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公开(公告)号：US12071854B2
公开(公告)日：2024-08-27
申请号：US17438339
申请日：2020-03-11
CPC分类号： F01D21/045 , F01D5/026 , F01D5/066 , F02C3/107 , F02C7/36 , F16D1/10 , F05D2240/61 , F05D2250/182 , F05D2260/4031 , F05D2260/902 , F16D2001/103 , Y10T403/16 , Y10T403/559 , Y10T403/7045
摘要： A toothed coupling mechanism for an assembly of rotating elements of an aircraft gas turbine engine includes a pair of coupling halves having an axial toothed coupling interface therebetween. Each coupling half has a plurality of splined teeth inter-engaged about an axis for transmitting torque therebetween. A protrusion is located on one of the splined teeth of one of the coupling halves. A splined tooth of the other coupling half comes into contact with the protrusion in a situation of uncoupling of said coupling halves.
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公开(公告)号：US12055096B2
公开(公告)日：2024-08-06
申请号：US17588650
申请日：2022-01-31
申请人： RTX CORPORATION
IPC分类号： F02C7/06 , F01D5/02 , F01D5/06 , F01D9/06 , F01D17/10 , F02C3/04 , F02C3/06 , F02C3/10 , F02C3/107 , F02C7/28 , F02C7/36 , F02C9/18 , F02K1/06 , F02K1/09 , F02K3/04 , F02K3/06 , F04D29/32 , F04D29/38 , F16H1/28
CPC分类号： F02C7/06 , F01D5/02 , F01D5/06 , F01D9/06 , F01D17/105 , F02C3/04 , F02C3/06 , F02C3/10 , F02C3/107 , F02C7/28 , F02C7/36 , F02C9/18 , F02K1/06 , F02K1/09 , F02K3/04 , F02K3/06 , F04D29/321 , F04D29/325 , F04D29/38 , F16H1/28 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2240/12 , F05D2240/24 , F05D2240/35 , F05D2240/52 , F05D2240/54 , F05D2240/60 , F05D2260/40311
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：US11898490B2
公开(公告)日：2024-02-13
申请号：US17662195
申请日：2022-05-05
CPC分类号： F02C3/107 , F02C7/32 , F02C9/28 , F02C9/40 , F05D2220/323 , F05D2260/40311 , F05D2270/304
摘要： 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.
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公开(公告)号：US11891914B2
公开(公告)日：2024-02-06
申请号：US17284939
申请日：2019-08-12
发明人： Trevor Milne
CPC分类号： F01D5/025 , F01D21/04 , F02C7/00 , F01D5/026 , F01D19/00 , F01D21/00 , F01D21/06 , F02C3/107 , F05D2220/323 , F05D2240/24 , F05D2240/60 , F05D2260/36
摘要： A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus includes an elongate member defining a longitudinal axis and at least two arms projecting away from the longitudinal axis of the elongate member. In use, in a first orientation, the elongate member is configured to be connected to a tool apparatus for applying a load energy to the tension stud and the at least two arms of the safety apparatus are configured to overlap with at least part of the tool apparatus in the direction of the longitudinal axis of the elongate member to contain the release of energy therebetween.
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公开(公告)号：US11866160B2
公开(公告)日：2024-01-09
申请号：US17982629
申请日：2022-11-08
申请人： Xiaoyi Zhu
发明人： Xiaoyi Zhu
IPC分类号： B64C27/16 , F01D5/12 , F01D1/32 , B64C11/16 , B64C1/16 , F02F3/00 , F02B23/04 , F02B19/00 , B64C11/24 , B64C27/473 , F01K25/02 , F02B39/02 , F02C3/107
CPC分类号： B64C27/16 , B64C1/16 , B64C11/24 , B64C27/473 , F01D1/32 , F01D5/12 , F01K25/02 , F02B19/00 , F02B23/04 , F02B39/02 , F02C3/107 , F02F3/0076
摘要： The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.
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公开(公告)号：US20230383699A1
公开(公告)日：2023-11-30
申请号：US18107126
申请日：2023-02-08
CPC分类号： F02C7/36 , F02K3/06 , F02C3/107 , F01D1/26 , F01D15/12 , F05D2260/40311 , F05D2270/051
摘要： A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
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公开(公告)号：US11781506B2
公开(公告)日：2023-10-10
申请号：US16891492
申请日：2020-06-03
IPC分类号： F02K3/075 , F02K3/077 , F02K1/72 , F02K3/06 , F02C3/107 , F02K3/068 , F04D29/66 , F04D29/54 , F01D5/14
CPC分类号： F02K3/077 , F02K3/075 , F01D5/145 , F02K1/72 , F02K3/06 , F04D29/542 , F04D29/661
摘要： A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.
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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：US11719161B2
公开(公告)日：2023-08-08
申请号：US17488690
申请日：2021-09-29
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号： F01D5/02 , F02C7/24 , F02K3/06 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
CPC分类号： F02C7/24 , F01D5/02 , F01D5/12 , F01D5/16 , F01D9/041 , F01D15/12 , F01D17/105 , F01D25/04 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2200/36 , F05D2210/31 , F05D2220/32 , F05D2220/327 , F05D2240/301 , F05D2240/307 , F05D2260/40311 , F05D2260/96 , Y02T50/60
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.
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公开(公告)号：US20230235715A1
公开(公告)日：2023-07-27
申请号：US18130539
申请日：2023-04-04
发明人： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
摘要： A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.
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