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公开(公告)号：US12253026B1
公开(公告)日：2025-03-18
申请号：US18133709
申请日：2023-04-12
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
Abstract: A rear bearing air cooling system including an engine inlet section housing a nose cone; a central rotor shaft interior of the nose cone; a rear bearing supporting the central rotor shaft; and a cooling air passage formed through the nose cone and the central rotor shaft, the cooling air passage in fluid communication with the nose cone, the rear bearing and a nose cone vent.
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公开(公告)号：US12203413B1
公开(公告)日：2025-01-21
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：US12195191B2
公开(公告)日：2025-01-14
申请号：US17535200
申请日：2021-11-24
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Paul R. Hanrahan , Joseph B. Staubach , Jill Klinowski
Abstract: A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.
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公开(公告)号：US12158112B1
公开(公告)日：2024-12-03
申请号：US18205333
申请日：2023-06-02
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Gregory E. Reinhardt
Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a geartrain, a first bladed rotor, a second bladed 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 bladed rotor is coupled to the ring gear. The second bladed rotor is coupled to the carrier. The rotating structure is coupled to the sun gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first bladed rotor and the second bladed rotor through the geartrain.
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公开(公告)号：US11958624B2
公开(公告)日：2024-04-16
申请号：US18202734
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: B64D35/04 , B64D35/02 , F02C7/36 , B64D2027/026
Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a carrier, a first gear system, a second gear system and an idler. The first gear system includes a first sun gear, a first ring gear and a plurality of first intermediate gears. Each of the first intermediate gears is between and is meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the carrier. The second gear system includes a second sun gear, a second ring gear and a plurality of second intermediate gears. Each of the second intermediate gears is between and is meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The idler gear couples the first ring gear to the second ring gear.
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Patent Agency Ranking
公开(公告)号：US11898490B2
公开(公告)日：2024-02-13
申请号：US17662195
申请日：2022-05-05
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
CPC classification number: F02C3/107 , F02C7/32 , F02C9/28 , F02C9/40 , F05D2220/323 , F05D2260/40311 , F05D2270/304
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：US20230358176A1
公开(公告)日：2023-11-09
申请号：US17662204
申请日：2022-05-05
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
CPC classification number: F02C7/36 , F02C9/26 , F05D2220/32 , F05D2240/35 , F05D2260/4031
Abstract: A gas turbine engine includes a first spool associated with a primary combustor, a second spool associated with a secondary combustor, and a third spool, each spool including a compressor and a turbine mounted to a shaft. A transmission and accessory gearing are enclosed within an housing of an accessory gearbox. The transmission rotationally couples the third spool to the second spool and accessory gearing. A method of operating the gas turbine engine includes supplying a first fuel flow rate to the primary combustor and supplying a second fuel flow rate to the secondary combustor within an intermediate speed range of the gas turbine engine.
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公开(公告)号：US11781506B2
公开(公告)日：2023-10-10
申请号：US16891492
申请日：2020-06-03
Applicant: Raytheon Technologies Corporation
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan
IPC: F02K3/075 , F02K3/077 , F02K1/72 , F02K3/06 , F02C3/107 , F02K3/068 , F04D29/66 , F04D29/54 , F01D5/14
CPC classification number: F02K3/077 , F02K3/075 , F01D5/145 , F02K1/72 , F02K3/06 , F04D29/542 , F04D29/661
Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.
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公开(公告)号：US11692491B1
公开(公告)日：2023-07-04
申请号：US17662193
申请日：2022-05-05
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel B. Kupratis
CPC classification number: F02C7/32 , F02C7/36 , F05D2220/323 , F05D2260/4031 , F05D2260/53 , F05D2270/023 , F05D2270/07
Abstract: A gas turbine engine includes a first spool rotationally coupled to a plurality of accessories via a first gearing and a second spool rotationally coupled to a third spool via a second gearing. The first gearing and the second gearing rotate independently and are enclosed within a housing of an accessory gearbox. 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 supply a second fuel flow rate 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：US11674548B2
公开(公告)日：2023-06-13
申请号：US16913019
申请日：2020-06-26
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Paul R. Hanrahan
IPC: F16C27/04 , F01D25/16 , F16C35/077
CPC classification number: F16C27/04 , F01D25/164 , F16C35/077 , F16C2360/23
Abstract: A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.
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