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公开(公告)号：US11208958B2
公开(公告)日：2021-12-28
申请号：US16939291
申请日：2020-07-27
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.
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公开(公告)号：US11187160B2
公开(公告)日：2021-11-30
申请号：US16878114
申请日：2020-05-19
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine comprises a fan drive turbine driving a shaft. The shaft engages a gear reduction. The gear reduction drives a fan rotor at a speed that is less than the speed of the fan drive turbine. The gear reduction is a non-epicyclic gear reduction.
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公开(公告)号：US20210339880A1
公开(公告)日：2021-11-04
申请号：US17376675
申请日：2021-07-15
Applicant: Raytheon Technologies Corporation
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US20210239052A1
公开(公告)日：2021-08-05
申请号：US17236850
申请日：2021-04-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
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公开(公告)号：US20210140373A1
公开(公告)日：2021-05-13
申请号：US16939291
申请日：2020-07-27
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.
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Patent Agency Ranking
公开(公告)号：US12018574B2
公开(公告)日：2024-06-25
申请号：US18358524
申请日：2023-07-25
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F01D25/18 , B01D19/0068 , B01D19/0073 , F01D25/20 , F02C7/06 , F05D2260/609 , Y02T50/60
Abstract: A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.
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公开(公告)号：US11725589B2
公开(公告)日：2023-08-15
申请号：US17085616
申请日：2020-10-30
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F02C7/36 , F01D25/20 , F02C3/04 , F02C7/06 , F16N39/002 , F01M2013/0427 , F05D2260/40311 , F05D2260/608 , F05D2260/98 , Y02T50/60
Abstract: A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides. A method of designing a gas turbine engine is also disclosed.
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公开(公告)号：US11697999B2
公开(公告)日：2023-07-11
申请号：US18074560
申请日：2022-12-05
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan , William P. Ogden
CPC classification number: F01D15/12 , F02C3/04 , F02C7/06 , F02C7/36 , F02C9/18 , F02K3/06 , F16H57/0482 , F05D2220/323 , F05D2230/10 , F05D2230/232 , F05D2230/60 , F05D2230/90 , F05D2260/31 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F05D2300/141 , F05D2300/171 , F05D2300/2284 , F16H1/28 , Y02T50/60
Abstract: A gas turbine engine includes a propulsor and a fan drive turbine. The fan drive turbine drives the propulsor through a geared architecture. The geared architecture includes a sun gear, a ring gear, and intermediate gears supported on journal support pins. The sun gear engages the intermediate gears and the intermediate gears engages the ring gear. The journal support pins include a titanium body and an outer surface outside of the titanium body that has a surface hardness that is harder than the titanium body. The outer surface is provided by a steel sleeve. Oil supply holes extend from a central bore in the titanium body through the steel sleeve. At least one pin extends through the steel sleeve to secure the steel sleeve to the titanium body.
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公开(公告)号：US11597527B2
公开(公告)日：2023-03-07
申请号：US17376675
申请日：2021-07-15
Applicant: Raytheon Technologies Corporation
IPC: F02C6/14 , B64D27/24 , B64D27/10 , F01D15/10 , F02C7/36 , H02K7/18 , B64D27/02 , F02C6/02 , F02C3/107
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US11578665B2
公开(公告)日：2023-02-14
申请号：US17218369
申请日：2021-03-31
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.
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