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公开(公告)号：US10920591B2
公开(公告)日：2021-02-16
申请号：US16592512
申请日：2019-10-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey Leon , William Indoe , Kimberly Caruso , Brian J. Burke , Fabian D. Betancourt , Kurt Leach
Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion. A base portion of the bore includes a spool engagement surface, a first arm extending in an aft direction and a second arm extending in a fore direction and a radially extending first transition portion connecting an aft end of the spool engagement surface to a radially inward portion of the first arm and a radially extending second transition portion connecting a fore end of the spool engagement surface to a radially inward portion of the second arm.
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公开(公告)号：US10472968B2
公开(公告)日：2019-11-12
申请号：US15694488
申请日：2017-09-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey Leon , William Indoe , Kimberly Caruso , Brian J. Burke , Fabian D. Betancourt , Kurt Leach
Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion. A base portion of the bore includes a spool engagement surface, a first arm extending in an aft direction and a second arm extending in a fore direction and a radially extending first transition portion connecting an aft end of the spool engagement surface to a radially inward portion of the first arm and a radially extending second transition portion connecting a fore end of the spool engagement surface to a radially inward portion of the second arm.
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公开(公告)号：US20160237854A1
公开(公告)日：2016-08-18
申请号：US15027027
申请日：2014-10-06
Applicant: United Technologies Corporation
Inventor： Fernando K. Grant , Fabian D. Betancourt
CPC classification number: F01D25/145 , F01D15/10 , F01D25/243 , F01D25/30 , F02C3/10 , F05D2220/32 , F05D2240/15 , F05D2240/35 , F05D2260/231
Abstract: A gas turbine engine comprises an exhaust section member, a turbine section member, a heat shield and a spacer. The turbine section member is coupled to the exhaust section member. The heat shield is retained between the exhaust section member and the turbine section member. The spacer is positioned between the exhaust section member and the turbine section member to produce a gap for the heat shield. In one embodiment, the exhaust section member comprises a duct and the turbine section member comprises a bearing support.
Abstract translation: 燃气涡轮发动机包括排气部件，涡轮部件，隔热罩和间隔件。 涡轮部分构件联接到排气部件。 隔热罩保持在排气部件和涡轮部件之间。 间隔件定位在排气部件和涡轮部件之间以产生用于隔热罩的间隙。 在一个实施例中，排气部件包括管道，涡轮机部件包括轴承座。
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公开(公告)号：US10550702B2
公开(公告)日：2020-02-04
申请号：US15694499
申请日：2017-09-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey Leon , William Indoe , Kimberly Caruso , Brian J. Burke , Kurt Leach , Fabian D. Betancourt
Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.
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Patent Agency Ranking
公开(公告)号：US20190101022A1
公开(公告)日：2019-04-04
申请号：US15720523
申请日：2017-09-29
Applicant: United Technologies Corporation
Inventor： San Quach , Jeffrey C. Strausbaugh , Fabian D. Betancourt , Joseph J. Sedor , Jonathan A. Scott , Major D. Jones
Abstract: Aspects of the disclosure are directed to a case for a gas turbine engine, the case including a case wall and a boss that extends from the case wall, the boss including a distal top contoured surface with a through hole fotmed there in, the distal top contoured surface having a non-uniform radial wall thickness.
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公开(公告)号：US10208622B2
公开(公告)日：2019-02-19
申请号：US15027027
申请日：2014-10-06
Applicant: United Technologies Corporation
Inventor： Fernando K. Grant , Fabian D. Betancourt
Abstract: A gas turbine engine comprises an exhaust section member, a turbine section member, a heat shield and a spacer. The turbine section member is coupled to the exhaust section member. The heat shield is retained between the exhaust section member and the turbine section member. The spacer is positioned between the exhaust section member and the turbine section member to produce a gap for the heat shield. In one embodiment, the exhaust section member comprises a duct and the turbine section member comprises a bearing support.
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公开(公告)号：US10724374B2
公开(公告)日：2020-07-28
申请号：US15694475
申请日：2017-09-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey Leon , William Indoe , Kimberly Caruso , Brian J. Burke , Fabian D. Betancourt , Kurt Leach
Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore disposed about the central axis, a rim and a web disposed radially between the bore and the rim. The bore has a fore surface and an aft surface. The aft surface of the bore may include an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and an aft base transition portion radially inward of the aft ramp portion. The fore surface of the bore may include a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and a fore base transition portion radially inward of the fore ramp portion. The aft ramp portion includes a substantially linear portion and the fore ramp portion includes a substantially linear portion.
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公开(公告)号：US10544677B2
公开(公告)日：2020-01-28
申请号：US15694420
申请日：2017-09-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jeffrey Leon , William Indoe , Kimberly Caruso , Kurt Leach , Fabian D. Betancourt , Brian J. Burke
Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.
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公开(公告)号：US20180038241A1
公开(公告)日：2018-02-08
申请号：US15231023
申请日：2016-08-08
Applicant: United Technologies Corporation
Inventor： Fabian D. Betancourt , Amarnath Ramlogan , Lisa P. O'Neill
CPC classification number: F01D21/003 , F01D9/041 , F01D11/003 , F01D25/24 , F05D2220/32 , F05D2260/30 , F05D2260/80 , F05D2260/941
Abstract: A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster. The base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity.
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