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公开(公告)号：US20250003367A1
公开(公告)日：2025-01-02
申请号：US18215957
申请日：2023-06-29
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
Abstract: An assembly for rotational equipment includes a shaft, a first rolling-element bearing, a second rolling-element bearing, and a mid-shaft foil bearing. The shaft extends along a rotational axis between and to a first axial end and a second axial end. The shaft is configured for rotation about the rotational axis. The first rolling-element bearing is disposed at the first axial end. The second rolling-element bearing is disposed at the second axial end. The mid-shaft foil bearing is disposed axially between the first rolling-element bearing and the second rolling-element bearing.
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公开(公告)号：US20240401536A1
公开(公告)日：2024-12-05
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：US12092040B2
公开(公告)日：2024-09-17
申请号：US18202727
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: F02C7/36 , B64C27/32 , B64D27/10 , B64D35/00 , F05D2260/40311 , F05D2260/90
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.
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公开(公告)号：US20240060453A1
公开(公告)日：2024-02-22
申请号：US17888955
申请日：2022-08-16
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
IPC: F02C7/32
CPC classification number: F02C7/32 , F05D2220/323 , F05D2220/36 , F05D2260/40311 , B64D2013/0618
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：US20230415902A1
公开(公告)日：2023-12-28
申请号：US17849668
申请日：2022-06-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
Abstract: An aircraft system is provided that includes a first gas turbine engine, a propulsor rotor, a second gas turbine engine, an electric generator and an electric component. The first gas turbine engine includes a first compressor section, a first combustor section, a first turbine section and a first flowpath. The propulsor rotor is rotatably driven by the first gas turbine engine. The second gas turbine engine includes a second compressor section, a second combustor section, a second turbine section and a second flowpath between a second inlet and a second exhaust. The second inlet and the second exhaust are each fluidly coupled with the first flowpath upstream of a combustor of the first combustor section. The electric generator is rotatably driven by the second gas turbine engine. The electric component receives electricity generated by the electric generator. The electric component is discrete from the first gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US20230383695A1
公开(公告)日：2023-11-30
申请号：US18202731
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Michael G. McCaffrey
CPC classification number: F02C6/20 , B64D27/10 , B64D27/24 , F02C9/16 , B64D2027/026
Abstract: A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.
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公开(公告)号：US20230332546A1
公开(公告)日：2023-10-19
申请号：US17721642
申请日：2022-04-15
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis , David Allen Stachowiak
CPC classification number: F02C7/32 , F01D15/08 , F01D15/10 , F01D15/12 , F02C7/36 , F02K3/06 , F02C7/268 , F05D2220/323 , F05D2260/40311
Abstract: A gas turbine engine includes a high speed turbine and a high speed compressor connected by a high speed shaft to define a high speed spool. A low speed turbine and a low speed compressor are connected by a low speed shaft to define a low speed spool. A high speed tower shaft is driven by the high speed spool and a low speed tower shaft is driven by the low speed spool. The low speed tower shaft drives a low speed input gear in an accessory drive differential. The high speed tower shaft drives a high speed input gear in the accessory drive differential. One of the high speed input gear and the low speed input gear increases an output speed of an output gear, and the other decreases an output speed of the output gear. The output gear drives at least one accessory for the gas turbine engine.
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公开(公告)号：US20230235699A1
公开(公告)日：2023-07-27
申请号：US17584909
申请日：2022-01-26
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Paul R. Hanrahan
CPC classification number: F02C7/12 , B64D33/08 , F28D7/0041 , F05D2260/213
Abstract: An aircraft heat exchanger system according to an exemplary embodiment of this disclosure, among other possible things includes a first heat exchanger assembly that is disposed in an inlet duct assembly, and a skin heat exchanger assembly is in thermal communication with an outer surface of an aircraft structure. The skin heat exchanger is in fluid communication with the first heat exchanger such that a working fluid is communicated therebetween.
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公开(公告)号：US11591911B2
公开(公告)日：2023-02-28
申请号：US17238793
申请日：2021-04-23
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
IPC: F01D5/08
Abstract: Gas turbine engines and rotor arms thereof are described. The gas turbine engines include a first disk, a second disk, and a rotor arm arranged between and connecting the first disk to the second disk, wherein a cavity is defined at least between the rotor arm and the first disk. The rotor arm includes a radial portion having an inner diameter end and an outer diameter end, an axial portion having a first end and a second end, wherein the first end of the axial portion is connected to the outer diameter end of the radial portion, at least one entrance flow path defined within the radial portion extending from the inner diameter end to the outer diameter end, and at least one exit aperture arranged proximate the second end of the axial portion.
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公开(公告)号：US20210054809A1
公开(公告)日：2021-02-25
申请号：US16999408
申请日：2020-08-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Mark Tu , Paul R. Hanrahan , Arthur M. Salve, JR.
Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, 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; a high pressure compressor connected to a high pressure compressor spool; and a 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 connected to the high pressure compressor spool.
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