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公开(公告)号：WO2015026448A2
公开(公告)日：2015-02-26
申请号：PCT/US2014/045945
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KLING, Colin J. , PARKOS, Joseph , LOMASNEY, Gary M. , BOGUE, William
CPC classification number: G06K19/07749 , B29C37/0025 , B29C64/124 , B29C64/153 , B29C67/0062 , B29C67/0077 , B29C70/42 , B29C70/54 , B29K2079/08 , B29K2105/0058 , B29K2105/12 , B29K2105/251 , B29K2105/253 , B29K2307/04 , B29K2309/08 , B29L2009/008 , B29L2031/082 , B32B27/08 , B32B27/281 , B32B2250/02 , B32B2255/10 , B32B2255/205 , B32B2262/101 , B32B2262/106 , B32B2603/00 , B33Y10/00 , B33Y70/00 , B33Y80/00 , C23C18/1641 , C23C18/1653 , C23C18/1657 , C23C18/166 , C23C18/22 , C23C18/30 , C23C18/32 , C23C28/021 , C23C28/023 , C25D1/003 , C25D1/02 , C25D1/20 , C25D3/02 , C25D5/06 , C25D5/54 , C25D5/56 , C25D7/00 , C25D7/04 , C25D9/02 , C25D17/12 , G01B7/16 , G01D5/12 , G01N3/08 , G01N2203/026 , G01N2203/0268 , G01N2203/0298
Abstract: A method for balancing a rotatable component is disclosed This method comprises and then plating the component to deposit a metal layer onto the component until the component is balanced. In addition, and alternative method for balancing a rotatable component is disclosed. This method comprises attaching a balancing weight to the rotatable component and rotating the component. This is followed by plating the component and the balancing weight to deposit a metal layer onto the balancing weight and the component until the component is balanced.
Abstract translation: 公开了一种用于平衡可旋转部件的方法。该方法包括然后电镀该部件以将金属层沉积到部件上直到部件平衡。 另外，公开了用于平衡可旋转部件的替代方法。 该方法包括将平衡配重附接到可旋转部件并旋转部件。 接着是电镀组件和平衡重量，以在平衡重和组件上沉积金属层，直到组件平衡为止。
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2.发明申请REPLACING AN APERTURE WITH AN ANNULAR BUSHING IN A COMPOSITE LAMINATED COMPOSITE COMPONENT 审中-公开在复合复合复合材料组件中使用环形布置替换孔
公开(公告)号：WO2015026798A1
公开(公告)日：2015-02-26
申请号：PCT/US2014/051651
申请日：2014-08-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HOLLAND, Brian K. , DENTON, Jeffrey , BOGUE, William
CPC classification number: F01D25/24 , B29C73/06 , B29C2073/268 , F01D25/005 , F02C7/00 , F05D2230/80 , F05D2260/31 , F05D2300/603 , F16B5/01 , F16B11/006 , F16B43/00
Abstract: An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an outer surface of the annular cylindrical portion and the flange. The multiple of spacers are operable to control a bond line thickness.
Abstract translation: 环形衬套包括环形圆柱形部分，其具有沿轴线限定紧固件孔的凸缘。 多个间隔件从环形圆柱形部分和凸缘的外表面延伸。 多个间隔件可操作以控制粘结线厚度。
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公开(公告)号：WO2014133602A3
公开(公告)日：2014-09-04
申请号：PCT/US2013/068708
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOGUE, William , TABOR, Timothy, J.
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.
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公开(公告)号：WO2014099161A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/068750
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOGUE, William , PRIHAR, Ron, I.P.E.
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 barrier 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: 公开了一种用于填充燃气涡轮发动机的部件中的冷却孔的方法。 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：暴露部件的外表面，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，并施加热障涂层 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。
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公开(公告)号：WO2015088593A1
公开(公告)日：2015-06-18
申请号：PCT/US2014/051189
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ALARCON, Andrew, G. , BOGUE, William
CPC classification number: F04D29/083 , F01D11/001 , F01D11/008 , F04D19/002 , F04D29/322 , F04D29/329 , F04D29/34 , F04D29/38 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2240/80 , F05D2250/121 , F05D2260/98 , F05D2300/43
Abstract: An edge seal for preventing airflow through a space between a fan platform and an adjacent airfoil in a gas turbine engine may include a bonding segment being bondable to the fan platform. A sealing flap converges with the bonding segment so that the sealing flap is operatively contactable with the adjacent airfoil. A bumper rib protrudes from the bonding segment so that the bumper rib is bondable to the fan platform.
Abstract translation: 用于防止气流通过燃气涡轮发动机中的风扇平台和相邻翼型之间的空间的边缘密封件可以包括可与风扇平台接合的接合段。 密封翼与接合段会聚，使得密封翼可操作地与相邻的翼型接触。 保险杠肋从接合段突出，使得保险杠肋可接合到风扇平台。
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Patent Agency Ranking6.发明申请
公开(公告)号：WO2015017405A1
公开(公告)日：2015-02-05
申请号：PCT/US2014/048607
申请日：2014-07-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HOLLAND, Brian K. , BOGUE, William , DENTON, Jeffrey
CPC classification number: B23K31/02 , F01D5/005 , F02K1/78 , F05D2230/232 , F05D2230/40 , F05D2300/133 , F05D2300/174 , F05D2300/701 , G01N21/3563 , G01N21/552 , G01N21/94 , G01N2021/3595 , G01N2201/0221
Abstract: A method of immobilizing a contaminant within a component includes identifying the contaminate; and thermally processing the component via a specific thermal cycle related to the contaminate. A method of repairing a component includes immobilizing a contaminant within the component; and weld repairing the component subsequent to immobilizing the contaminant. An aerospace component includes a honeycomb structure with a thermally decomposed contaminate and a weld repair.
Abstract translation: 将组分中污染物固定的方法包括识别污染物; 并通过与污染物相关的特定热循环热处理该组件。 修复部件的方法包括将污染物固定在所述部件内; 并在固定污染物之后焊接修补部件。 航空航天部件包括具有热分解污染物和焊接修复的蜂窝结构。
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公开(公告)号：WO2015006487A1
公开(公告)日：2015-01-15
申请号：PCT/US2014/046012
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOGUE, William , COOK, Grant, O. III , LOMASNEY, Gary, M. , PARKOS, Joseph , KLING, Colin, J. , WATSON, Charles, R.
CPC classification number: C25D5/56 , B05D5/00 , B05D7/02 , B22C7/023 , B22C9/043 , B22C9/10 , B28B1/24 , B28B7/342 , B28B11/04 , B28B11/243 , B32B3/263 , B32B7/12 , B32B15/04 , B32B15/08 , B32B15/20 , B32B37/12 , B32B37/1284 , B32B37/14 , B32B2255/10 , B32B2307/202 , B32B2307/554 , B32B2603/00 , B33Y10/00 , B33Y80/00 , B62D35/00 , B64C39/024 , B64C39/028 , B64C2201/10 , C04B35/76 , C04B35/806 , C09D5/26 , C23C14/20 , C23C16/06 , C23C18/1633 , C23C18/165 , C23C18/2013 , C23C18/22 , C23C18/31 , C23C26/00 , C23C28/02 , C25D3/02 , C25D3/38 , C25D3/46 , C25D5/48 , C25D9/04 , C25D11/20 , F01D5/00 , F01D5/147 , F01D5/187 , F01D5/284 , F01D5/288 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/005 , F04D29/023 , F04D29/324 , F04D29/542 , F05D2220/32 , F05D2230/10 , F05D2230/22 , F05D2230/30 , F05D2230/312 , F05D2230/314 , F05D2240/122 , F05D2240/304 , F05D2300/10 , F05D2300/11 , F05D2300/121 , F05D2300/132 , F05D2300/133 , F05D2300/1616 , F05D2300/171 , F05D2300/177 , F05D2300/20 , F05D2300/30 , F05D2300/44 , F05D2300/501 , F05D2300/603 , F05D2300/611 , F05D2300/614 , F42B10/02
Abstract: A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.
Abstract translation: 公开了复合组分和镀覆聚合物组分。 复合部件可以包括由有机基质复合材料形成的主体部分，施加到主体部分的表面上的第一金属涂层以及耐腐蚀的第一金属涂层上的外部金属层。 镀覆的聚合物组分可以包括聚合物基材，施加到聚合物基材的表面的金属镀层，以及金属镀层中的至少一个选择性增稠区域。 所述至少一个选择性增稠的区域可有助于保护镀覆的聚合物组分免受磨损和/或侵蚀。
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公开(公告)号：WO2014150362A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/023054
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOGUE, William , TABOR, Timothy, J. , PARKOS, Joseph, J., Jr.
CPC classification number: F01D5/288 , C23C4/02 , C23C4/11 , C23C4/134 , C23C28/04 , C25D11/022 , C25D11/04 , C25D11/08 , C25D11/10 , C25D11/18 , F01D11/08 , F05D2220/36 , F05D2230/31 , F05D2230/312 , F05D2240/307 , F05D2300/121
Abstract: A blade (100) has an airfoil (106) having a leading edge (114), a trailing edge (116), a pressure side (118), and a suction side (120) and extending from an inboard end (110) to a tip (112). An attachment root (108) is at the inboard end. The blade comprises an aluminum alloy substrate (102) and a coating at the tip (130). The coating (130) comprises an anodic layer (160) atop the substrate and an aluminum oxide layer (162) atop the anodic layer.
Abstract translation: 叶片（100）具有翼缘（106），其具有前缘（114），后缘（116），压力侧（118）和吸力侧（120），并且从内侧端部（110）延伸到 尖端（112）。 附件根（108）位于内侧。 刀片包括铝合金基底（102）和尖端处的涂层（130）。 涂层（130）包括位于基底顶部的阳极层（160）和位于阳极层顶部的氧化铝层（162）。
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公开(公告)号：WO2014099160A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/068745
申请日：2013-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOGUE, William , PRIHAR, Ron, I.P.E.
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: 公开了一种用于填充燃气涡轮发动机的部件中的冷却孔的方法。 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，并且施加热障碍 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。
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公开(公告)号：EP2971531B1
公开(公告)日：2020-03-04
申请号：EP14769262.8
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： BOGUE, William , TABOR, Timothy, J. , PARKOS, Joseph, J., Jr.
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