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公开(公告)号：US20220228506A1
公开(公告)日：2022-07-21
申请号：US17711177
申请日：2022-04-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.
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公开(公告)号：US11313278B2
公开(公告)日：2022-04-26
申请号：US16909490
申请日：2020-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
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公开(公告)号：US20220074353A1
公开(公告)日：2022-03-10
申请号：US17532085
申请日：2021-11-22
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier, positioning baffles between side walls of the carrier such that an end of each of the baffles abuts a respective mount of the carrier, inserting intermediate gears through a central opening of the carrier, and then moving the intermediate gears radially outwardly into respective gear pockets of the carrier, inserting a sun gear through the central opening, moving the intermediate gears radially inwardly to engage the sun gear, coupling a shaft to the carrier, including attaching a torque frame to the carrier such that the torque frame interconnects the carrier and the shaft, placing first and second ring gear halves of a ring gear onto an outer periphery of the intermediate gears, and fixedly attaching the ring gear to an engine static structure. A gear system is also disclosed.
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公开(公告)号：US20220010736A1
公开(公告)日：2022-01-13
申请号：US17484331
申请日：2021-09-24
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
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Patent Agency Ranking
公开(公告)号：US11221066B2
公开(公告)日：2022-01-11
申请号：US17038724
申请日：2020-09-30
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Lawrence E. Portlock
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a turbo fan supported on a turbo fan shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the turbo fan shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth, the first and second portions arranged about and intermeshing with the intermediate gears, the first and second portions abutting one another at a radial interface, the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, and the teeth of the first and second portions being oppositely angled teeth.
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公开(公告)号：US11156166B2
公开(公告)日：2021-10-26
申请号：US16180548
申请日：2018-11-05
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
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公开(公告)号：US11060417B2
公开(公告)日：2021-07-13
申请号：US16409167
申请日：2019-05-10
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune
Abstract: A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end.
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公开(公告)号：US20210079843A1
公开(公告)日：2021-03-18
申请号：US16909490
申请日：2020-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
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公开(公告)号：US20210017936A1
公开(公告)日：2021-01-21
申请号：US17062197
申请日：2020-10-02
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft. A plurality of planetary gears and a first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. A gear system support is relative to a fixed housing facilitating segregation of vibrations. An annular channel is axially aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
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