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公开(公告)号：US20190101061A1
公开(公告)日：2019-04-04
申请号：US15722000
申请日：2017-10-02
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.
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公开(公告)号：US20180038378A1
公开(公告)日：2018-02-08
申请号：US15229423
申请日：2016-08-05
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
IPC: F04D29/051 , F16C27/08 , F16C19/54 , F04D29/059 , F16C19/52
CPC classification number: F04D29/051 , F01D25/164 , F04D29/059 , F16C19/525 , F16C19/54 , F16C19/542 , F16C25/083 , F16C27/045 , F16C27/08 , F16C2360/23
Abstract: A bearing system for a gas turbine engine includes an outer housing and a first ball bearing assembly disposed radially inward from the outer housing relative a center axis of the outer housing. The bearing system also includes a second ball bearing assembly disposed radially inward from the outer housing and positioned axially aft of the first ball bearing assembly. The bearing system also includes a resilient member that is connected to the outer housing and compressed against at least one of a first outer race of the first ball bearing assembly and a second outer race of the second ball bearing assembly in an axial direction parallel to the center axis.
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公开(公告)号：US20160290151A1
公开(公告)日：2016-10-06
申请号：US15037127
申请日：2014-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock , Enzo DiBenedetto
Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.
Abstract translation: 密封件包括壳体。 涂层具有至少两层，其中结合层定位在壳体和第二硬质层之间。 第二硬层形成为比接合层更硬。 接合层具有大于或等于200psi且小于或等于2000psi的粘合强度。 还公开了一种燃气涡轮发动机，以及形成涂层的方法。
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34.发明授权公开(公告)号：US11293298B2
公开(公告)日：2022-04-05
申请号：US16704642
申请日：2019-12-05
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre , Horacio Antonio Altagracia
Abstract: A compressor case to blade tip clearance system comprising a rotor having blades with tips, the case including an inner case comprising at least one surface feature fluidly coupled to a distribution manifold disposed in a cooling air passageway, the at least one surface feature configured to interact with the cooling air, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of the cooling air over the at least one surface feature.
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公开(公告)号：US11131195B2
公开(公告)日：2021-09-28
申请号：US16353182
申请日：2019-03-14
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Griffin D. Lavine
Abstract: A tie shaft assembly for a gas turbine engine includes a compressor tie shaft that has an upstream end and a downstream end. The downstream end includes a radially outer threaded surface and a radially inner threaded surface. A turbine tie shaft has an upstream end with a radially outer threaded surface in engagement with the radially inner threaded surface on the compressor tie shaft.
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Patent Agency Ranking
公开(公告)号：US11073044B2
公开(公告)日：2021-07-27
申请号：US13745943
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Enzo DiBenedetto
Abstract: A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan. An oil channel collects oil thrown outwardly of the gear drive. A bearing support mounts bearings supporting the fan drive shaft. The oil channel and the bearing support each include mating faces that are bolted together by a plurality of bolts. The bolts extend through oil channel holes in the mating face of the oil channel. The oil channel holes have one dimension which closely receives the bolts and another dimension which is larger than an outer diameter of the extending portion of the bolts, such that the bolts may adjust radially within the oil channel holes.
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公开(公告)号：US10767485B2
公开(公告)日：2020-09-08
申请号：US15864925
申请日：2018-01-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E Bintz , Enzo DiBenedetto , Paul E Coderre
Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
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公开(公告)号：US10473028B2
公开(公告)日：2019-11-12
申请号：US15651497
申请日：2017-07-17
Applicant: United Technologies Corporation
Inventor： John C. DiTomasso , Enzo DiBenedetto
IPC: F01D5/00 , F02C3/113 , F04D29/26 , F02C9/00 , F04D29/053 , F16D27/10 , F16D35/00 , F01D5/06 , F04D19/02 , F04D25/02 , F02C7/36
Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.
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公开(公告)号：US10400629B2
公开(公告)日：2019-09-03
申请号：US14012576
申请日：2013-08-28
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Todd A. Davis , Gregory E. Reinhardt , Enzo DiBenedetto
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
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公开(公告)号：US20190017436A1
公开(公告)日：2019-01-17
申请号：US15651497
申请日：2017-07-17
Applicant: United Technologies Corporation
Inventor： John C. DiTomasso , Enzo DiBenedetto
Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.
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