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1.发明授权公开(公告)号：US09249679B2
公开(公告)日：2016-02-02
申请号：US13589375
申请日：2012-08-20
Applicant: Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
Inventor： Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
CPC classification number: F01D9/023 , F05D2260/201 , F23R3/06 , F23R2900/03044
Abstract: An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.
Abstract translation: 公开了一种冲击套筒和用于设计和形成冲击套筒的方法。 在一个实施例中，冲击套筒包括构造成至少部分地围绕燃烧器的过渡件的主体。 所述冲击套筒还包括限定在所述主体中的多个冷却孔，所述多个冷却孔具有冷却孔图案，所述冷却孔图案被配置为为所述过渡件提供期望的操作值。 多个冷却孔中的至少一个具有至少部分地在所述多个冷却孔中的至少一个冷却孔的入口和出口之间延伸的倒角。 多个冷却孔的至少一部分大体上是纵向不对称的。
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2.发明授权公开(公告)号：US08938978B2
公开(公告)日：2015-01-27
申请号：US13099938
申请日：2011-05-03
Applicant: Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
Inventor： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
CPC classification number: F23R3/283 , F23D2900/00003 , F23R3/286 , F23R3/46 , F23R3/54 , F23R2900/00017 , F23R2900/00018
Abstract: A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
Abstract translation: 提供了一种燃气涡轮发动机燃烧器，其包括燃料喷嘴阵列，围绕燃料喷嘴阵列设置的燃烧壳体组件和设置在燃烧壳体组件内的端盖组件，以便与燃烧壳体组件形成轴对称的环通过 所述流体行进到每个燃料喷嘴中，燃烧壳体组件和端盖组件中的至少一个形成有叶状的三维轮廓。
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3.发明授权Methods for controlling plasma spray coating porosity on an article and articles manufactured therefrom 有权用于控制由其制造的制品和制品上的等离子体喷涂孔隙率的方法公开(公告)号：US07722916B2
公开(公告)日：2010-05-25
申请号：US11420867
申请日：2006-05-30
Applicant: Hsin-Pang Wang , Michael Charles Ostrowski , Eric Moran , Stephen Gerard Pope , John Drake Vanselow , Edward Richard Haupt
Inventor： Hsin-Pang Wang , Michael Charles Ostrowski , Eric Moran , Stephen Gerard Pope , John Drake Vanselow , Edward Richard Haupt
IPC: C23C16/52
Abstract: Disclosed herein is a spray coating process for a robotic spray gun assembly comprising importing a discretized model of an object geometry to be coated; importing a numerically characterized spray pattern file; importing a robot motion file comprising a plurality of motion positions, dwell times and orientations defining a spray direction of the robotic spray gun; reading each motion position within the motion file; determining which portions of the object geometry are visible at each motion position; computing a void volume fraction at each visible portion of the object geometry based on the core compression, the incident angle of the robotic spray gun and the ricocheting of the spray for each motion position; and calculating total coating thickness on portions of the object geometry for the complete motion step.
Abstract translation: 本文公开了一种用于机器人喷枪组件的喷涂方法，包括导入待涂覆的物体几何体的离散模型; 导入数字表征的喷雾图案文件; 导入包括限定所述机器人喷枪的喷射方向的多个运动位置，停留时间和方向的机器人运动文件; 读取运动文件内的每个运动位置; 确定对象几何的哪些部分在每个运动位置可见; 基于核心压缩，机器人喷枪的入射角度和每个运动位置的喷射喷射计算物体几何体的每个可见部分处的空隙体积分数; 以及在整个运动步骤的对象几何部分上计算总涂层厚度。
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公开(公告)号：US20120279224A1
公开(公告)日：2012-11-08
申请号：US13099938
申请日：2011-05-03
Applicant: Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
Inventor： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
IPC: F23C3/00
CPC classification number: F23R3/283 , F23D2900/00003 , F23R3/286 , F23R3/46 , F23R3/54 , F23R2900/00017 , F23R2900/00018
Abstract: A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
Abstract translation: 提供了一种燃气涡轮发动机燃烧器，其包括燃料喷嘴阵列，围绕燃料喷嘴阵列设置的燃烧壳体组件和设置在燃烧壳体组件内的端盖组件，以便与燃烧壳体组件形成轴对称的环通过 所述流体行进到每个燃料喷嘴中，燃烧壳体组件和端盖组件中的至少一个形成有叶状的三维轮廓。
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公开(公告)号：US20100092896A1
公开(公告)日：2010-04-15
申请号：US12250875
申请日：2008-10-14
Applicant: Jesse Ellis Barton , Jonathan Dwight Berry , Mark Allan Hadley , Glenn David Nelson , Robert Joseph Rohrssen , John Drake Vanselow
Inventor： Jesse Ellis Barton , Jonathan Dwight Berry , Mark Allan Hadley , Glenn David Nelson , Robert Joseph Rohrssen , John Drake Vanselow
CPC classification number: F23R3/04 , F23L7/005 , F23L2900/07002 , F23L2900/07003 , F23L2900/07009 , F23R3/283 , F23R3/44 , F23R3/60 , F23R2900/00017 , Y02E20/342
Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. At least one shroud is secured to the baffle plate and includes at least one piston ring disposed at the shroud. The at least one piston ring is configured to meter a flow of diluent between the at least one shroud and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a piston ring gap defined by at least one piston ring disposed at a baffle plate and a fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the piston ring gap toward at least one airflow hole in the fuel nozzle.
Abstract translation: 公开了一种燃烧器，其包括具有至少一个通过挡板孔的挡板和至少一个延伸穿过至少一个挡板孔的燃料喷嘴。 至少一个护罩固定在挡板上并且包括设置在护罩上的至少一个活塞环。 所述至少一个活塞环构造成测量所述至少一个护罩和所述至少一个燃料喷嘴之间的稀释剂流。 还公开了一种向燃烧器提供稀释剂的方法，包括提供由设置在挡板上的至少一个活塞环限定的活塞环间隙和延伸穿过挡板中的通孔的燃料喷嘴。 稀释剂通过活塞环间隙朝向燃料喷嘴中的至少一个气流孔流动。
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Patent Agency Ranking
6.发明申请METHODS FOR CONTROLLING PLASMA SPRAY COATING POROSITY ON AN ARTICLE AND ARTICLES MANUFACTURED THEREFROM 有权用于控制其制造的物品和制品上的等离子喷涂涂层的方法公开(公告)号：US20070281074A1
公开(公告)日：2007-12-06
申请号：US11420867
申请日：2006-05-30
Applicant: Hsin-Pang Wang , Michael Charles Ostrowski , Eric Moran , Stephen Gerard Pope , John Drake Vanselow , Edward Richard Haupt
Inventor： Hsin-Pang Wang , Michael Charles Ostrowski , Eric Moran , Stephen Gerard Pope , John Drake Vanselow , Edward Richard Haupt
Abstract: Disclosed herein is a spray coating process for a robotic spray gun assembly comprising importing a discretized model of an object geometry to be coated; importing a numerically characterized spray pattern file; importing a robot motion file comprising a plurality of motion positions, dwell times and orientations defining a spray direction of the robotic spray gun; reading each motion position within the motion file; determining which portions of the object geometry are visible at each motion position; computing a void volume fraction at each visible portion of the object geometry based on the core compression, the incident angle of the robotic spray gun and the ricocheting of the spray for each motion position; and calculating total coating thickness on portions of the object geometry for the complete motion step.
Abstract translation: 本文公开了一种用于机器人喷枪组件的喷涂方法，包括导入待涂覆的物体几何体的离散模型; 导入数字表征的喷雾图案文件; 导入包括限定所述机器人喷枪的喷射方向的多个运动位置，停留时间和方向的机器人运动文件; 读取运动文件内的每个运动位置; 确定对象几何的哪些部分在每个运动位置可见; 基于核心压缩，机器人喷枪的入射角度和每个运动位置的喷射喷射计算物体几何体的每个可见部分处的空隙体积分数; 以及在整个运动步骤的对象几何部分上计算总涂层厚度。
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公开(公告)号：US20110008614A1
公开(公告)日：2011-01-13
申请号：US12500502
申请日：2009-07-09
Applicant: Tamara Jean Muth , Patricia Chapman Irwin , Surinder Singh Pabla , John Drake Vanselow
CPC classification number: C04B35/6306 , C04B35/6303 , C04B35/6309 , C04B35/6313 , C04B2235/3241 , F01D5/284 , F01D5/288 , F05D2230/90 , F05D2260/95 , Y10T428/256 , Y10T428/31515 , Y10T428/31678
Abstract: In one embodiment, a protective coating may be electrostatically applied to a rotary machine component. The powder coating includes an electrically conductive sacrificial base coat and a ceramic oxide erosion resistant top coat.
Abstract translation: 在一个实施例中，保护涂层可以静电地施加到旋转机器部件。 粉末涂料包括导电牺牲基底涂层和陶瓷耐氧化物侵蚀顶涂层。
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公开(公告)号：US20100089020A1
公开(公告)日：2010-04-15
申请号：US12250933
申请日：2008-10-14
Applicant: Jesse Ellis Barton , Jonathan Dwight Berry , Mark Allan Hadley , John Drake Vanselow
Inventor： Jesse Ellis Barton , Jonathan Dwight Berry , Mark Allan Hadley , John Drake Vanselow
Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle.
Abstract translation: 公开了一种燃烧器，其包括具有至少一个通过挡板孔的挡板和至少一个延伸穿过至少一个挡板孔的燃料喷嘴。 一个可周向调节的套环位于挡板和至少一个燃料喷嘴之间的至少一个挡板孔处。 在轴环处的多个开口被配置成测量在挡板孔和至少一个燃料喷嘴之间的稀释剂流。 还公开了一种用于向燃烧器提供稀释剂的方法，包括提供设置在挡板和至少一个延伸穿过挡板中的通孔的燃料喷嘴之间的周向可调环圈处的多个开口。 稀释剂通过多个开口朝向至少一个燃料喷嘴中的至少一个气流孔流动。
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9.发明申请TURBOMACHINE COMBUSTOR NOZZLE INCLUDING A MONOLITHIC NOZZLE COMPONENT AND METHOD OF FORMING THE SAME 有权涡轮喷雾器喷嘴，包括单声道喷嘴组件及其形成方法公开(公告)号：US20130318975A1
公开(公告)日：2013-12-05
申请号：US13482540
申请日：2012-05-29
Applicant: Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
Inventor： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
CPC classification number: F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49323
Abstract: A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
Abstract translation: 涡轮机燃烧器喷嘴包括具有板元件和多个喷嘴元件的单片喷嘴部件。 多个喷嘴元件中的每一个包括从板元件延伸到第二端的第一端。 板元件和多个喷嘴元件形成为整体部件。 板构件与喷嘴部件接合。 板构件包括限定第一和第二表面的外边缘和在第一和第二表面之间延伸的多个开口。 多个开口被配置和设置成与多个喷嘴元件中对应的喷嘴元件的对应的第二端对准并接收。
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10.发明申请公开(公告)号：US20130269351A1
公开(公告)日：2013-10-17
申请号：US13449012
申请日：2012-04-17
Applicant: Zhaoli Hu , Mark Lawrence Hunt , Chandrudu Srikanth Kottilingam , James Christopher Monaghan , John Drake Vanselow
Inventor： Zhaoli Hu , Mark Lawrence Hunt , Chandrudu Srikanth Kottilingam , James Christopher Monaghan , John Drake Vanselow
CPC classification number: F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49229
Abstract: A micromixer assembly of a turbine system includes a plate having at least one aperture comprising a receiving diameter. Also included is at least one tube having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor, wherein the at least one tube includes an inner diameter and an outer diameter, wherein the outer diameter is configured to fit within the receiving diameter of the at least one aperture, wherein the at least one tube is operably coupled at a location on the outer diameter to the receiving diameter of the at least one aperture by exerting a radial force on the inner diameter of the tube.
Abstract translation: 涡轮机系统的微混合器组件包括具有包括接收直径的至少一个孔的板。 还包括至少一个管，其具有用于接收流动并将流分散到燃烧器的入口和出口，其中所述至少一个管包括内径和外径，其中外径配置成适合 接收所述至少一个孔的直径，其中所述至少一个管通过在所述管的内径上施加径向力而在所述外径上的位置处可操作地联接到所述至少一个孔的接收直径。
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