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公开(公告)号：US11236632B2
公开(公告)日：2022-02-01
申请号：US15882051
申请日：2018-01-29
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.
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公开(公告)号：US11168702B2
公开(公告)日：2021-11-09
申请号：US15673635
申请日：2017-08-10
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
IPC: F04D29/38 , F04D29/32 , F04D29/52 , F04D29/66 , F01D5/14 , F01D5/20 , F02K3/06 , F04D25/04 , F01D21/04
Abstract: A fan blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, and extends radially between a root portion and a tip portion. A tip pocket is defined by collapsible external walls of the tip portion, and has a pocket opening at a radially outer face of the tip portion.
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公开(公告)号：US20210222562A1
公开(公告)日：2021-07-22
申请号：US16796248
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 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. The vanes include a first vane that is integral with the first rotor disk and projects axially to the second rotor disk.
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公开(公告)号：US20210207537A1
公开(公告)日：2021-07-08
申请号：US16734925
申请日：2020-01-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A fuel power transfer system for an engine may include a cryogenic fuel supply, a fuel pump in fluid communication with the cryogenic fuel supply, a multi-position valve in fluid communication with the fuel pump and a combustion chamber of the engine, a fuel turbine operatively coupled to the fuel pump and having a primary discharge port in fluid communication with the combustion chamber, a primary heat exchanger in fluid communication between the multi-position valve and the fuel turbine, and a gearbox operatively coupled to the fuel turbine and the fuel pump and configured to transfer power from the fuel turbine to the engine.
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公开(公告)号：US11028697B2
公开(公告)日：2021-06-08
申请号：US14761348
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
IPC: F01D5/02 , F01D5/28 , F01D5/34 , F01D5/22 , F04D29/02 , F04D29/32 , F02K3/06 , F01D5/30 , F04D29/34 , F01D5/14 , F02C3/04
Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.
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Patent Agency Ranking
公开(公告)号：US10927707B2
公开(公告)日：2021-02-23
申请号：US16213395
申请日：2018-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.
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公开(公告)号：US10920671B2
公开(公告)日：2021-02-16
申请号：US16141382
申请日：2018-09-25
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a first spool including a first compressor coupled to a first turbine through a first shaft, a second spool including a second compressor coupled to a second turbine through a second shaft. A first tower shaft is coupled to the first shaft through a first gear assembly and a second tower shaft is coupled to the second shaft through a second gear assembly. A first load generating device is driven by the first tower shaft and a second load generating device is driven by the second tower shaft. A controller controls each of the first load generating device and the second load generating device to vary a proportion of the total load applied to each of the first spool and the second spool to bias a direction of an axial load on each of the first spool and the second spool.
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公开(公告)号：US20200378307A1
公开(公告)日：2020-12-03
申请号：US16426260
申请日：2019-05-30
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section where the turbine section is downstream of the combustor section. A shaft connects the turbine section to the compressor section. A bore tube is disposed within the shaft downstream of the compressor section. The bore tube includes an inlet connected to an air source for passing cooling air in an upstream direction of the shaft.
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公开(公告)号：US10815885B2
公开(公告)日：2020-10-27
申请号：US16046090
申请日：2018-07-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
Abstract: An anti-ice system for a gas turbine engine may comprise a power generating device and a first thermally conductive applique comprising a first heating circuit. The power generating device may comprise a first component configured to rotate about an axis and generate a current. A first conductive layer may electrically couple the first heating circuit and the first component of the power generating device.
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公开(公告)号：US10814445B2
公开(公告)日：2020-10-27
申请号：US15149543
申请日：2016-05-09
Applicant: United Technologies Corporation
Inventor： Gary D. Roberge
IPC: B23Q3/08 , B23Q3/06 , B23Q11/12 , B23Q17/22 , F01D5/14 , F01D5/30 , F04D29/32 , F04D29/34 , F04D29/38
Abstract: Disclosed is a method for machining a component, comprising: installing the component on a fixture, causing a medium of the fixture to solidify to encase a first portion of the component, applying a toolset to a second portion of the component that is outside of the solidified medium, and subsequent to applying the toolset, extracting the component from the fixture when the medium is in one of a liquid state or a semi-liquid state, where the medium has a melting-point temperature that is less than 500 degrees Fahrenheit. Disclosed is a fixture for machining a component, comprising: a medium configured to encase a first portion of the component when the medium is in a solidified state, and a toolset configured to be applied to a second portion of the component that is outside of the solidified medium, the medium having a melting-point temperature that is less than 500 degrees Fahrenheit.
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