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公开(公告)号：US11982238B2
公开(公告)日：2024-05-14
申请号：US17881399
申请日：2022-08-04
CPC分类号： F02C7/36 , F16H1/28 , F05D2220/36 , F05D2260/40311
摘要： 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：US11773786B2
公开(公告)日：2023-10-03
申请号：US17408607
申请日：2021-08-23
发明人： William G. Sheridan
摘要： A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
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公开(公告)号：US20230193818A1
公开(公告)日：2023-06-22
申请号：US18108270
申请日：2023-02-10
CPC分类号： F02C3/107 , F02C7/36 , F02K3/06 , F02C7/06 , F05D2260/4031 , F05D2260/403
摘要： A gas turbine engine includes a propulsor and a drive gear system. The drive gear system includes at least one ring gear, a plurality of intermediate gears positioned between and enmeshing with a sun gear and the at least one ring gear, with the plurality of intermediate gears carried by a gear carrier. A first bearing is configured to rotate with the gear carrier. A second bearing is on an opposite side of the drive gear system from the first bearing.
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公开(公告)号：US20230182909A1
公开(公告)日：2023-06-15
申请号：US18103935
申请日：2023-01-31
CPC分类号： B64D27/24 , B64D27/10 , F01D15/10 , F02C6/14 , F02C7/36 , H02K7/1823 , F05D2270/053 , B64D2221/00 , F02C3/107
摘要： 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：US20230167787A1
公开(公告)日：2023-06-01
申请号：US18161340
申请日：2023-01-30
CPC分类号： F02K3/06 , F02C7/36 , F01D25/168 , F04D29/522 , F05D2220/36 , F05D2260/40311
摘要： An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.
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公开(公告)号：US20220372918A1
公开(公告)日：2022-11-24
申请号：US17881399
申请日：2022-08-04
摘要： 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：US20220307387A1
公开(公告)日：2022-09-29
申请号：US17586875
申请日：2022-01-28
发明人： William G. Sheridan
摘要： 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：US11248494B2
公开(公告)日：2022-02-15
申请号：US17016935
申请日：2020-09-10
发明人： William G. Sheridan
摘要： 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：US11203982B2
公开(公告)日：2021-12-21
申请号：US16436569
申请日：2019-06-10
摘要： A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between 219 and 328.
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公开(公告)号：US11136920B2
公开(公告)日：2021-10-05
申请号：US17034713
申请日：2020-09-28
发明人： William G. Sheridan , John R. Otto
摘要： A gas turbine engine includes a fan, a fan shaft coupled with the fan and arranged along an engine central axis, and a frame supporting the fan shaft. The frame defines a lateral frame stiffness (LFS). An epicyclic gear system is coupled to the fan shaft, and a non-rotatable flexible coupling and a rotatable flexible coupling support the epicyclic gear system. The non-rotatable flexible coupling and the rotatable flexible coupling each have a stiffness of a common stiffness type under a common type of motion with respect to the engine central axis. The stiffness is defined with respect to the LFS. The stiffness of the rotatable flexible coupling is greater than the stiffness of the non-rotatable flexible coupling.
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