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    Sliding Contact Wear Surfaces Coated with PTFE/Aluminum Oxide Thermal Spray Coating
    23.
    发明申请
    Sliding Contact Wear Surfaces Coated with PTFE/Aluminum Oxide Thermal Spray Coating 审中-公开
    滑动接触磨损表面涂有PTFE /氧化铝热喷涂

    公开(公告)号：US20150369133A1

    公开(公告)日：2015-12-24

    申请号：US14758742

    申请日：2013-11-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William Bogue ,  Timothy Tabor

    IPC: F02C9/18 ,  F16K3/02 ,  F16K31/122 ,  F16K25/00 ,  C23C4/10 ,  B05D1/08

    Abstract: A method of applying a wear-resistant coating to aluminum sliding contact wear surfaces is disclosed. The method includes providing a plurality of parts having sliding contact wear surfaces and thermal spray coating at least one of a composite aluminum oxide and PTFE or a blend of aluminum oxide and PTFE. The disclosed method may be used to repair aluminum parts subject to sliding contact wear as well as in the design of new aluminum parts subject to sliding contact wear. Improved compressor bleed valves for gas turbine engines and improved fan exit case assemblies are also disclosed.

    Abstract translation: 公开了一种向铝滑动接触磨损表面施加耐磨涂层的方法。 该方法包括提供多个具有滑动接触磨损表面的部件和热喷涂复合氧化铝和PTFE中的至少一种或氧化铝和PTFE的共混物。 所公开的方法可以用于修复受滑动接触磨损的铝部件以及在滑动接触磨损的新铝部件的设计中。 还公开了用于燃气涡轮发动机和改进的风扇出口箱组件的改进的压缩机放气阀。

    REPAIR OR REMANUFACTURE OF LINER PANELS FOR A GAS TURBINE ENGINE
    24.
    发明申请
    REPAIR OR REMANUFACTURE OF LINER PANELS FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的内衬板的修理或拆卸

    公开(公告)号：US20150240661A1

    公开(公告)日：2015-08-27

    申请号：US14628263

    申请日：2015-02-22

    Applicant: United Technologies Corporation

    Inventor： Brian K. Holland ,  Michael A. Morden ,  Brandon A. Gates ,  William Bogue

    IPC: F01D25/24 ,  F01D25/00 ,  B23P6/00

    CPC classification number: F01D25/24 ,  B23P6/005 ,  B29C73/04 ,  B29C73/26 ,  F01D25/005 ,  F02C9/00 ,  Y02T50/672 ,  Y10T29/49318

    Abstract: A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.

    Abstract translation: 一种用于燃气涡轮发动机的衬板的再制造方法包括从损坏的部件移除衬套; 并用材料成型模制衬套。 用于燃气涡轮发动机的衬板包括前风扇出口壳衬里面板，其具有来自损坏的前风扇出口壳衬套板的供体衬套。 用于燃气涡轮发动机的衬板包括由包括多个层的材料装料模制的前风扇出口壳衬里面板。 层的多重中的至少一个包括不连续性。

    Device and Method for Repairing A Forward Frame V-Blade In An Aircraft Engine
    25.
    发明申请
    Device and Method for Repairing A Forward Frame V-Blade In An Aircraft Engine 有权
    在飞机发动机中修复前方V形叶片的装置和方法

    公开(公告)号：US20150184513A1

    公开(公告)日：2015-07-02

    申请号：US14325066

    申请日：2014-07-07

    Applicant: United Technologies Corporation

    Inventor： Brian Kenneth Holland ,  Michael J. Madel, JR. ,  William Bogue

    IPC: F01D5/00 ,  F01D5/14 ,  B23P6/00

    CPC classification number: F01D5/005 ,  B23P6/005 ,  F01D5/141 ,  F05B2260/301 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49321 ,  Y10T29/49721

    Abstract: A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a repair part and a splice plate, the combination of which is secured to the forward frame v-blade. The repair part includes a repair part web and a pair of stiffening legs with a leg thickness that is greater that the thickness of corresponding flanges on the forward frame v-blade. The splice plate is configured to accommodate for the increased thickness of the stiffening legs, providing by way of example a reduced thickness area compatible with the repair part. Fasteners such as rivets are used to couple the repair device to the splice plate, and to couple the splice plate to the forward frame v-blade.

    Abstract translation: 描述了用于修复飞机发动机上的前方叶片V形叶片的修理装置和方法，其中修理装置取代前方叶片V形叶片的一部分。 在一个实施例中，修理装置包括修理部分和拼接板，其组合被固定到前框架叶片。 修理部分包括修理部件腹板和一对加强腿，其腿部厚度大于前部框架v形叶片上的对应凸缘的厚度。 接合板被配置为适应增强的腿部的增加的厚度，例如提供与修复部件相容的减小厚度的区域。 诸如铆钉的紧固件用于将修复装置连接到拼接板，并将拼接板连接到前架v叶片。

    Closure of Cooling Holes with a Filling Agent
    26.
    发明申请
    Closure of Cooling Holes with a Filling Agent 有权
    用填充剂封闭冷却孔

    公开(公告)号：US20140174092A1

    公开(公告)日：2014-06-26

    申请号：US13722253

    申请日：2012-12-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William Bogue ,  Ron I. P. E. Prihar

    IPC: B05D7/22 ,  F23R3/00

    CPC classification number: B05D7/22 ,  B23P6/007 ,  B23P2700/06 ,  B23P2700/13 ,  C23C4/02 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/42 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/434 ,  F23R3/002 ,  F23R2900/00016 ,  F23R2900/00019

    Abstract: A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.

    Abstract translation: 公开了一种用于在燃气涡轮发动机的部件中填充冷却孔的方法。 部件可以包括延伸穿过部件的壁的多个第一冷却孔。 该方法可以包括以下步骤：暴露组件的外表面，用聚酰亚胺填充多个第一冷却孔，固化聚酰亚胺以阻止冷却流体通过多个第一冷却孔，并且施加热泡沫涂层 在组件的外表面上。 该方法还可以包括在组件的壁中安装第二多个冷却孔的步骤，其中多个第二冷却孔穿过热障涂层和部件的壁并允许冷却流体通过。

    Closure of Cooling Holes with a Filing Agent
    27.
    发明申请
    Closure of Cooling Holes with a Filing Agent 有权
    使用归档代理关闭冷却孔

    公开(公告)号：US20140166255A1

    公开(公告)日：2014-06-19

    申请号：US13719892

    申请日：2012-12-19

    Applicant: United Technologies Corporation

    Inventor： William Bogue ,  Ron I. P. E. Prihar

    IPC: F02C7/12

    CPC classification number: F02C7/12 ,  B23P6/002 ,  B23P2700/06 ,  C23C4/00 ,  C25D7/04 ,  F01D5/18 ,  F01D5/284 ,  F01D5/288 ,  F01D25/12 ,  F05D2230/90 ,  Y02T50/675

    Abstract: A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes penetrating the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes of the component with a filling agent, curing the filling agent to block the passage of air through the cooling holes, and applying a thermal barrier coating over the surface of the component. The method may further include installing a second plurality of cooling holes, the second plurality of cooling holes penetrating the thermal barrier coating and the wall of the component and allow air to pass therethrough.

    Abstract translation: 公开了一种用于在燃气涡轮发动机的部件中填充冷却孔的方法。 该部件可以包括穿过部件的壁的多个第一冷却孔。 该方法可以包括以下步骤：暴露组件的外表面，用填充剂填充组件的多个第一冷却孔，固化填充剂以阻止空气通过冷却孔，并施加热障碍 涂覆在组件的表面上。 该方法可以进一步包括安装第二多个冷却孔，第二多个冷却孔穿过热障涂层和部件的壁并允许空气通过。

    NON-DESTRUCTIVE TEST INSPECTION METHOD FOR EVALUATING THERMAL DEGRADATION OF BISMALEIMIDE RESIN
    28.
    发明申请
    NON-DESTRUCTIVE TEST INSPECTION METHOD FOR EVALUATING THERMAL DEGRADATION OF BISMALEIMIDE RESIN 有权
    非破坏性测试方法，用于评估双马来酰亚胺树脂的热降解

    公开(公告)号：US20140096350A1

    公开(公告)日：2014-04-10

    申请号：US14046652

    申请日：2013-10-04

    Applicant: United Technologies Corporation

    Inventor： Jeffrey Denton ,  James H. Stewart ,  William Bogue

    IPC: G01N33/44 ,  G01N21/25

    CPC classification number: G01N33/44 ,  G01N21/25 ,  G01N21/3563 ,  Y10T29/49769

    Abstract: A non-destructive method for determining an amount of temperature exposure to a Bismaleimide Resin (BMI) matrix substrate, the method includes determining component data of a Bismaleimide Resin (BMI) matrix component via fourier transform infrared (FTIR) spectroscopy; correlating the component data to model data to determine a structural debit from temperature exposure; and bounding a structurally damaged area in response to the correlating.

    Abstract translation: 一种用于确定双马来酰亚胺树脂（BMI）基质基质的温度暴露量的非破坏性方法，该方法包括通过傅立叶变换红外（FTIR）光谱测定双马来酰亚胺树脂（BMI）基质组分的成分数据; 将组件数据与模型数据相关联，以确定温度暴露的结构性借方; 并结合相关的结构损伤区域。

    High temperature composite seal
    29.
    发明授权
    High temperature composite seal 有权

    公开(公告)号：US11065825B2

    公开(公告)日：2021-07-20

    申请号：US16210528

    申请日：2018-12-05

    Applicant: United Technologies Corporation

    Inventor： Kerry Lynn Davis ,  William Bogue

    IPC: B29C65/00 ,  B29C35/02 ,  B29C65/02 ,  B29K79/00

    Abstract: A method of sealing a first component to a second component comprising the steps of locating at least one fiber reinforced polyimide resin layer against a first sealing surface on a first component and against a second sealing surface on a second component. At least one fiber reinforced polyimide resin layer is compressed against the first sealing surface and the second sealing surface prior to curing at least one fiber reinforced polyimide resin layer. At least one fiber reinforced polyimide resin layer is heated to promote flow and conformation to the first sealing surface and the second sealing surface. At least one fiber reinforced polyimide resin layer is cured to provide a fluid tight seal between the first component and the second component.

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