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公开(公告)号：US20230366355A1
公开(公告)日：2023-11-16
申请号：US18107671
申请日：2023-02-09
发明人： William G. Sheridan
CPC分类号： F02C7/36 , F01D25/16 , F01D25/162 , F02C3/107 , F02C7/06 , F01D5/02 , F01D15/12 , F02C3/04 , F05D2260/40311 , F05D2220/32 , F05D2230/60
摘要： A gas turbine engine includes a propulsor having blades extending from a propulsor hub. A compressor section includes a first compressor and a second compressor. A speed reduction device includes an epicyclic gear system. The epicyclic gear system includes a sun gear, a plurality of intermediate gears, a carrier supporting the intermediate gears and the propulsor hub, and a ring gear. A turbine section includes a first turbine and a second turbine. The second turbine drives the propulsor through the epicyclic gear system. The epicyclic gear system is straddled by forward and aft bearings that engage the carrier.
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公开(公告)号：US11814976B2
公开(公告)日：2023-11-14
申请号：US17586875
申请日：2022-01-28
发明人： William G. Sheridan
CPC分类号： F01D25/18 , B01D19/0068 , B01D19/0073 , F01D25/20 , F02C7/06 , F05D2260/609 , Y02T50/60
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：US11686209B2
公开(公告)日：2023-06-27
申请号：US17213444
申请日：2021-03-26
发明人： William G. Sheridan
CPC分类号： F01D15/12 , F01D21/045 , F02C7/36 , F16H1/2809 , F16H1/2818 , F16H1/2827 , F16H1/2836 , F16H1/48 , F05D2220/32 , F05D2260/40311 , F16H2001/289
摘要： An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate. At least one epicyclic gear set is located between the first plate and the second plate. The first plate is configured to rotate with an output of the epicyclic gear assembly. A first bearing race is attached to the first plate for supporting a first bearing. A second bearing race is attached to the second plate for supporting a second bearing.
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公开(公告)号：US11560852B2
公开(公告)日：2023-01-24
申请号：US17484331
申请日：2021-09-24
摘要： A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
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公开(公告)号：US11492932B2
公开(公告)日：2022-11-08
申请号：US16992727
申请日：2020-08-13
摘要： A gas turbine engine includes a turbine section that includes a fan drive turbine. A geared architecture includes a sun gear in driving engagement with the fan drive turbine. A plurality of planet gears surrounds the sun gear. A ring gear surrounds the plurality of planet gears. A deflection limiter mechanically attaches the ring gear to an engine static structure. The deflection limiter includes a first support fixed to the ring gear that has a first interlocking feature and a second support fixed to the engine static structure that has a second interlocking feature. The first and second interlocking features define at least one of a radial clearance of between 0.005 inches (0.127 mm) and 0.080 inches (2.032 mm) or a circumferential clearance of between 0.005 inches (0.127 mm) and 0.250 inches (2.032 mm). A fan section includes a plurality of fan blades in driving engagement with the geared architecture through a fan drive shaft.
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公开(公告)号：US20220260022A1
公开(公告)日：2022-08-18
申请号：US17729129
申请日：2022-04-26
摘要： A method of assembling a gear train includes providing a unitary carrier. The unitary carrier has a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes inserting a plurality of intermediate gears through the central opening and moving the intermediate gears radially outwardly into the gear pockets to extend into the apertures, placing a ring gear on an outer periphery of the intermediate gears to engage the intermediate gears, and securing the gear train to a fan shaft by a connection.
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公开(公告)号：US20220154643A1
公开(公告)日：2022-05-19
申请号：US17588650
申请日：2022-01-31
IPC分类号： F02C7/06 , F02K1/09 , F02C7/36 , F02C3/107 , F02K3/04 , F01D5/02 , F01D9/06 , F01D17/10 , F02C3/06 , F02C3/10 , F04D29/32 , F01D5/06 , F02C3/04 , F02C7/28 , F02C9/18 , F02K1/06 , F02K3/06 , F04D29/38 , F16H1/28
摘要： A gas turbine engine according to the present disclosure includes, among other things, a propulsor section including a propulsor having a plurality of blades, the plurality of blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine that drives a first compressor and a second turbine that drives the propulsor section. A second inboard boundary of a core flowpath has a radius R1 defined at a first stage of a second compressor and has a radius R2 defined at a splitter rim that guides flow into the core flowpath.
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公开(公告)号：US20220074353A1
公开(公告)日：2022-03-10
申请号：US17532085
申请日：2021-11-22
摘要： A method of assembling a gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier, positioning baffles between side walls of the carrier such that an end of each of the baffles abuts a respective mount of the carrier, inserting intermediate gears through a central opening of the carrier, and then moving the intermediate gears radially outwardly into respective gear pockets of the carrier, inserting a sun gear through the central opening, moving the intermediate gears radially inwardly to engage the sun gear, coupling a shaft to the carrier, including attaching a torque frame to the carrier such that the torque frame interconnects the carrier and the shaft, placing first and second ring gear halves of a ring gear onto an outer periphery of the intermediate gears, and fixedly attaching the ring gear to an engine static structure. A gear system is also disclosed.
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公开(公告)号：US20220010736A1
公开(公告)日：2022-01-13
申请号：US17484331
申请日：2021-09-24
摘要： A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
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公开(公告)号：US11156166B2
公开(公告)日：2021-10-26
申请号：US16180548
申请日：2018-11-05
摘要： A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
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