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公开(公告)号：US11441450B2
公开(公告)日：2022-09-13
申请号：US16001699
申请日：2018-06-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jacob Peter Mastro
Abstract: A lubrication system may comprise a shaft including a shaft gear, a pump configured to supply a flow of lubricant to a component benefiting from lubrication and an input gear train coupled to the shaft gear and configured to drive the gear pump with a unidirectional rotation in response to a forward rotation and an reverse rotation of the shaft gear. The input gear grain may comprise a primary gear coupled to a common shaft. The input gear train may further comprise a forward shaft and a forward gear about the common shaft, wherein the forward gear is coupled to the forward shaft.
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公开(公告)号：US11441448B2
公开(公告)日：2022-09-13
申请号：US16789977
申请日：2020-02-13
Applicant: United Technologies Corporation
Inventor： Sin Chien Siw , Timothy Castaldo , Charles Joseph Banas , Jorn Axel Glahn
Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.
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公开(公告)号：US11434822B2
公开(公告)日：2022-09-06
申请号：US15175073
申请日：2016-06-07
Applicant: United Technologies Corporation
Inventor： Michael Ronan
Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive.
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公开(公告)号：US11434774B2
公开(公告)日：2022-09-06
申请号：US16202817
申请日：2018-11-28
Applicant: United Technologies Corporation
Inventor： Lisa P. O'Neill , Amarnath Ramlogan
Abstract: Borescope plugs are described. The borescope plugs include a borescope plug base having a first side configured to support a shank and a second side having a centroid defined as the center of the borescope plug base, a first mounting aperture formed in the second side, and a second mounting aperture formed in the second side. The first and second mounting apertures are configured to each receive a fastener to mount the borescope plug base to a case, and an offset line drawn through the center of the first mounting aperture and through the center of the second mounting aperture does not pass through the centroid or does not include a point defined by the centroid.
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公开(公告)号：US11433322B2
公开(公告)日：2022-09-06
申请号：US16550020
申请日：2019-08-23
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Gregory E. Reinhardt , Daniel A. Szkrybalo
Abstract: A machine has a first member; a second member; a third member; a bearing having an inner race mounted to the second member and an outer race mounted to the third member; a damper chamber between the first member and the third member; a fluid outlet in the first member to the damper chamber; a fluid supply flowpath to the fluid outlet; and an unvented chamber open to and locally above the fluid supply flowpath.
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Patent Agency Ranking
公开(公告)号：US11428162B2
公开(公告)日：2022-08-30
申请号：US16746284
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： Joseph B. Staubach , Amanda J. L. Boucher
Abstract: Gas turbine engines are described. The gas turbine engines includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. A cooling duct is provided that is separate from the core flow path. A waste heat recovery system is arranged with a heat rejection heat exchanger arranged within the cooling duct and a blower is arranged within the cooling duct and configured to generate a pressure drop across the heat rejection heat exchanger.
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公开(公告)号：US11421590B2
公开(公告)日：2022-08-23
申请号：US16656931
申请日：2019-10-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Arthur M. Salve, Jr.
Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
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公开(公告)号：US11415044B2
公开(公告)日：2022-08-16
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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公开(公告)号：US11408296B2
公开(公告)日：2022-08-09
申请号：US16272175
申请日：2019-02-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark E. Simonds , Steven J. Feigleson
Abstract: A vane stage includes an arcuate platform defining an axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.
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公开(公告)号：US11384877B2
公开(公告)日：2022-07-12
申请号：US16257917
申请日：2019-01-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward Guevel
Abstract: A retaining assembly may comprise a bracket assembly having a first end and a second end. The first end may be configured to mount to a clamping band. The retaining assembly may further comprise a retention component. The retention component may have a clevis coupled to the second end. The retaining assembly may be coupled to an otherwise loose external component on a gas turbine engine. The retaining assembly may keep the otherwise loose external component fixed to the gas turbine engine during maintenance operations and prevent the otherwise loose external component from being lost or misplaced.
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