加厚的区域从加厚区域的后端朝向外带段的前凸缘逐渐变细。插入层可以设置在加厚区域之间的一些带状层之间，可以分组在一起，或者分散在一些带状层中。插入层可以具有三角形形状。

8. 发明申请

US20090169384A1 METHODS AND SYSTEM FOR BALANCING TURBINE ROTOR ASSEMBLIES 有权
标题翻译：用于平衡涡轮转子总成的方法和系统
公开(公告)号：US20090169384A1
公开(公告)日：2009-07-02
申请号：US11965042
申请日：2007-12-27
申请人： Albert Frank Storace , Ian Francis Prentice
发明人： Albert Frank Storace , Ian Francis Prentice
IPC分类号： F16F15/10
CPC分类号： G01M15/14 , F01D5/027 , G01M1/22 , G01M1/36
摘要： A balancing system and method for reducing imbalance in a rotatable member of a machine is provided. The system includes a plurality of vibration sensors positioned about a stationary portion of the machine, a controller assembly communitively coupled to the plurality of vibration sensors, and a balancing assembly coupled to the rotatable member, said balancing assembly configured to wirelessly communicate with said controller assembly, said balancing assembly configured to modify the weight distribution of the rotatable member in response to a command wirelessly transmitted from the controller assembly. The controller assembly is configured to receive data from the plurality of vibration sensors and determine an imbalance in the rotatable member using the received data.
摘要翻译：提供了一种用于减少机器的可旋转构件的不平衡的平衡系统和方法。该系统包括围绕机器的固定部分定位的多个振动传感器，与多个振动传感器共同耦合的控制器组件，以及耦合到可旋转构件的平衡组件，所述平衡组件配置成与所述控制器组件无线地连通所述平衡组件被配置为响应于从控制器组件无线传送的命令来修改可旋转构件的重量分布。控制器组件被配置为从多个振动传感器接收数据，并使用接收的数据确定可旋转构件的不平衡。

9. 发明授权

US07097720B2 Lower fluence boundary laser shock peening 有权
标题翻译：低能量密度边界激光冲击硬化
公开(公告)号：US07097720B2
公开(公告)日：2006-08-29
申请号：US10426816
申请日：2003-04-30
申请人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
发明人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
IPC分类号： C21D1/04 , C21D1/09 , C21D1/10
CPC分类号： F01D5/286 , C21D10/005
摘要： A method for laser shock peening an article including laser shock peening a first area with at least one high fluence laser beam and laser shock peening a border area between the first area and a non-laser shock peened area of the article with at least one first low fluence laser beam. The border area may be laser shock peened with a second low fluence laser beam or more low fluence laser beams wherein the second low fluence laser beam and others have a lower fluence than the first low fluence laser beam. The border area may be laser shock peened with progressively lower fluence laser beams starting with the one first fluence laser beam wherein the progressively lower fluence laser beams are in order of greatest fluence to least fluence in a direction outwardly from the first area through the border area to the non-laser shock peened area.
摘要翻译：一种用于激光冲击硬化处理物品的方法，所述方法包括用至少一个高注量激光束激光冲击第一区域的激光冲击，以及用所述第一区域和所述第一区域和所述第一区域之间的至少一个第一区域激光冲击所述第一区域和所述制品的非激光冲击硬化区域之间的边界区域低能量激光束。边界区域可以是用第二低注量激光束或更低的能量密度激光束进行激光冲击喷丸，其中第二低注量激光束和其它激光束具有比第一低注量激光束更低的能量密度。边界区域可以是激光冲击喷丸，其中以一个第一注量激光束开始逐渐降低的注量激光束，其中逐渐更低的注量激光束按照最小注量的顺序，在从第一区域通过边界区域向外的方向上的最小注量到非激光冲击硬化区域。

10. 发明授权

US09085989B2 Airfoils including compliant tip 有权
标题翻译：翼型包括合适的尖端
公开(公告)号：US09085989B2
公开(公告)日：2015-07-21
申请号：US13336001
申请日：2011-12-23
申请人： Pranav Dhoj Shah , Scott Roger Finn , Nicholas Joseph Kray , Ian Francis Prentice , Dong-Jin Shim , Bo Wang
发明人： Pranav Dhoj Shah , Scott Roger Finn , Nicholas Joseph Kray , Ian Francis Prentice , Dong-Jin Shim , Bo Wang
IPC分类号： F01D5/20 , F01D21/04
CPC分类号： F01D5/20 , F01D21/045 , F05D2300/43 , F05D2300/431 , F05D2300/432 , Y02T50/672 , Y02T50/673
摘要： An airfoil, a fan assembly and an engine include at least one airfoil including a root portion, a body portion and a tip portion. The body portion is configured extending radially outward from the root portion and the tip portion is configured extending radially outward from the root portion and the body portion. The airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil including a compliant tip at the tip portion. The compliant tip extending along at least a portion of the tip portion in a chord-wise direction and a span-wise direction. The compliant tip is configured to provide wave propagation along the tip portion such that critical strain proximate the tip portion and the trailing edge is reduced during a foreign object impact.
摘要翻译：翼型件，风扇组件和发动机包括至少一个包括根部，主体部分和顶端部分的翼型件。主体部分被配置为从根部径向向外延伸，并且尖端部分被构造成从根部部分和主体部分径向向外延伸。所述翼型件包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。所述翼型件在尖端部分包括柔性尖端。柔性尖端沿着顶端部分的至少一部分沿着弦向和跨度方向延伸。柔性尖端构造成沿着尖端部分提供波传播，使得在异物冲击期间，靠近尖端部分和后缘的临界应变减小。

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