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公开(公告)号：US12135076B1
公开(公告)日：2024-11-05
申请号：US18375065
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 rotating structure and a support structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The intermediate gears are arranged circumferentially about the axis in an array. Each of the intermediate gears are radially 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 rotating structure forms the carrier. The rotating structure includes a shaft and a rotating structure passage. The support structure circumscribes the shaft with a plenum formed by and radially between the support structure and the shaft. The support structure includes a support structure passage. The plenum fluidly couples the support structure passage to the rotating structure passage.
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公开(公告)号：US11781479B2
公开(公告)日：2023-10-10
申请号：US17313605
申请日：2021-05-06
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Daniel Bernard Kupratis , Christopher J. Hanlon
IPC: F02C7/052
CPC classification number: F02C7/052 , F05D2220/32
Abstract: A gas turbine engine includes a core section including a compressor, a main combustor, and a main turbine. Combustion products from the main combustor drive rotation of the turbine and the compressor. A power turbine is fluidly connected to the main turbine and driven by exhaust from the main turbine. The gas turbine engine further includes a fan section having a fan rotor located fluidly upstream of the core section. The power turbine is operably connected to the fan rotor to drive rotation of the fan rotor via rotation of the power turbine. The gas turbine engine includes a bleed arrangement having one or more bleed passages configured to divert a bleed airflow from the compressor around the main combustor and main turbine, and reintroduce the bleed airflow into the power turbine.
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公开(公告)号：US20250116227A1
公开(公告)日：2025-04-10
申请号：US18376706
申请日：2023-10-04
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Michael G. McCaffrey , Paul R. Hanrahan
Abstract: A particle separator configured to be disposed within a turbine engine diffuser flow path is provided. The particle separator includes a housing that extends between a forward end and an aft end, first and second swirl vane stages, and first and second air flow exits. The first swirl vane stage is configured to cause an air flow passing through the first swirl vane stage to swirl within the housing as the air flow travels axially in a direction from the forward end toward the aft end of the housing. The second swirl vane stage is configured to cause a first portion of the air flow passing through the second swirl vane stage to redirect into a substantially axially directed flow that enters the second air flow exit.
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公开(公告)号：US20250109712A1
公开(公告)日：2025-04-03
申请号：US18374985
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan
IPC: F02C7/36
Abstract: An aircraft assembly includes a geartrain, a first propulsor rotor and a rotating assembly. The geartrain includes a first gear system and a second gear system. The first gear system includes a first sun gear, a first ring gear, a plurality of first intermediate gears and a first carrier. The first intermediate gears are radially between and meshed with the first sun gear and the first ring gear. The second gear system includes a second sun gear, a second ring gear, a plurality of second intermediate gears and a second carrier. The second sun gear is rotatable about the axis with the first sun gear. The second intermediate gears are radially between and meshed with the second sun gear and the second ring gear. The second carrier is coupled to the first ring gear. The rotating assembly is configured to drive rotation of the first propulsor rotor through the geartrain.
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公开(公告)号：US20250109707A1
公开(公告)日：2025-04-03
申请号：US18375011
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan
Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a first propulsor rotor, a geartrain, a rotating assembly and an auxiliary turbine. The rotating assembly is rotatable about an axis and includes a turbine rotor. The rotating assembly is coupled to and is configured to drive rotation of the first propulsor rotor through the geartrain. The auxiliary turbine is coupled to the first propulsor rotor independent of the geartrain.
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Patent Agency Ranking
公开(公告)号：US20250101921A1
公开(公告)日：2025-03-27
申请号：US18973929
申请日：2024-12-09
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a differential geartrain, a first rotating assembly, a second rotating assembly, a first actuator and a second actuator. The differential geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The first rotating assembly is coupled to the differential geartrain through the carrier. The first rotating assembly includes a first turbine rotor. The second rotating assembly is coupled to the differential geartrain through the ring gear. The second rotating assembly includes a second turbine rotor. The first actuator is coupled to the differential geartrain through the ring gear. The second actuator is coupled to the differential geartrain through the sun gear.
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17.发明授权公开(公告)号：US12188551B1
公开(公告)日：2025-01-07
申请号：US18375028
申请日：2023-09-29
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan
IPC: F16H57/04 , F02C7/06 , F02C7/36 , F16H57/029
Abstract: An engine assembly is provided that includes a geartrain, a rotating structure, a support structure and a bearing. The rotating structure is rotatable about an axis. The rotating structure forms a first component of the geartrain. The rotating structure includes a shaft and a rotating structure passage. The support structure circumscribes the shaft with a plenum, where the plenum is formed by and radially between the support structure and the shaft. The support structure includes a support structure passage. The plenum fluidly couples the support structure passage to the rotating structure passage. The bearing rotatably couples the shaft to the support structure.
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公开(公告)号：US20240052784A1
公开(公告)日：2024-02-15
申请号：US18233662
申请日：2023-08-14
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan
CPC classification number: F02C7/32 , B64D35/04 , F02C7/28 , F02C3/04 , F05D2240/55 , F05D2260/4031
Abstract: An assembly is provided for an aircraft. This assembly includes a first rotating structure, a second rotating structure and a seal assembly. The seal assembly is configured to seal an annular gap radially between the first rotating structure and the second rotating structure. The seal assembly includes an arm, a seal element and a seal land. The arm is cantilevered from and extends axially along the second rotating structure. The seal element is connected to the arm and forms a seal interface with the seal land. The seal land is connected to the first rotating structure.
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公开(公告)号：US12253021B2
公开(公告)日：2025-03-18
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：US12071900B2
公开(公告)日：2024-08-27
申请号：US18233636
申请日：2023-08-14
Applicant: RTX Corporation
Inventor： Paul R. Hanrahan , David A. Stachowiak
CPC classification number: F02C7/36 , B64D35/00 , B64D35/04 , F05D2260/4031 , F05D2260/902
Abstract: A first gear system includes a first sun gear, a first ring gear, first intermediate gears and a first carrier. The first intermediate gears are between and meshed with the first sun gear and the first ring gear. Each first intermediate gear is rotatably mounted to the first carrier. A second gear system includes a second sun gear, a second ring gear, second intermediate gears and a second carrier. The second ring gear is coupled to the first carrier. The second intermediate gears are between and meshed with the second sun gear and the second ring gear. Each second intermediate gear is rotatably mounted to the second carrier. A first propulsor rotor is coupled to the first carrier. A rotating structure is coupled to the first ring gear and includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.
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