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公开(公告)号：US12084978B2
公开(公告)日：2024-09-10
申请号：US18196048
申请日：2023-05-11
IPC分类号： F16H57/04 , F01D1/02 , F01D5/02 , F01D15/12 , F01D25/16 , F01D25/18 , F02C7/32 , F02C7/36 , F02K3/06 , F16H57/08
CPC分类号： F01D15/12 , F01D1/02 , F01D5/02 , F01D5/027 , F01D25/16 , F01D25/18 , F02C7/32 , F16H57/04 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/40311 , F16H57/0423 , F16H57/0479 , F16H57/0486 , F16H2057/085
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.
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公开(公告)号：US20240076050A1
公开(公告)日：2024-03-07
申请号：US18215394
申请日：2023-06-28
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC分类号： B64D27/26 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F02K3/06
CPC分类号： B64D27/26 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F02K3/06 , B64D2027/266 , B64D2027/268 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
摘要： A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.
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3.发明授权公开(公告)号：US11913349B2
公开(公告)日：2024-02-27
申请号：US18104375
申请日：2023-02-01
发明人： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
CPC分类号： F01D25/164 , F01D15/12 , F01D25/162 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2240/60 , F05D2260/40311
摘要： A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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公开(公告)号：US20230304416A1
公开(公告)日：2023-09-28
申请号：US18196048
申请日：2023-05-11
CPC分类号： F01D15/12 , F01D25/18 , F01D25/16 , F01D1/02 , F01D5/02 , F01D5/027 , F02C7/32 , F16H57/04 , F05D2220/32 , F16H57/0423 , F16H57/0479 , F16H57/0486 , F05D2220/36 , F05D2240/70 , F05D2260/40311 , F16H2057/085
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.
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公开(公告)号：US11719169B2
公开(公告)日：2023-08-08
申请号：US17720587
申请日：2022-04-14
CPC分类号： F02C9/18 , F02C7/185 , F02K3/115 , G01M15/09 , F05D2260/213 , F05D2260/80 , F05D2270/053 , F05D2270/112 , F05D2270/301 , Y02T50/60
摘要： A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.
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6.发明公开公开(公告)号：US20230193830A1
公开(公告)日：2023-06-22
申请号：US18110454
申请日：2023-02-16
发明人： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
CPC分类号： F02C7/36 , F02K3/06 , F02C3/107 , F01D25/162 , F01D5/06 , F02C3/06 , F02C7/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a compressor section including a first compressor, a turbine section including a first turbine and a second turbine, a first shaft and a second shaft, the first shaft interconnecting the first turbine and the second compressor, and a geared architecture. The first shaft is supported on a first bearing in an overhung manner. A performance ratio is between 0.5 and 1.5.
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公开(公告)号：US20220228506A1
公开(公告)日：2022-07-21
申请号：US17711177
申请日：2022-04-01
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.
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公开(公告)号：US11346286B2
公开(公告)日：2022-05-31
申请号：US17037916
申请日：2020-09-30
摘要： A turbofan gas turbine engine includes a fan section having a fan, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture including an epicyclic gear train, a turbine section including a low pressure turbine and a high pressure turbine, the fan driven by the low pressure turbine through the geared architecture, and a power density between 4.84 lbf/in3 and 5.5 lbf/in3.
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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：US20220106912A1
公开(公告)日：2022-04-07
申请号：US17555606
申请日：2021-12-20
摘要： An example gas turbine engine includes a propulsor assembly consisting of a fan module and a fan drive turbine module, an epicyclic gear train, a high spool and a low spool. A weight of the propulsor assembly is less than 40% of a total weight of a gas turbine engine. The high spool includes an outer shaft, a high pressure turbine and a high pressure compressor. The low spool includes an inner shaft, a low pressure turbine and a low pressure compressor. The inner shaft drives the propulsor through the gear train to drive the propulsor. A weight of the propulsor is greater than a weight of the low pressure turbine.
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