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1. 发明申请

US20090142181A1 Gas Turbine Engine Systems Involving Mechanically Alterable Vane Throat Areas 有权
标题翻译：燃气轮机发动机系统涉及机械可变叶片喉区
公开(公告)号：US20090142181A1
公开(公告)日：2009-06-04
申请号：US11947160
申请日：2007-11-29
申请人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
发明人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D9/02 , F05D2270/17
摘要： Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.
摘要翻译：提供涉及可机械地改变的叶片喉部区域的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性叶片包括：前缘; 后缘吸引侧表面，其在前缘和后缘之间延伸; 空腔，其具有位于所述吸力侧表面中的孔; 以及位于腔体内且可在其中移动的筒体，使得筒体的移动改变了筒体穿过该孔突出的程度。

2. 发明申请

US20090148282A1 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT 有权
标题翻译：用于可变区域涡轮风扇装置的3D轮廓端板
公开(公告)号：US20090148282A1
公开(公告)日：2009-06-11
申请号：US11953478
申请日：2007-12-10
申请人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
发明人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
IPC分类号： F01D1/02
CPC分类号： F01D17/162 , F02C9/22
摘要： A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.
摘要翻译：燃气涡轮发动机的涡轮机部分包括具有基本上平坦的表面的弧形叶片平台段，旋转涡轮叶片可绕其旋转。

3. 发明授权

US08105019B2 3D contoured vane endwall for variable area turbine vane arrangement 有权
标题翻译：用于可变区域涡轮叶片布置的3D轮廓叶片端壁
公开(公告)号：US08105019B2
公开(公告)日：2012-01-31
申请号：US11953478
申请日：2007-12-10
申请人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
发明人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
IPC分类号： F01D9/02
CPC分类号： F01D17/162 , F02C9/22
摘要： A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.
摘要翻译：燃气涡轮发动机的涡轮机部分包括具有基本上平坦的表面的弧形叶片平台段，旋转涡轮叶片可绕其旋转。

4. 发明授权

US09447696B2 Blade outer air seal system for controlled tip clearance 有权
标题翻译：叶片外部空气密封系统，用于控制尖端间隙
公开(公告)号：US09447696B2
公开(公告)日：2016-09-20
申请号：US13727798
申请日：2012-12-27
申请人： Michael G. McCaffrey , Brandon T. Rouse , Thomas Almy , Igor S. Garcia , John R. Farris , Mark Borja
发明人： Michael G. McCaffrey , Brandon T. Rouse , Thomas Almy , Igor S. Garcia , John R. Farris , Mark Borja
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F05D2240/11 , F05D2300/50212 , Y02T50/671
摘要： A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.
摘要翻译：用于燃气涡轮发动机的叶片外部空气密封系统包括由具有第一热膨胀系数的第一材料制成的多个环形载体。多个密封段分别承载在多个环形载体上。在多个环形载体中承载环构件。环构件由与组成中的第一材料不同的第二材料制成。第二材料具有第二热膨胀系数，使得第一热膨胀系数为第二热膨胀系数的75-175％。

5. 发明授权

US09376916B2 Assembled blade platform 有权
标题翻译：组装刀片平台
公开(公告)号：US09376916B2
公开(公告)日：2016-06-28
申请号：US13488968
申请日：2012-06-05
申请人： Michael G. McCaffrey , Gregory H. Hasko , Michael G. Abbott
发明人： Michael G. McCaffrey , Gregory H. Hasko , Michael G. Abbott
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , C04B37/001 , C04B2237/365 , C04B2237/38 , C04B2237/61 , C04B2237/84 , Y10T29/49336
摘要： A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil.
摘要翻译：制造刀片平台的方法包括以下步骤：通过将模具中的织物固化在模具中并将织物带围绕两个平台部分定位以保持翼型件并限定刀片来创建两个平台部分。该方法还包括通过固化材料以限定固体材料的平台将两个平台部分结合在一起的步骤。该平台不与翼型结合。

6. 发明授权

US09212560B2 CMC blade with integral 3D woven platform 有权
标题翻译： CMC刀片与整体3D编织平台
公开(公告)号：US09212560B2
公开(公告)日：2015-12-15
申请号：US13173308
申请日：2011-06-30
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： C03B29/00 , D04H13/00 , B29C65/00 , B32B37/00 , B32B38/10 , B21K25/00 , B23P15/04 , B63H1/26 , B63H7/02 , B64C11/24 , B64C27/46 , F01D5/18 , F03B3/12 , F03B7/00 , F03D11/02 , F04D29/38 , B64C11/16 , F01D5/14 , F01D5/28 , C04B37/00 , B32B18/00 , B29C65/56 , B29C65/48
CPC分类号： F01D5/282 , B29C65/006 , B29C65/48 , B29C65/565 , B32B18/00 , C04B37/003 , C04B2235/5224 , C04B2235/524 , C04B2235/5244 , C04B2235/5248 , C04B2237/16 , C04B2237/341 , C04B2237/343 , C04B2237/348 , C04B2237/36 , C04B2237/365 , C04B2237/366 , C04B2237/368 , C04B2237/38 , C04B2237/61 , C04B2237/76 , C04B2237/86 , F01D5/147 , F01D5/28 , F01D5/284 , F05D2220/32 , F05D2240/30 , F05D2300/6012 , F05D2300/6033 , Y10T29/49316
摘要： A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.
摘要翻译：一种形成燃气涡轮发动机中使用的部件的方法包括形成翼型件/根部组件的步骤; 创建具有开口的平台组装结构; 将翼型件/根组件插入开口中; 以及将平台组件结构粘合到翼型件/根组件以形成部件。

7. 发明授权

US08562285B2 Angled on-board injector 有权
标题翻译：有角度的车载进样器
公开(公告)号：US08562285B2
公开(公告)日：2013-10-22
申请号：US11772335
申请日：2007-07-02
申请人： Michael G. McCaffrey , Joseph T. Caprario , George E. Allen , Christopher Moore , Ronald R. Gagnon
发明人： Michael G. McCaffrey , Joseph T. Caprario , George E. Allen , Christopher Moore , Ronald R. Gagnon
IPC分类号： F01D25/12 , F01D9/06
CPC分类号： F01D5/081 , F01D5/082 , F02C7/28 , F05D2240/56 , F05D2250/314 , F05D2260/60
摘要： A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an engine centerline to communicate cooling airflow to an angled annular section of a turbine rotor disk coverplate.
摘要翻译：二次流系统为涡轮机叶片提供紧凑的喷射器冷却结构，其包括倾斜的板上喷射器（AOBI），其将计量喉部相对于发动机中心线以向内的角度定位。 AOBI将计量喉部相对于发动机中心线以向内的角度定位，以将冷却气流传递到涡轮转子盘盖板的成角度的环形部分。

8. 发明申请

US20130022469A1 Turbine Rotor Non-Metallic Blade Attachment 有权
标题翻译：涡轮转子非金属刀片附件
公开(公告)号：US20130022469A1
公开(公告)日：2013-01-24
申请号：US13184736
申请日：2011-07-18
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/284 , F01D5/3084 , F05D2230/22 , F05D2300/6033
摘要： In an engine disk and blade combination, the metallic disk has a plurality of first blade attachment slots and a plurality of second blade attachment slots circumferentially interspersed with each other. There is a circumferential array of a plurality of first blades. Each first blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said first attachment slots. There is a circumferential array of second blades. Each second blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said second slots. The first blades and second blades are non-metallic. The first blades are radially longer than the second blades. The first slots are radially deeper than the second slots.
摘要翻译：在发动机盘和刀片组合中，金属盘具有多个第一刀片附接槽和多个第二刀片附接槽，其周向地彼此散布。存在多个第一叶片的圆周阵列。每个第一叶片具有翼型件和附接根部。附件根分别接收在相关联的所述第一附接槽中。有第二个叶片的圆周阵列。每个第二叶片具有翼型件和附接根部。附着根分别接收在相关联的所述第二槽中。第一个叶片和第二个叶片是非金属的。第一叶片比第二叶片径向长。第一槽比第二槽径向更深。

9. 发明申请

US20130004326A1 CMC BLADE WITH INTEGRAL 3D WOVEN PLATFORM 有权
标题翻译： CMC叶片与整体三维平铺
公开(公告)号：US20130004326A1
公开(公告)日：2013-01-03
申请号：US13173308
申请日：2011-06-30
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D5/14 , B32B38/10 , B32B37/02
CPC分类号： F01D5/282 , B29C65/006 , B29C65/48 , B29C65/565 , B32B18/00 , C04B37/003 , C04B2235/5224 , C04B2235/524 , C04B2235/5244 , C04B2235/5248 , C04B2237/16 , C04B2237/341 , C04B2237/343 , C04B2237/348 , C04B2237/36 , C04B2237/365 , C04B2237/366 , C04B2237/368 , C04B2237/38 , C04B2237/61 , C04B2237/76 , C04B2237/86 , F01D5/147 , F01D5/28 , F01D5/284 , F05D2220/32 , F05D2240/30 , F05D2300/6012 , F05D2300/6033 , Y10T29/49316
摘要： A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.
摘要翻译：一种形成燃气涡轮发动机中使用的部件的方法包括形成翼型件/根部组件的步骤; 创建具有开口的平台组装结构; 将翼型件/根组件插入开口中; 以及将平台组件结构粘合到翼型件/根组件以形成部件。

10. 发明授权

US08007229B2 Variable area turbine vane arrangement 有权
标题翻译：可变区域涡轮叶片装置
公开(公告)号：US08007229B2
公开(公告)日：2011-08-30
申请号：US12778084
申请日：2010-05-11
申请人： Michael G. McCaffrey , John R. Farris , Eric A. Hudson , George T. Suljak, Jr.
发明人： Michael G. McCaffrey , John R. Farris , Eric A. Hudson , George T. Suljak, Jr.
IPC分类号： F01D17/16
CPC分类号： F01D9/041 , F01D17/162 , F04D29/563 , F05D2240/40 , F05D2250/411 , Y10T29/49323
摘要： A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的环形叶片喷嘴包括在内部叶片环和外部叶片环之间的多个固定涡轮叶片和在内部叶片环和外部叶片环之间的多个旋转涡轮叶片叶片环，每个旋转涡轮叶片可围绕旋转轴线旋转。

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