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1. 发明专利

JP2013013995A Method for roughening metal surface and article manufactured thereby 有权
标题翻译：金属表面粗糙化方法及其制造方法
公开(公告)号：JP2013013995A
公开(公告)日：2013-01-24
申请号：JP2012143960
申请日：2012-06-27
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： TRIMMER ANDREW LEE , WEI BIN , MILLER JOSHUA LEIGH , KRAY NICHOLAS JOSEPH , LAMPHERE MICHAEL SCOTT
IPC分类号： B23H3/04 , B23H9/00 , C25F3/00
CPC分类号： C25F7/00 , B23H3/00 , B23H9/008 , B23H9/10 , C25F3/02 , C25F3/08
摘要： PROBLEM TO BE SOLVED: To provide an improved technique for roughening a metal surface.SOLUTION: A method for surface roughening a metal workpiece includes a step of disposing a region of the workpiece to be roughened proximate to a counter electrode. The region of the workpiece to be roughened and the counter electrode are then disposed together in an electrolyte. An electric potential with current flow is applied between the work piece and the counter electrode to roughen the metal surface to a desired roughness. The counter electrode may include a stainless steel mesh, copper mesh, brass mesh, bronze mesh, gold mesh, platinum mesh, titanium mesh, or a combination thereof.
摘要翻译：要解决的问题：提供一种用于使金属表面粗糙化的改进技术。解决方案：用于金属工件的表面粗糙化的方法包括将待粗糙化的工件的区域设置在靠近对电极的步骤。然后将待粗化的工件的区域和对电极一起放置在电解质中。在工件和对电极之间施加具有电流的电势，以将金属表面粗糙化成所需的粗糙度。对电极可以包括不锈钢网，铜网，黄铜网，青铜网，金网，铂网，钛网或其组合。版权所有（C）2013，JPO＆INPIT

2. 发明专利

JP2013256946A Mechanical interlock for multi-material airfoil 审中-公开
标题翻译：多材料空气动力学的机械互锁
公开(公告)号：JP2013256946A
公开(公告)日：2013-12-26
申请号：JP2013119359
申请日：2013-06-06
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KRAY NICHOLAS JOSEPH , SHAH PRANAV D , SHIM DONG-JIN
IPC分类号： F01D5/28 , F01D5/14 , F02C7/00
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： PROBLEM TO BE SOLVED: To provide a mechanical interlock for a multi-material airfoil.SOLUTION: A mechanical interlock includes: a first airfoil portion (34) which can be connected to a rotor disk (32); and a second airfoil portion (36) connected to an interlock feature of the first airfoil portion. The first airfoil portion is formed with a first material and can have the interlock feature (52) extended therefrom. The second airfoil portion radially extends from the first air foil portion, and can be formed with at least partially different materials.
摘要翻译：要解决的问题：为多材料翼型提供机械互锁。解决方案：机械互锁包括：可连接到转子盘（32）的第一翼型部分（34）; 以及连接到第一翼型部分的互锁特征的第二翼型部分（36）。第一翼型部分形成有第一材料并且可以具有从其延伸的互锁特征（52）。第二翼型部分从第一气翼部分径向延伸，并且可以形成有至少部分不同的材料。

3. 发明专利

JP2010121624A Fiber composite reinforced aircraft gas turbine engine drum with radially inwardly extending blade 有权
标题翻译：纤维复合增强型飞机气动涡轮发动机，带有径向延伸的叶片
公开(公告)号：JP2010121624A
公开(公告)日：2010-06-03
申请号：JP2009263441
申请日：2009-11-19
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SCHILLING JAN CHRISTOPHER , KRAY NICHOLAS JOSEPH
IPC分类号： F04D29/32 , F01D5/06 , F01D25/00 , F02C3/067 , F02C7/00
CPC分类号： F01D5/03 , F01D5/06 , F02K3/072 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a rotatable drum with lightweight and robust inwardly extending blades. SOLUTION: A gas turbine engine assembly 2 includes blade rows 48, 50, and 52 having blades 17 radially inwardly extending from the rotatable drum 46, and composite fiber material rings 72 arranged in a peripheral direction around the rotatable drum 46. The composite fiber material rings include high-strength fibers 73 or filaments extending in the circumferential direction. The rings can be axially aligned with the blade rows. Ring widths of the rings can be smaller than blade widths at blade bases of the blades at a radially inner surface of the drum 46. The ring can be made of a material including reinforced structural fibers or filaments disposed in an integral matrix and extending in a plurality of circumferential directions. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供具有重量轻且坚固的向内延伸的叶片的可旋转滚筒。解决方案：燃气涡轮发动机组件2包括具有从可旋转鼓46径向向内延伸的叶片17的叶片排48,50以及围绕可旋转滚筒46沿圆周方向布置的复合纤维材料环72。复合纤维材料环包括在周向延伸的高强度纤维73或长丝。环可以与叶片排轴向对准。环的环宽度可以小于在鼓46的径向内表面处的叶片的叶片基部处的叶片宽度。环可以由包括加强结构纤维或细丝的材料制成，所述增强结构纤维或细丝设置在整体基质中并在多个圆周方向。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2013164590A Acoustic panel and method of forming the same 审中-公开
标题翻译：声学面板及其形成方法
公开(公告)号：JP2013164590A
公开(公告)日：2013-08-22
申请号：JP2013022781
申请日：2013-02-08
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KRAY NICHOLAS JOSEPH , SETH ALEXANDER MCDONALD , BENJAMIN ROBY
IPC分类号： G10K11/172
CPC分类号： F02C7/24 , Y02T50/672
摘要： PROBLEM TO BE SOLVED: To provide components to fix an acoustic panel.SOLUTION: A disclosed embodiment provides an acoustic panel having a composite laminate panel having a back sheet layer, a face sheet layer, and a core layer disposed therebetween. The core layer has one or more depressions at an interface between the core layer and the face sheet layer, with the face sheet having a generally uniform thickness across the composite laminate panel. A hole extends through the composite laminate panel at the depressions, and a bolt assembly extends through the hole such that it is countersunk.
摘要翻译：要解决的问题：提供用于固定声学面板的部件。解决方案：所公开的实施例提供一种具有复合层压板的声学面板，所述复合层压板具有背板层，表面层和设置在其间的芯层。芯层在芯层和面片层之间的界面处具有一个或多个凹陷，其中该面片在复合层压板上具有大致均匀的厚度。孔在凹部处延伸穿过复合层压板，并且螺栓组件延伸穿过孔，使得其被埋入。

5. 发明专利

JP2013137021A Airfoil including compliant tip 审中-公开
标题翻译：航空包括合规提示
公开(公告)号：JP2013137021A
公开(公告)日：2013-07-11
申请号：JP2012272909
申请日：2012-12-14
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： SHAH PRANAV DHOJ , FINN SCOTT ROGER , KRAY NICHOLAS JOSEPH , PRENTICE IAN FRANCIS , SHIM DONG JIN , WANG BO
IPC分类号： F04D29/32 , F01D5/14 , F01D5/28 , F02K3/06 , F02K3/065 , F02K3/072
CPC分类号： F01D5/20 , F01D21/045 , F05D2300/43 , F05D2300/431 , F05D2300/432 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a fan blade that is resistant to airfoil surface strains produced during foreign object impacts.SOLUTION: The body portion 105 is configured extending radially outward from the root portion 106 and the tip portion 118 is configured extending radially outward from the root portion 106 and the body portion 105. The airfoil 102 includes a compliant tip 120 at the tip portion 118. The compliant tip 120 extends along at least a portion of the tip portion 118 in a chord-wise direction and a span-wise direction. The compliant tip 120 is configured to provide wave propagation along the tip portion 118 such that critical strain proximate the tip portion 118 and the trailing edge 116 is reduced during the foreign object impact.
摘要翻译：要解决的问题：提供一种能够抵抗在异物冲击期间产生的翼面表面应变的风扇叶片。解决方案：主体部分105构造成从根部106径向向外延伸，并且顶端部分118构造成从根部106和主体部分105.翼型件102在尖端部分118处包括柔性尖端120.柔性尖端120沿着顶端部分118的至少一部分沿弦向方向和跨度方向延伸方向。柔性尖端120被配置为沿着尖端部分118提供波传播，使得在外来物体撞击期间，靠近尖端部分118和后缘116的临界应变减小。

6. 发明专利

JP2013044328A Metal fan blade platform 有权
标题翻译：金属风扇叶片平台
公开(公告)号：JP2013044328A
公开(公告)日：2013-03-04
申请号：JP2012180696
申请日：2012-08-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KRAY NICHOLAS JOSEPH , PLATZ JR GREGORY ALLEN , HASTINGS MATTHEW ROBERT , BRYANT JR GARY WILLARD , KRAL JUSTIN JEFFREY
IPC分类号： F02K3/06 , F01D25/00 , F02C7/00
CPC分类号： F04D29/321 , F01D5/3007 , F01D11/008 , F04D29/644 , F05D2220/36 , F05D2240/80 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide an inexpensive fan platform which does not restrict a rotation capacity of an adjacent fan blade, and is small and is easy to manufacture.SOLUTION: The platform 34 is arranged to be used between the adjacent fan blades 18 joined to a rotor disk and provide an inner side flow passage boundary. The platform 34 includes: a metal arched body having opposing front end and rear end and opposite lateral edge parts; and a pair of fragile wings extending from the lateral edge parts in a lateral direction over the body in a radial direction.
摘要翻译：要解决的问题：提供不限制相邻风扇叶片的旋转能力的廉价的风扇平台，并且小且易于制造。解决方案：平台34布置成在与转子盘接合的相邻风扇叶片18之间使用，并提供内侧流动通道边界。平台34包括：金属拱形体，其具有相对的前端和后端以及相对的侧边缘部分; 以及一对脆弱的翼片，其沿着横向方向从横向边缘部分沿径向方向延伸到身体上。版权所有（C）2013，JPO＆INPIT

7. 发明专利

JP2012026448A Components with bonded edges 审中-公开
标题翻译：具有粘合边缘的组件
公开(公告)号：JP2012026448A
公开(公告)日：2012-02-09
申请号：JP2011160822
申请日：2011-07-22
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KRAY NICHOLAS JOSEPH , MILLER JOSHUA LEIGH , DAVIS TOD WINTON , SCHUMACHER PETER CHRISTOPHER , KELLEY JOHN ROBERT
IPC分类号： F04D29/38 , F02C3/073 , F02C7/00 , F02K3/06
CPC分类号： F04D29/324 , B23P15/04 , F01D5/28 , F04D29/023 , F05D2230/23 , F05D2240/303 , F05D2300/10 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T428/12403
摘要： PROBLEM TO BE SOLVED: To provide a component having a bonded metallic edge used in a gas turbine engine and a method of manufacturing such component.SOLUTION: A metallic sheath (10) for mounting on a component is disclosed. The metallic sheath comprises a nose portion (160) extending in a chordwise direction (5), a first side-wall extending in the chordwise direction from the nose portion, and a second side-wall (166) extending in the chordwise direction from the nose portion (160). The second side-wall (162) is bonded to the nose portion (160) such that the nose portion (160), the first side-wall (166) and the second side-wall (162) form a cavity (164) capable of receiving a portion of the component.
摘要翻译：要解决的问题：提供一种在燃气涡轮发动机中使用的具有接合金属边缘的部件和制造这种部件的方法。公开了一种用于安装在部件上的金属护套（10）。金属护套包括沿弦向（5）延伸的鼻部（160），从鼻部向弦方向延伸的第一侧壁和沿着弦状方向延伸的第二侧壁（166）鼻部（160）。第二侧壁（162）结合到鼻部（160），使得鼻部（160），第一侧壁（166）和第二侧壁（162）形成能够形成的空腔（164）接收部件的一部分。版权所有（C）2012，JPO＆INPIT

8. 发明专利

JP2010276604A Non-destructive inspection system having self-aligning probe assembly 有权
标题翻译：具有自我校准探头组件的非破坏性检查系统
公开(公告)号：JP2010276604A
公开(公告)日：2010-12-09
申请号：JP2010117920
申请日：2010-05-24
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： LEE BYUNGWOO , WU YANYAN , KRAY NICHOLAS JOSEPH
IPC分类号： G01N29/26 , G01N27/90
CPC分类号： G01B21/20 , G01N21/9515
摘要： PROBLEM TO BE SOLVED: To cause sensors to contact and to be substantially normal or perpendicular to the surfaces of structures to be inspected in order to improve inspection accuracy.
SOLUTION: An inspection system (10) includes: a sensor (16) configured to obtain inspection data of an object; a motion control device (11); a joint assembly (12) coupled to the motion control device (11); and a probe housing (13) coupled to the joint assembly (12) and configured to hold the sensor (16). The inspection system (10) further includes a compliant element (14) coupled to the probe housing (13) and configured to cooperate with the joint assembly (12) and the motion control device (11) to position the sensor (16) relative to the object. A self-aligning probe assembly is also presented.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提高检测精度，使传感器接触并且基本正常或垂直于要检查的结构的表面。检测系统（10）包括：传感器（16），被配置为获得物体的检查数据; 运动控制装置（11）; 耦合到运动控制装置（11）的联合组件（12）; 以及联接到所述接头组件（12）并被配置为保持所述传感器（16）的探针壳体（13）。检查系统（10）还包括联接到探针壳体（13）并被配置为与接头组件（12）和运动控制装置（11）协作以将传感器（16）相对于物体。还提出了自对准探针组件。版权所有（C）2011，JPO＆INPIT

9. 发明专利

JP2004138069A Method and device for promoting breakage prevention of gas turbine engine blade 审中-公开
标题翻译：用于促进气体涡轮发动机叶片的破坏的方法和装置
公开(公告)号：JP2004138069A
公开(公告)日：2004-05-13
申请号：JP2003357150
申请日：2003-10-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINHA SUNIL KUMAR , FARSON MAX ROBERT , LI MING CHENG , IZON PAUL , KRAY NICHOLAS JOSEPH
IPC分类号： F01D5/30 , F01D5/32 , F04D29/34
CPC分类号： F01D5/3007 , F05D2230/00 , F05D2250/70 , F05D2260/94 , F05D2260/941 , Y10T29/49321
摘要： PROBLEM TO BE SOLVED: To provide a method and a device for promoting breakage prevention of gas turbine engine blades. SOLUTION: A rotor assembly (12) of a gas turbine engine (10) is manufactured. The method includes a wing-shaped portion (50) extending from an integrated dovetail (52), and a blade (30) fitted by using the dovetail is formed in the rotor assembly. A projecting portion (94) extends from at least a part of the blade, and breakage of the blade is prevented by keeping the stress exerted in at least a part (86) of the blade to be lower than a predetermined threshold for breakage of the blade. COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：提供一种用于促进燃气轮机发动机叶片的破坏预防的方法和装置。解决方案：制造燃气涡轮发动机（10）的转子组件（12）。该方法包括从集成的燕尾（52）延伸的翼形部分（50），并且在转子组件中形成通过使用燕尾形装配的叶片（30）。突出部分（94）从叶片的至少一部分延伸，并且通过将施加在叶片的至少一部分（86）中的应力保持在低于预定阈值以下的方式来防止叶片的断裂刀。版权所有（C）2004，JPO

10. 发明专利

JP2017089640A エネルギー吸収エッジガードを有する翼形部审中-公开
公开(公告)号：JP2017089640A
公开(公告)日：2017-05-25
申请号：JP2016214745
申请日：2016-11-02
申请人：ゼネラル・エレクトリック・カンパニイ , General Electric Co
发明人： KRAY NICHOLAS JOSEPH , ALBRECHT RICHARD WILLIAM JR
IPC分类号： F01D5/16 , F01D5/28
CPC分类号： F01D5/16 , B64C11/205 , B64C11/24 , B64C11/26 , B64C27/473 , F01D5/147 , F01D5/288 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2250/231 , Y02E10/721 , Y02T50/672 , Y02T50/673
摘要：【課題】従来の方法で製造でき、単純な形状を有するエッジガード装置を提供する。【解決手段】翼形部用のエッジガード装置(30)は、ノーズ(36)を有する本体(32)であって、ノーズ(36)から延在する離隔した第1のウィング(38)及び第2のウィング(40)を有し、第1のウィング(38)と第2のウィング(40)の間に空洞(44)を画成する本体(32)と、空洞(44)内に配置されているエネルギー吸収構造(34)とを備える。【選択図】図2

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