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公开(公告)号：US11519368B2
公开(公告)日：2022-12-06
申请号：US16736342
申请日：2020-01-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Curtis C. Cowan , Rebecca R. Dunnigan , Gary D. Roberge
Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.
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公开(公告)号：US11479861B2
公开(公告)日：2022-10-25
申请号：US16688824
申请日：2019-11-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge , William J. Brindley
Abstract: A method for forming a metallic structure having a secondary component includes positioning the secondary component on a main formation surface of a main tool, the main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing a layer of material on the secondary component and the main formation surface using a cold-spray technique such that the layer of material bonds to the secondary component. The method also includes removing the layer of material and the secondary component to form the metallic structure.
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公开(公告)号：US11339673B2
公开(公告)日：2022-05-24
申请号：US16796268
申请日：2020-02-20
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.
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公开(公告)号：US11078843B2
公开(公告)日：2021-08-03
申请号：US15993675
申请日：2018-05-31
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge , Jorn Axel Glahn
Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.
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公开(公告)号：US20210222574A1
公开(公告)日：2021-07-22
申请号：US16746286
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A rotor blade is provided for a gas turbine engine. This rotor blade includes a rotor blade pair including a mount, a first airfoil and a second airfoil. The mount includes a forked body with a first leg and a second leg. The first airfoil is connected to the first leg. The second airfoil is connected to the second leg and arranged circumferentially next to the first airfoil.
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Patent Agency Ranking
公开(公告)号：US10989117B2
公开(公告)日：2021-04-27
申请号：US16131712
申请日：2018-09-14
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system.
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公开(公告)号：US10801410B2
公开(公告)日：2020-10-13
申请号：US15951527
申请日：2018-04-12
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.
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公开(公告)号：US10746181B2
公开(公告)日：2020-08-18
申请号：US15242701
申请日：2016-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.
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公开(公告)号：US20200248314A1
公开(公告)日：2020-08-06
申请号：US16706083
申请日：2019-12-06
Applicant: United Technologies Corporation
Inventor： William J. Brindley , Gary D. Roberge
Abstract: A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. The method also includes positioning a secondary tool having a secondary formation surface in a portion of a first volume defined by a first surface of the first layer of material. The method also includes depositing a second layer of material on the secondary formation surface using the cold-spray deposition technique. The method also includes removing the secondary tool such that the first volume is positioned between the first layer of material and the second layer of material.
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公开(公告)号：US10724543B2
公开(公告)日：2020-07-28
申请号：US15674646
申请日：2017-08-11
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A variable-pitch vane system for a gas turbine engine includes a plurality of vanes and a synchronization ring assembly operably connected to the plurality of vanes. The synchronization ring assembly includes a first synchronization ring, a second synchronization ring and a bridge bracket connecting the first synchronization ring to the second synchronization ring. The bridge bracket includes a first face sheet, a second face sheet, a honeycomb core located between the first face sheet and the second face sheet, a first attachment feature located at a first end of the bridge bracket at which the first synchronization ring is secured, and a second attachment feature located at a second end of the bridge bracket at which the second synchronization ring is secured.
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