公开(公告)号：US10118361B2

公开(公告)日：2018-11-06

申请号：US15004261

申请日：2016-01-22

Applicant: United Technologies Corporation

Inventor： Stuart C. Kozan ,  William Bogue

IPC: B32B3/10 ,  B32B3/08 ,  F16L59/02 ,  F16L59/14 ,  F16L59/16 ,  F17C13/00

Abstract: A thermal protection apparatus is disclosed. The thermal protection apparatus may comprise a thermally insulative layer positioned proximate to a portion of a structure having a dimensional transition, wherein the dimensional transition is thermally protected.

公开(公告)号：US10094242B2

公开(公告)日：2018-10-09

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: B29C73/04 ,  F01D25/24 ,  F02C9/00 ,  B23P6/00 ,  F01D25/00 ,  B29C73/26

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.

公开(公告)号：US10049318B2

公开(公告)日：2018-08-14

申请号：US14903915

申请日：2014-07-09

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Joseph Parkos ,  Gary M. Lomasney ,  William Bogue

IPC: C25D5/06 ,  C25D17/14 ,  G06K19/077 ,  G01N3/08 ,  C23C18/16 ,  C23C28/02 ,  C23C18/22 ,  C25D1/02 ,  C25D1/20 ,  C25D7/04 ,  C25D3/02 ,  C25D5/56 ,  C25D7/00 ,  C25D9/02 ,  C25D17/12 ,  B29C37/00 ,  B29C67/00 ,  C23C18/30 ,  C23C18/32 ,  C25D1/00 ,  G01B7/16 ,  G01D5/12 ,  B29C70/42 ,  B29C70/54 ,  B32B27/08 ,  C25D5/54 ,  B32B27/28 ,  B33Y10/00 ,  B29K79/00 ,  B29K105/00 ,  B29K105/12 ,  B29K307/04 ,  B29K309/08 ,  B29L9/00 ,  B29L31/08 ,  B33Y70/00 ,  B33Y80/00

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.

公开(公告)号：US09926793B2

公开(公告)日：2018-03-27

申请号：US14774420

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： William Bogue ,  Timothy J. Tabor ,  Joseph J. Parkos, Jr.

IPC: C23C4/02 ,  F01D5/28 ,  C25D11/18 ,  F01D11/08 ,  C23C28/04 ,  C25D11/04 ,  C25D11/02 ,  C23C4/11 ,  C23C4/134 ,  C25D11/08 ,  C25D11/10

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.

公开(公告)号：US09897009B2

公开(公告)日：2018-02-20

申请号：US15017978

申请日：2016-02-08

Applicant: United Technologies Corporation

Inventor： Paul E. Strong ,  Younus Ahmed ,  William Bogue ,  Michael Chrysosferidis

IPC: B32B3/06 ,  F02C7/24 ,  F02C7/22 ,  B32B3/26 ,  B32B5/02 ,  B32B5/26 ,  B32B7/08 ,  B32B7/12 ,  B32B9/00 ,  B32B9/04

CPC classification number: F02C7/24 ,  B32B3/06 ,  B32B3/266 ,  B32B5/024 ,  B32B5/26 ,  B32B7/08 ,  B32B7/12 ,  B32B9/005 ,  B32B9/047 ,  B32B2255/205 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/101 ,  B32B2262/105 ,  B32B2307/304 ,  B32B2307/7265 ,  B32B2571/00 ,  B32B2605/18 ,  F01D25/08 ,  F02C7/222 ,  Y02T50/675

Abstract: Aspects of the disclosure are directed to a flexible thermal blanket assembly, comprising: a stack-up of material layers that are configured to wrap around a component, a plurality of snaps configured to be mechanically fastened through the material layers, and a cap configured as a baffle to prevent thermal energy located at an exterior of the thermal blanket assembly from entering an interior of the thermal blanket assembly when the thermal blanket assembly is assembled.

公开(公告)号：US20170260904A1

公开(公告)日：2017-09-14

申请号：US15606086

申请日：2017-05-26

Applicant: United Technologies Corporation

Inventor： William Bogue ,  Ron I. Prihar

IPC: F02C7/12 ,  F01D25/12 ,  F01D5/28

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 ,  Y02T50/6765

Abstract: A component of a gas turbine engine includes a plurality of first cooling holes extending between an outer surface and an inner surface of the component, the plurality of first cooling holes being filled with a filling agent, the filling agent being cured to solid form to block the flow of cooling fluid though the plurality of first cooling holes; a thermal barrier coating over the outer surface of the component and completely covering the cured filling agent; anda plurality of second cooling holes penetrating the thermal barrier coating and extending between the outer surface and the inner surface, the plurality of second cooling holes allowing cooling fluid to pass therethrough.

公开(公告)号：US09664111B2

公开(公告)日：2017-05-30

申请号：US13719892

申请日：2012-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William Bogue ,  Ron I. Prihar

IPC: F02C7/12 ,  F01D5/28 ,  F01D25/12 ,  B23P6/00 ,  F01D5/18 ,  C23C4/00 ,  C25D7/04

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.

公开(公告)号：US20160215697A1

公开(公告)日：2016-07-28

申请号：US14527175

申请日：2014-10-29

Applicant: United Technologies Corporation

Inventor： Derek W. Anderson ,  Ron I. Prihar ,  William Bogue

IPC: F02C7/20 ,  F16M13/02 ,  F16L3/02

CPC classification number: F02C7/20 ,  F02C7/32 ,  F16L3/223 ,  F16L3/237 ,  F16L55/035 ,  F16L57/00

Abstract: A bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A doubler is mechanically fastened adjacent to the separation. Another bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A cushioned tube support is welded to the bracket base. A doubler is mechanically fastened adjacent to the separation. A method of assembling a bracket assembly for a gas turbine engine includes mechanically fastening a doubler to a bracket base adjacent to a separation between a first bended feature and a second bended feature.

Abstract translation: 用于燃气涡轮发动机的支架组件包括具有第一弯曲特征和第二弯曲特征之间的间隔的托架基座。 倍增器在分离附近机械固定。 用于燃气涡轮发动机的另一个支架组件包括具有第一弯曲特征和第二弯曲特征之间的间隔的托架基座。 缓冲管支撑件焊接到支架底座。 倍增器在分离附近机械固定。 组装用于燃气涡轮发动机的支架组件的方法包括将倍频器机械地紧固到与第一弯曲特征和第二弯曲特征之间的间隔相邻的支架基座。