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公开(公告)号：US11408291B2
公开(公告)日：2022-08-09
申请号：US16047319
申请日：2018-07-27
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: A coating membrane for a component of a gas-turbine engine includes a solid membrane having a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface. Also disclosed are a coated component coated with the membrane, and a method for producing a coated component with the membrane.
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公开(公告)号：US20210131286A1
公开(公告)日：2021-05-06
申请号：US16668820
申请日：2019-10-30
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction, and includes a sheath having first and second sheath portions extending along an airfoil body of the airfoil section. The first sheath portion includes a first interface portion, and the second sheath portion includes a second interface portion that cooperates with the first interface portion to establish a joint having a circuitous profile along an edge of the airfoil body. A method of assembly for an airfoil is also disclosed.
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公开(公告)号：US10167885B2
公开(公告)日：2019-01-01
申请号：US15076077
申请日：2016-03-21
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: A mechanical joint is provided between a first component and a second component. The mechanical joint includes a flanged retainer and a fastener. The flanged retainer includes a base and a flange. The base includes a bore and a counterbore that extends longitudinally along a centerline into the base from a longitudinal end of the base to the bore. The flange extends radially out from and circumferentially about the base at the longitudinal end of the base. The flange longitudinally engages the first component and the base projects longitudinally through the aperture and longitudinally engages the second component. The fastener includes an anchor and a shaft. The anchor is seated within the counterbore. The shaft projects longitudinally from the anchor, through the bore, and at least to the second component.
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公开(公告)号：US20170268546A1
公开(公告)日：2017-09-21
申请号：US15076077
申请日：2016-03-21
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
CPC classification number: F16B5/02 , F01D25/243 , F05D2220/32 , F16B39/24 , F16B43/00
Abstract: A mechanical joint is provided between a first component and a second component. The mechanical joint includes a flanged retainer and a fastener. The flanged retainer includes a base and a flange. The base includes a bore and a counterbore that extends longitudinally along a centerline into the base from a longitudinal end of the base to the bore. The flange extends radially out from and circumferentially about the base at the longitudinal end of the base. The flange longitudinally engages the first component and the base projects longitudinally through the aperture and longitudinally engages the second component. The fastener includes an anchor and a shaft. The anchor is seated within the counterbore. The shaft projects longitudinally from the anchor, through the bore, and at least to the second component.
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公开(公告)号：US11215054B2
公开(公告)日：2022-01-04
申请号：US16668820
申请日：2019-10-30
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction, and includes a sheath having first and second sheath portions extending along an airfoil body of the airfoil section. The first sheath portion includes a first interface portion, and the second sheath portion includes a second interface portion that cooperates with the first interface portion to establish a joint having a circuitous profile along an edge of the airfoil body. A method of assembly for an airfoil is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20210131294A1
公开(公告)日：2021-05-06
申请号：US16673020
申请日：2019-11-04
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction. A sheath extends in the spanwise direction along at least one of the pressure and suction sides of the airfoil section. A tip cap extends in the chordwise direction along the at least one of the pressure and suction sides. The sheath includes a first set of interface members. The tip cap includes a second set of interface members interleaved with the first set of interface members to establish at least one joint along an external surface of the at least one of the pressure and suction sides. A method of assembly for an airfoil is also disclosed.
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公开(公告)号：US10483659B1
公开(公告)日：2019-11-19
申请号：US16194931
申请日：2018-11-19
Applicant: United Technologies Corporation
Inventor： David R. Lyders , Nicholas D. Stilin , Kevin M. Bell
IPC: H01R4/66 , H01R4/64 , H01R43/027 , F01D9/04 , F01D25/28
Abstract: A grounding clip for an organic matrix composite guide vane with a metallic sheath comprises the organic matrix composite guide vane includes a body having a leading edge and a trailing edge opposite the leading edge and a root end extending between the leading end edge and the trailing edge. The metallic sheath is attached proximate the leading edge and extends to the root end. A metallic attachment fitting has a receiver configured to receive the root end of the organic matrix composite guide vane for coupling the organic matrix composite guide vane to the metallic attachment fitting. The grounding clip is coupled to the sheath proximate the root end; wherein the grounding clip is electrically connected to the metallic attachment fitting and the metallic sheath.
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公开(公告)号：US20190292921A1
公开(公告)日：2019-09-26
申请号：US15926370
申请日：2018-03-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Bradley L. Paquin , Nicholas D. Stilin
Abstract: A composite airfoil is disclosed. The composite airfoil includes a first ply having a first plurality of strips of fiber oriented at a first angle with respect to a longitudinal axis and a second plurality of strips of fiber oriented at a second angle with respect to the longitudinal axis at least a first subset of the first plurality of strips of fibers have fibers intersecting and oriented at an angle to the fibers in at least a second subset of the second plurality of strips of fibers within a ply boundary.
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公开(公告)号：US20150218957A1
公开(公告)日：2015-08-06
申请号：US14428749
申请日：2013-03-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carl Brian Klinetob , Nicholas D. Stilin
CPC classification number: F01D11/001 , F01D9/02 , F01D11/005 , F01D11/006 , F02C3/04 , F05D2240/12 , F05D2240/55 , F05D2250/141 , F05D2250/241 , F05D2300/431 , F05D2300/437 , F05D2300/501 , F16J15/027
Abstract: A seal for use with a static guide vane of a gas turbine engine has a strap member extending to a generally cylindrical bulb. The bulb forms a diameter, and is spaced a distance defined between an end of the strap remote from the bulb, to a point on the bulb furthest from the end. A ratio of the diameter to the distance is between 0.2 and 0.5. A static guide vane and a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的静态导向叶片的密封件具有延伸到大致圆柱形灯泡的带部件。 灯泡形成直径，并且间隔开距离灯泡的带的端部之间的距离，距离最远端的灯泡上的点。 直径与距离之比在0.2与0.5之间。 还公开了静态导向叶片和燃气涡轮发动机。
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公开(公告)号：US20200032660A1
公开(公告)日：2020-01-30
申请号：US16047319
申请日：2018-07-27
Applicant: United Technologies Corporation
Inventor： Nicholas D. Stilin
Abstract: A coating membrane for a component of a gas-turbine engine includes a solid membrane having a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface. Also disclosed are a coated component coated with the membrane, and a method for producing a coated component with the membrane.
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