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公开(公告)号：US10472049B2
公开(公告)日：2019-11-12
申请号：US15030787
申请日：2014-05-23
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Scot A. Webb , James J. McPhail
Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.
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公开(公告)号：US20180347463A1
公开(公告)日：2018-12-06
申请号：US16045957
申请日：2018-07-26
Applicant: United Technologies Corporation
Inventor： Thomas W. Ward , Scot A. Webb
CPC classification number: F02C7/047 , F01D25/02 , F05D2300/5024 , Y02T50/672
Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies. A method of de-icing a gas turbine engine is also disclosed.
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公开(公告)号：US20180238233A1
公开(公告)日：2018-08-23
申请号：US15960132
申请日：2018-04-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas W. Ward , Scot A. Webb , Isaac Jon Hogate
CPC classification number: F02C7/047 , F01D15/10 , F01D25/02 , F02C7/32 , F05D2220/76 , H02K7/1823 , H05B3/0014 , H05B3/06
Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil an electrical coil operatively associated with a non-rotating forward assembly of the gas turbine engine; a magnet operatively associated with a rotating surface of the fan, the magnet and the electrical coil producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.
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公开(公告)号：US20170241435A1
公开(公告)日：2017-08-24
申请号：US15051377
申请日：2016-02-23
Applicant: United Technologies Corporation
Inventor： Scot A. Webb
CPC classification number: F04D29/526 , B64D27/26 , B64D2027/266 , F01D25/243 , F02C3/04 , F04D19/00 , F04D29/644 , F05D2220/32 , F05D2240/35 , F05D2250/315
Abstract: An engine case may include a first half and a second half. The first half may have a semiannular geometry with a first flange located at a circumferential edge of the first half. The second half may also have a semiannular geometry. The second half may further include a flange located at a circumferential edge of the first half. The second flange may be aligned with the first flange and mechanically coupled to the first flange. The first flange and the second flange may be configured to substantially align with an engine mounting point. The engine case may also have an annular geometry.
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公开(公告)号：US20160090849A1
公开(公告)日：2016-03-31
申请号：US14826537
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Thomas J. Robertson , Scot A. Webb
CPC classification number: F01D5/288 , F01D5/147 , F05D2220/32 , F05D2220/36 , F05D2300/10 , F05D2300/224 , F05D2300/611 , Y02T50/671
Abstract: The present disclosure relates generally to a fan blade for use in a gas turbine engine, wherein the fan blade includes a metallic fan blade body, including a fan blade body leading edge and body outer surface, extending radially outward from a root, and a static dissipative coating material disposed on the body outer surface.
Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机的风扇叶片，其中风扇叶片包括金属风扇叶片体，其包括从根部径向向外延伸的风扇叶片体前缘和主体外表面，以及静态 设置在身体外表面上的耗散涂料。
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Patent Agency Ranking
公开(公告)号：US10830137B2
公开(公告)日：2020-11-10
申请号：US15960132
申请日：2018-04-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas W. Ward , Scot A. Webb , Isaac Jon Hogate
Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil an electrical coil operatively associated with a non-rotating forward assembly of the gas turbine engine; a magnet operatively associated with a rotating surface of the fan, the magnet and the electrical coil producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.
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公开(公告)号：US20200318489A1
公开(公告)日：2020-10-08
申请号：US16373876
申请日：2019-04-03
Applicant: United Technologies Corporation
Inventor： Scot A. Webb
Abstract: A gas turbine engine assembly includes a compressor including a plurality of rotors, where at least one of the plurality of rotors includes a radial inner sealing surface. A rotating shaft drives rotation of the plurality of rotors, where the rotating shaft includes an annular groove proximate the radial inner sealing surface. A seal is disposed within the annular groove, and the seal comprises at least two annular sections forming a complete circumference. Each of the at least two annular sections are separate parts and include a radially-facing sealing surface engaged to the radial inner sealing surface of the rotor and an annular slot disposed radially inward of the radially-facing sealing surface. A retainer is disposed within the annular slot limiting radial expansion of the at least two annular sections.
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公开(公告)号：US10458428B2
公开(公告)日：2019-10-29
申请号：US14917476
申请日：2014-08-04
Applicant: United Technologies Corporation
Inventor： Lee M. Drozdenko , James O. Hansen , Jesse C. Meyer , John J. Marcin, Jr. , Robert M. Shemenski , Scot A. Webb , Brandon A. Gates , Michael A. Morden
Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.
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公开(公告)号：US10087840B2
公开(公告)日：2018-10-02
申请号：US14781943
申请日：2014-03-31
Applicant: United Technologies Corporation
Inventor： Thomas W. Ward , Scot A. Webb
Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies.
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公开(公告)号：US20180202299A1
公开(公告)日：2018-07-19
申请号：US15408882
申请日：2017-01-18
Applicant: United Technologies Corporation
Inventor： James R. Murdock , James H. Moffitt , Scot A. Webb , Jay Thomas Abraham , Maria C. Kirejczyk
CPC classification number: F01D5/28 , F01D5/3092 , F04D29/023 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/303 , F05D2260/95 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/1616 , F05D2300/50 , Y02T50/671
Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.
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