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公开(公告)号：US12292006B2
公开(公告)日：2025-05-06
申请号：US18233615
申请日：2023-08-14
Applicant: RTX Corporation
Inventor： Jui-Lin Chang , Paul R. Hanrahan
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an engine core, a bypass duct and a bleed circuit. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The bypass duct includes a bypass flowpath outside of the engine core. The bleed circuit includes a bleed passage and a flow regulator. The bleed circuit is configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position. The bleed circuit is configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position.
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公开(公告)号：US20250109708A1
公开(公告)日：2025-04-03
申请号：US18375102
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan
Abstract: An engine assembly is provided that includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first rotating structure, a second rotating structure and a first bearing. The ring gear is rotatable about an axis and circumscribes the sun gear. The intermediate gears are arranged circumferentially about the axis in an array. Each of the intermediate gears is radially between and meshed with the sun gear and the ring gear. The carrier is rotatable about the axis. Each of the intermediate gears is rotatably mounted to the carrier. The first rotating structure is configured as or otherwise includes the carrier. The second rotating structure is configured as or otherwise includes the ring gear. The first bearing is radially between and engaged with the first rotating structure and the second rotating structure.
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公开(公告)号：US20250058888A1
公开(公告)日：2025-02-20
申请号：US18233620
申请日：2023-08-14
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Benjamin T. Mylrea , David A. Stachowiak
Abstract: An assembly is provided for an aircraft. This assembly includes a geartrain, a first propulsor rotor and a rotating structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The ring gear circumscribes the sun gear and is rotatable about an axis. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The carrier is rotatable about the axis. The first propulsor rotor is coupled to the carrier. The rotating structure is coupled to the ring gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.
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公开(公告)号：US20240384682A1
公开(公告)日：2024-11-21
申请号：US18405801
申请日：2024-01-05
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
Abstract: A gas turbine engine includes a first spool, a second spool, a third spool, and a epicyclic differential. The epicyclic differential includes a sun gear, planet gears supported from a planet carrier, a ring gear, and a locking member, each housed within an accessory gearbox. The planet carrier couples to the second spool. The sun gear couples to the third spool, and the ring gear couples to engine accessories. A method of operating the gas turbine engine includes supplying a first fuel flow rate to a primary combustor associated with the first and third spools and supplying a second fuel flow rate to a secondary combustor associated with the second spool based on a power lever angle within an intermediate power level range.
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公开(公告)号：US20240052790A1
公开(公告)日：2024-02-15
申请号：US18233615
申请日：2023-08-14
Applicant: RTX Corporation
Inventor： Jui-Lin Chang , Paul R. Hanrahan
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an engine core, a bypass duct and a bleed circuit. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The bypass duct includes a bypass flowpath outside of the engine core. The bleed circuit includes a bleed passage and a flow regulator. The bleed circuit is configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position. The bleed circuit is configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position.
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Patent Agency Ranking
公开(公告)号：US12292107B2
公开(公告)日：2025-05-06
申请号：US18375132
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Robert G. Murphy, II
Abstract: An engine assembly is provided that includes a geartrain, a device and a fluid damper. The geartrain is configured as or otherwise includes an epicyclic gear system. A first component of the geartrain is rotatable about an axis. The device is configured to brake and/or lock rotation of the first component of the geartrain about the axis. The device is configured as or otherwise includes a device structure. The fluid damper engages the device structure. The fluid damper is configured to damp vibrations in the device.
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公开(公告)号：US11840958B2
公开(公告)日：2023-12-12
申请号：US17393508
申请日：2021-08-04
Applicant: RTX Corporation
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Christopher J. Hanlon
Abstract: A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.
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公开(公告)号：US20250162709A1
公开(公告)日：2025-05-22
申请号：US18512719
申请日：2023-11-17
Applicant: RTX Corporation
Inventor： Daniel B. Kupratis , Paul R. Hanrahan , Benjamin T. Mylrea
Abstract: A system is provided for an aircraft. This aircraft system includes an aircraft and an air system. The airframe includes a body and a vane connected to the body. The vane projects spanwise away from the body to a vane tip. The vane extends longitudinally between a leading edge and a trailing edge. The vane extends laterally between a first vane side and a second vane side. The air system includes a circuit inlet, a circuit outlet and an air circuit. The circuit inlet is arranged with the body and laterally offset from the vane. The circuit outlet is arranged with the vane. The air circuit extends within the airframe from the circuit inlet to the circuit outlet.
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公开(公告)号：US20250109784A1
公开(公告)日：2025-04-03
申请号：US18375132
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Robert G. Murphy, II
Abstract: An engine assembly is provided that includes a geartrain, a device and a fluid damper. The geartrain is configured as or otherwise includes an epicyclic gear system. A first component of the geartrain is rotatable about an axis. The device is configured to brake and/or lock rotation of the first component of the geartrain about the axis. The device is configured as or otherwise includes a device structure. The fluid damper engages the device structure. The fluid damper is configured to damp vibrations in the device.
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公开(公告)号：US12173644B2
公开(公告)日：2024-12-24
申请号：US18364422
申请日：2023-08-02
Applicant: RTX 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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