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公开(公告)号：US09802288B2
公开(公告)日：2017-10-31
申请号：US14741056
申请日：2015-06-16
IPC分类号： B24B19/14 , B24B19/26 , B24B49/12 , B24B49/16 , B24B49/14 , F01D5/14 , B24B17/00 , B24B19/00 , B24B27/00 , B25J11/00 , F01D5/00
CPC分类号： B24B19/14 , B24B17/00 , B24B19/009 , B24B19/26 , B24B27/0038 , B24B49/12 , B24B49/14 , B24B49/16 , B25J11/0065 , F01D5/005 , F01D5/141 , F05D2220/32 , F05D2230/14 , Y02T50/673
摘要： An abrasive profiling tool that may be part of a robotic machining system for machining a trailing edge of an airfoil, includes a shank extending along a rotational axis, a bearing guide rotationally secured to a distal end of the shank for riding upon the airfoil; and an abrasive profiler projecting radially and rigidly outward from the shank for grinding at least the trailing edge as the shank rotates. The profiler may include a round-over portion for grinding the trailing edge and a chamfered blending portion for grinding adjacent surfaces of the airfoil to produce a smooth transition from the adjacent surfaces and to the trailing edge.
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公开(公告)号：US20160003477A1
公开(公告)日：2016-01-07
申请号：US14790970
申请日：2015-07-02
发明人： Tracy A. Propheter-Hinckley , Dominic J. Mongillo , Joel H. Wagner , Mark F. Zelesky , Stanislav Kostka , Timothy S. Snyder
CPC分类号： F23R3/06 , F23R3/002 , F23R3/005 , F23R2900/00019 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.
摘要翻译： 可以用于燃气涡轮发动机的燃烧器的自冷却孔结构，并且还可以是稀释孔结构，包括热侧板，与热侧板间隔开的冷侧板，以及连续的内壁，其延伸 在热和冷侧板之间并且限定具有中心线并且轴向地通过热和冷侧板的孔口。 该结构的多个端壁位于由冷热侧板和内壁部分限定的冷却腔中。 每个端壁在热侧面板和冷侧面板之间延伸并与之接合，并与下一个相邻的端壁沿圆周间隔开。 多个入口孔延伸穿过冷侧面板并且与空腔流体连通，并且多个入口孔中的每一个靠近多个端壁中的相应一个的第一侧。 多个出口孔延伸穿过热侧面板并且与空腔流体连通，并且多个出口孔中的每一个与多个端壁中的相应一个端壁的相对的第二侧相关联。
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公开(公告)号：US20150345302A1
公开(公告)日：2015-12-03
申请号：US14706045
申请日：2015-05-07
发明人： Michael J. Birnkrant , Dominic J. Mongillo, JR. , Joel H. Wagner , Weina Li , Jose L. Santana , Carey Clum , James T. Beals
IPC分类号： F01D5/18
CPC分类号： F01D5/183 , C04B35/01 , C04B35/10 , C04B35/453 , C04B35/56 , C04B35/565 , C04B35/58 , C04B35/58085 , C04B38/00 , C04B38/0054 , C04B38/0074 , C04B2111/00982 , C04B2111/763 , F05D2260/203 , F05D2300/10 , F05D2300/20 , F05D2300/514 , F05D2300/612 , Y02T50/676 , C04B38/0045
摘要： A transpiration-cooled article includes a body wall that has first and second opposed surfaces. The first surface is adjacent a passage that is configured to receive a pressurized cooling fluid. At least a portion of the body wall includes a nanocellular foam through which the pressurized cooling fluid from the passage can flow to the second surface. The article can be an airfoil that includes an airfoil body that has an internal passage and an outer gas-path surface. At least a portion of the airfoil body includes a nanocellular foam through which cooling fluid from the internal passage can flow to the gas-path surface.
摘要翻译： 蒸发冷却制品包括具有第一和第二相对表面的主体壁。 第一表面邻近经配置以接收加压冷却流体的通道。 体壁的至少一部分包括纳米细胞泡沫，来自通道的加压冷却流体可以通过该泡沫泡沫流到第二表面。 该制品可以是包括具有内部通道和外部气体路径表面的翼型件的翼型件。 翼型体的至少一部分包括纳米孔泡沫，通过该纳米孔泡沫，来自内部通道的冷却流体可通过其流到气体路径表面。
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公开(公告)号：US20150160097A1
公开(公告)日：2015-06-11
申请号：US14564774
申请日：2014-12-09
CPC分类号： G01J5/0088 , F01D5/284 , F01D5/288 , F01D21/003 , F01D21/12 , F05D2260/80 , G01J5/0022 , G01J5/0066 , G01J2005/0077
摘要： A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.
摘要翻译： 一种系统包括具有一个或多个检查端口的涡轮机。 LWIR传感器位于涡轮机的检查口中，以感测涡轮机组件发出的热能。 成像装置可以可操作地连接到LWIR传感器，以基于感测的热能将来自LWIR传感器的信号转换成涡轮机组件的热图像。 在一些实施例中，LWIR传感器被配置成对陶瓷涂覆的涡轮叶片进行成像。
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公开(公告)号：US20210003485A1
公开(公告)日：2021-01-07
申请号：US16502242
申请日：2019-07-03
发明人： Joel H. Wagner , Kevin W. Schlichting , Michael Joseph Murphy , Steven H. Zysman , Nigel David Sawyers-Abbott , Andrew A. Consiglio , Charles Waldo Haldeman, IV
IPC分类号： G01N1/22 , G01N23/223
摘要： An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.
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公开(公告)号：US20200086380A1
公开(公告)日：2020-03-19
申请号：US16131695
申请日：2018-09-14
发明人： John Paulus , Dustin W. Davis , Joel H. Wagner
摘要： A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.
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公开(公告)号：US10450960B2
公开(公告)日：2019-10-22
申请号：US14860167
申请日：2015-09-21
发明人： Mark F. Zelesky , Joel H. Wagner , Shayan Ahmadian
摘要： A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.
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公开(公告)号：US10392968B2
公开(公告)日：2019-08-27
申请号：US15495283
申请日：2017-04-24
发明人： Ram Ranjan , James D. Hill , Glenn Levasseur , Joel H. Wagner
摘要： A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.
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公开(公告)号：US10156359B2
公开(公告)日：2018-12-18
申请号：US14655059
申请日：2013-03-15
发明人： Mark F. Zelesky , Joel H. Wagner , Tracy A. Propheter-Hinckley , Michael F. Blair , Thomas N. Slavens , Dominic J. Mongillo
IPC分类号： F23R3/00 , F01D25/12 , F01D11/08 , F01D25/24 , F02C7/18 , F01D5/18 , B33Y10/00 , B33Y70/00 , B33Y80/00
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
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公开(公告)号：US10101029B2
公开(公告)日：2018-10-16
申请号：US14673622
申请日：2015-03-30
发明人： Tracy A. Propheter-Hinckley , Dominic J. Mongillo , Mark F. Zelesky , Joel H. Wagner , William A. Sowa
摘要： The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.
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