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公开(公告)号：US20230037652A1
公开(公告)日：2023-02-09
申请号：US17393508
申请日：2021-08-04
Applicant: Raytheon Technologies 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：US12244209B2
公开(公告)日：2025-03-04
申请号：US18207522
申请日：2023-06-08
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
Abstract: An aircraft system is provided that includes a first turbine engine, a second turbine engine and an electrical system. The electrical system includes a clutch, a first electric machine and a second electric machine electrically coupled to the first electric machine. The first electric machine is mechanically coupled to a first rotating assembly of the first turbine engine. The second electric machine is mechanically coupled to a second rotating assembly of the second turbine engine through the clutch.
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公开(公告)号：US12163476B1
公开(公告)日：2024-12-10
申请号：US18205345
申请日：2023-06-02
Applicant: Raytheon Technologies 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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公开(公告)号：US11939926B2
公开(公告)日：2024-03-26
申请号：US17888955
申请日：2022-08-16
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The assembly also includes a rotating structure, a geartrain, a propulsor rotor and a turbine. The rotating structure includes a turbine rotor within the turbine section. The geartrain is coupled to the rotating structure. The propulsor rotor is coupled to the geartrain. The rotating structure is configured to drive rotation of the propulsor rotor through the geartrain. The turbine is coupled to the geartrain. The turbine is configured to receive bleed gas from the flowpath.
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公开(公告)号：US20240077033A1
公开(公告)日：2024-03-07
申请号：US17903681
申请日：2022-09-06
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2220/323 , F05D2260/40311 , F05D2260/902
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The assembly also includes a turbine rotor, a propulsor rotor and an auxiliary turbine. The turbine rotor is within the turbine section. The turbine rotor is configured to rotatably drive the propulsor rotor. The auxiliary turbine includes an auxiliary turbine rotor. The auxiliary turbine rotor is configured to rotatably drive the propulsor rotor with the turbine rotor. The auxiliary turbine is configured to receive bleed gas from the flowpath.
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Patent Agency Ranking
公开(公告)号：US20230382548A1
公开(公告)日：2023-11-30
申请号：US18202736
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: B64D35/04 , F02C7/36 , B64D35/02 , B64D2027/026
Abstract: An assembly is provided for an aircraft. The aircraft assembly includes a rotating structure, a geartrain, a propulsor rotor and an electric machine. The rotating structure includes a turbine rotor. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The sun gear is rotatably driven by the rotating structure. 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 propulsor rotor is rotatably driven by the carrier. The electric machine is coupled to the ring gear.
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公开(公告)号：US11692493B1
公开(公告)日：2023-07-04
申请号：US17662199
申请日：2022-05-05
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Stephen K. Kramer , Daniel B. Kupratis
Abstract: A gas turbine engine includes a first spool associated with a diffuser and a primary combustor and a second spool associated with a secondary combustor. The first spool includes a first compressor and a first turbine mounted to a first shaft, and the second spool includes a second compressor and a second turbine mounted to a second shaft. An inlet duct fluidly connects the diffuser to the second compressor. An outlet duct assembly fluidly connects the second turbine to the diffuser and the primary combustor.
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公开(公告)号：US11408343B1
公开(公告)日：2022-08-09
申请号：US17313618
申请日：2021-05-06
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel Bernard Kupratis
IPC: F02K3/02 , F02K3/077 , F02K3/11 , F02C7/36 , F02C7/052 , B64D27/10 , F02C6/20 , F02C9/18 , B64C27/12
Abstract: A turboshaft engine includes a core section extending between an inlet and an outlet of the turboshaft engine. The core section includes a compressor, a main combustor, and a main turbine, such that combustion products from the main combustor drives 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. A primary bypass is fluidly connected to the inlet and the outlet. The primary bypass directs a portion of an airflow entering the inlet around the core section to the outlet. A secondary bypass is located in the core section and is configured to divert a portion of a core airflow of the core section around the main combustor and the main turbine to the power turbine.
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公开(公告)号：US11268442B2
公开(公告)日：2022-03-08
申请号：US16918225
申请日：2020-07-01
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Paul R. Hanrahan
Abstract: A shaft and sleeve assembly of a gas turbine engine includes an outer shaft extending about an engine central longitudinal axis and having a radially inner shaft surface. The radially inner shaft surface has a shaft groove define therein. A sleeve is located radially inboard of the radially inner shaft surface. The sleeve includes a sleeve groove defined in a radially outer sleeve surface. The sleeve groove is formed at an axial location between a first axial end and a second axial end of the sleeve. A retaining element is installed in the shaft groove and the sleeve groove to retain the sleeve relative to the outer shaft. The sleeve includes one or more sleeve openings formed therein, and the sleeve groove is aligned with the one or more sleeve openings.
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公开(公告)号：US20220056870A1
公开(公告)日：2022-02-24
申请号：US17350767
申请日：2021-06-17
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan
Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, a first electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft, and an electric compressor extending along a second axis that is radially offset from the central longitudinal axis, the electric compressor in fluid communication with the second turbine section.
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