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1. 发明申请

US20130302168A1 Embedded Actuators in Composite Airfoils 审中-公开
标题翻译：复合翼型嵌入式致动器
公开(公告)号：US20130302168A1
公开(公告)日：2013-11-14
申请号：US13466671
申请日：2012-05-08
申请人： Nicholas Joseph Kray , Ian Francis Prentice , Andrew Breeze-Stringfellow , Dong-Jin Shim , Gregory Carl Gemeinhardt
发明人： Nicholas Joseph Kray , Ian Francis Prentice , Andrew Breeze-Stringfellow , Dong-Jin Shim , Gregory Carl Gemeinhardt
IPC分类号： B63H1/06
CPC分类号： F01D5/141 , F05D2260/90 , F05D2300/505 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： An airfoil having active actuators and at least one morphing area allowing shape change of the airfoil and further allowing for optimization of the airfoil shape at more than one operating condition.
摘要翻译：具有主动致动器和至少一个变形区域的翼型件允许翼型的形状改变，并且还允许在多于一个操作条件下优化翼型形状。

2. 发明申请

US20130146217A1 Method of Applying Surface Riblets to an Aerodynamic Surface 审中-公开
标题翻译：将表面轮廓应用于空气动力学表面的方法
公开(公告)号：US20130146217A1
公开(公告)日：2013-06-13
申请号：US13315550
申请日：2011-12-09
申请人： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Dong-Jin Shim
发明人： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Dong-Jin Shim
IPC分类号： B31F1/20
CPC分类号： B64C21/10 , B64C2230/26 , F15D1/003 , F15D1/0085 , Y02T50/166 , Y10T156/1025
摘要： A method for applying texture to an aerodynamic surface is provided. A master plate is provided having a textured surface. A first material is then applied to that surface and cured forming a caul sheet with a negative impression of the master plate textured surface. A surface to which a texture is to be applied is then provided; this may be an aerodynamic surface. Another material, different from the first, is then applied to the aerodynamic surface and the caul sheet is placed on top. The second material is cured and the caul sheet is removed. The second material is adhered to the aerodynamic surface and has a surface that is substantially a negative impression of the caul sheet textured surface and substantially similar to the master plate textured surface.
摘要翻译：提供了将纹理应用于空气动力学表面的方法。提供具有纹理表面的主板。然后将第一材料施加到该表面并固化，形成具有主板纹理表面的负印象的铜版纸。然后提供要施加纹理的表面; 这可能是一个空气动力学表面。然后将与第一种不同的另一种材料施加到空气动力学表面上，并将盖板放置在顶部。第二种材料被固化并且去除了铜箔片。第二材料粘附到空气动力学表面上，并且具有基本上为铜版纸表面的负压印并且基本上类似于母板纹理表面的表面。

3. 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。

4. 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。

5. 发明授权

US08905719B2 Composite rotor and vane assemblies with integral airfoils 有权
标题翻译：具有整体翼型的复合转子和叶片组件
公开(公告)号：US08905719B2
公开(公告)日：2014-12-09
申请号：US13331418
申请日：2011-12-20
申请人： Nicholas Joseph Kray , Christopher Lee McAfee , Dong-Jin Shim
发明人： Nicholas Joseph Kray , Christopher Lee McAfee , Dong-Jin Shim
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , B29B11/16 , B29C70/48 , B29L2031/08 , F01D5/30 , F01D5/34 , F01D9/042 , F05D2300/6034 , Y02T50/672
摘要： A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter-clockwise airfoil segments may be stitched together.
摘要翻译：复合燃气涡轮发动机结构包括具有与保持环安装在一体并与径向远离保持环的翼型的保持环。保持环包括环形复合层，周向分段的翼型环，包括围绕保持环的外周和内周中的一个设置的翼型环段。翼型环段包括环形基座和在环形基座的顺时针和逆时针端部处的径向延伸的顺时针和逆时针的翼型段。复合翼型件包括沿周向相邻的顺时针和逆时针翼型段。围绕分段翼型环周向设置的流路外壳环流体流路外壳和保持环之间的环形基座。复合翼型翼型件延伸穿过流道外壳中的槽。层可以包裹在由连续的复合胶带制成的单个螺旋。槽可以是周向成角度的。沿顺时针方向和逆时针方向的翼型段可以缝合在一起。

6. 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。

7. 发明申请

US20150192023A1 Mechanical Interlock Feature for Multi-Material Airfoils 审中-公开
标题翻译：多材料翼型的机械联锁特性
公开(公告)号：US20150192023A1
公开(公告)日：2015-07-09
申请号：US13492130
申请日：2012-06-08
申请人： Nicholas Joseph Kray , Dong-Jin Shim , Pranav D. Shah
发明人： Nicholas Joseph Kray , Dong-Jin Shim , Pranav D. Shah
IPC分类号： F01D5/28 , F01D5/22 , F01D5/30
CPC分类号： F01D5/282 , F01D5/147 , F01D5/22 , F01D5/30 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2230/23 , F05D2260/36 , F05D2300/43 , F05D2300/6034 , Y02T50/672
摘要： An airfoil of a first parent material and a second wrap material wherein the parent and wrap materials are of at least partially different materials and wherein an interlock region is formed between the parent and wrap materials having an interlock feature.
摘要翻译：第一母材和第二包裹材料的翼型，其中母材和包裹材料是至少部分不同的材料，并且其中在具有互锁特征的母料和包装材料之间形成互锁区域。

8. 发明申请

US20130156592A1 FAN BLADE WITH COMPOSITE CORE AND WAVY WALL TRAILING EDGE CLADDING 有权
标题翻译：风扇叶片与复合核心和波纹墙拖车边缘
公开(公告)号：US20130156592A1
公开(公告)日：2013-06-20
申请号：US13331301
申请日：2011-12-20
申请人： Nicholas Joseph Kray , Daniel Edward Mollmann , Dong-Jin Shim , Trevor Howard Wood
发明人： Nicholas Joseph Kray , Daniel Edward Mollmann , Dong-Jin Shim , Trevor Howard Wood
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , F01D5/141 , F05D2220/36 , F05D2240/304 , F05D2250/184 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
摘要翻译：燃气涡轮发动机翼型包括前缘和后缘，压力和吸力侧从翼型基部延伸到翼面，由复合材料复合芯结合的包层材料制成的后缘包层，比复合材料脆的包层材料，复合芯包括中心芯部分延伸到复合芯的前缘部分到后缘部分的下游，以及包括波浪壁和后缘的后缘包层。后缘包层的压力和吸力侧面可以结合到后缘部分的压力和吸力侧表面。波浪形波浪的波浪可以垂直于和远离压力和吸力侧表面延伸。后缘包层可能包括波浪压力和吸力侧后缘护罩，包括波浪形波浪。翼型件可以从叶片的平台向外延伸。根可以包括整体的燕尾。

9. 发明授权

US09121294B2 Fan blade with composite core and wavy wall trailing edge cladding 有权
标题翻译：风扇叶片与复合芯和波浪形墙后缘包层
公开(公告)号：US09121294B2
公开(公告)日：2015-09-01
申请号：US13331301
申请日：2011-12-20
申请人： Nicholas Joseph Kray , Daniel Edward Mollmann , Dong-Jin Shim , Trevor Howard Wood
发明人： Nicholas Joseph Kray , Daniel Edward Mollmann , Dong-Jin Shim , Trevor Howard Wood
IPC分类号： F01D5/28 , F01D5/14
CPC分类号： F01D5/282 , F01D5/141 , F05D2220/36 , F05D2240/304 , F05D2250/184 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
摘要翻译：燃气涡轮发动机翼型包括前缘和后缘，压力和吸力侧从翼型基部延伸到翼面，由复合材料复合芯结合的包层材料制成的后缘包层，比复合材料脆的包层材料，复合芯包括中心芯部分延伸到复合芯的前缘部分到后缘部分的下游，以及包括波浪壁和后缘的后缘包层。后缘包层的压力和吸力侧面可以结合到后缘部分的压力和吸力侧表面。波浪形波浪的波浪可以垂直于和远离压力和吸力侧表面延伸。后缘包层可能包括波浪压力和吸力侧后缘护罩，包括波浪形波浪。翼型件可以从叶片的平台向外延伸。根可以包括整体的燕尾。

10. 发明申请

US20130330496A1 COMPOSITE STRUCTURE WITH LOW DENSITY CORE AND COMPOSITE STITCHING REINFORCEMENT 审中-公开
标题翻译：具有低密度芯和复合结构加固的复合结构
公开(公告)号：US20130330496A1
公开(公告)日：2013-12-12
申请号：US13490235
申请日：2012-06-06
申请人： Nicholas Joseph Kray , Wendy Wen-Ling Lin , Dong-Jin Shim , Ross Spoonire
发明人： Nicholas Joseph Kray , Wendy Wen-Ling Lin , Dong-Jin Shim , Ross Spoonire
IPC分类号： B32B7/08 , B63H1/26 , B32B38/00
CPC分类号： B29C70/08 , B29C70/086 , B29C70/24 , B29C70/865 , B29K2063/00 , B29K2307/04 , B29L2031/08 , B32B5/06 , Y10T428/233 , Y10T428/239
摘要： A composite structure includes: a core having a pair of opposed exterior surfaces and having a first density; a composite layup surrounding the core, the composite layup comprising a plurality of layers of fibers embedded in a matrix and extending along the exterior surfaces of the core, the composite layup having a second density; and stitching comprising fibers extending through the core and at least a portion of the composite layup.
摘要翻译：复合结构包括：具有一对相对的外表面并具有第一密度的芯; 所述复合叠层包括嵌入在基体中并沿所述芯的外表面延伸的多个纤维层，所述复合叠层具有第二密度; 以及缝合，其包括延伸通过所述芯的纤维和所述复合叠层的至少一部分。

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