-
公开(公告)号：US20220003164A1
公开(公告)日：2022-01-06
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.
-
公开(公告)号：US20240401537A1
公开(公告)日：2024-12-05
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.
-
公开(公告)号：US12043405B2
公开(公告)日：2024-07-23
申请号：US18202736
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: B64D35/02 , F02C7/36 , B64D27/026 , F05D2260/40311
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.
-
公开(公告)号：US11952949B2
公开(公告)日：2024-04-09
申请号：US17903699
申请日：2022-09-06
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: F02C7/36 , B64D27/10 , F16H37/065 , F16H57/10
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a carrier, a first gear system, a second gear system and a lock device. The first gear system includes a sun gear, a first ring gear and a plurality of first intermediate gears between and meshed with the 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 ring gear and a plurality of second intermediate gears meshed with the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The lock device is configured to lock rotation of the carrier about an axis during a first mode. The lock device is configured to unlock rotation of the carrier about the axis during a second mode.
-
公开(公告)号：US20240077034A1
公开(公告)日：2024-03-07
申请号：US17903699
申请日：2022-09-06
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: F02C7/36 , B64D27/10 , F16H37/065 , F16H57/10
Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a carrier, a first gear system, a second gear system and a lock device. The first gear system includes a sun gear, a first ring gear and a plurality of first intermediate gears between and meshed with the 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 ring gear and a plurality of second intermediate gears meshed with the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The lock device is configured to lock rotation of the carrier about an axis during a first mode. The lock device is configured to unlock rotation of the carrier about the axis during a second mode.
-
Patent Agency Ranking
公开(公告)号：US20240052786A1
公开(公告)日：2024-02-15
申请号：US17980670
申请日：2022-11-04
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Benjamin T. Mylrea , David A. Stachowiak
CPC classification number: F02C7/36 , B64D35/00 , F05D2260/4031
Abstract: An aircraft assembly includes a geartrain with 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 sun gear and the first ring gear are each rotatable about an axis. The first intermediate gears are between and meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the first carrier. The second gear system is interconnected with the first gear system. 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 intermediate gears are between and meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the second carrier.
-
公开(公告)号：US11891953B2
公开(公告)日：2024-02-06
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.
-
公开(公告)号：US20230383700A1
公开(公告)日：2023-11-30
申请号：US18202727
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan
CPC classification number: F02C7/36 , B64D27/10 , B64C27/32 , 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.
-
公开(公告)号：US20230358165A1
公开(公告)日：2023-11-09
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 , F05D2260/40311 , F05D2220/323 , 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.
-
公开(公告)号：US11506146B2
公开(公告)日：2022-11-22
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.
-
-
-
-
-
-
-
-
-
Search Results
55
records
(took 0.025 seconds)
