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1.发明授权公开(公告)号：US11981419B2
公开(公告)日：2024-05-14
申请号：US17560544
申请日：2021-12-23
CPC分类号： B64C11/38 , F02K3/06 , F04D29/325 , F04D29/36 , F04D29/362 , Y02T50/60
摘要： The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.
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公开(公告)号：US20230258134A1
公开(公告)日：2023-08-17
申请号：US18307201
申请日：2023-04-26
发明人： Arthur William Sibbach , Brandon Wayne Miller , Christopher James Kroger , Jeffrey Donald Clements , Sean Christopher Binion , Tsuguji Nakano
CPC分类号： F02C7/36 , F02K3/06 , F05D2260/606 , F05D2260/40311 , F05D2220/36
摘要： A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of rotatable fan blades, each fan blade defining a fan tip speed; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and a gear box, wherein the turbomachine is operably coupled to the fan through the gear box, wherein a gear ratio of the gear box is greater than or equal to 1.2 and less than or equal to 3.0; wherein during operation of the turbofan engine at a rated speed the fan tip speed is greater than or equal to 1000 feet per second. In exemplary embodiments, during operation of the turbofan engine at the rated speed the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US20230028503A1
公开(公告)日：2023-01-26
申请号：US17384999
申请日：2021-07-26
发明人： Arthur William Sibbach , Brandon Wayne Miller , Christopher James Kroger , Jeffrey Donald Clements , Sean Christopher Binion , Tsuguji Nakano
摘要： A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of rotatable fan blades, each fan blade defining a fan tip speed; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and a gear box, wherein the turbomachine is operably coupled to the fan through the gear box, wherein a gear ratio of the gear box is greater than or equal to 1.2 and less than or equal to 3.0; wherein during operation of the turbofan engine at a rated speed the fan tip speed is greater than or equal to 1000 feet per second. In exemplary embodiments, during operation of the turbofan engine at the rated speed the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US11286853B2
公开(公告)日：2022-03-29
申请号：US16167408
申请日：2018-10-22
IPC分类号： F02C7/14 , F02C7/06 , F02C7/18 , F02C7/224 , F25B41/31 , F02C7/16 , F25B1/00 , F28D15/00 , F28F27/02 , F28D21/00
摘要： A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger. The plurality of heat source exchangers and the at least one heat sink exchanger are in thermal communication with the heat exchange fluid in the thermal transport bus. The plurality of heat source exchangers are arranged along the thermal transport bus and configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the at least one heat sink exchanger is located downstream of the plurality of heat source exchangers and configured to remove heat from the heat exchange fluid.
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公开(公告)号：US10823078B2
公开(公告)日：2020-11-03
申请号：US15635574
申请日：2017-06-28
发明人： Nathan Evan McCurdy Gibson , Christopher James Kroger , Sean Christopher Binion , Scott Douglas Waun
IPC分类号： F02C7/268 , F02C7/275 , F02C3/04 , H02J7/00 , H01G4/38 , H02K11/00 , F02C7/26 , B64D27/10 , B64F1/34 , H02J3/38 , B64D33/00 , B64C39/02 , B64D5/00 , H01G4/40 , H02J7/34
摘要： Systems and methods for starting a powerplant are provided. In one exemplary aspect, a starting system of a powerplant includes one or more features that allow for the powerplant to be started electrically with a burst of electrical power and without deriving electrical power from an offboard power source or a relatively heavy onboard energy storage device.
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公开(公告)号：US10539076B2
公开(公告)日：2020-01-21
申请号：US14937266
申请日：2015-11-10
摘要： A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.
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公开(公告)号：US20180363554A1
公开(公告)日：2018-12-20
申请号：US15625101
申请日：2017-06-16
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
CPC分类号： F02C7/057 , F02C3/04 , F02C7/042 , F02K3/06 , F04D29/522 , F04D29/541 , F04D29/681
摘要： A gas turbine engine includes a compressor section and a turbine section. The turbine section includes a drive turbine and is located downstream of the compressor section. The gas turbine engine also includes a fan mechanically coupled to and rotatable with the drive turbine such that the fan is rotatable by the drive turbine at the same rotational speed as the drive turbine, the fan defining a fan pressure ratio and including a plurality of fan blades, each fan blade defining a fan tip speed. During operation of the gas turbine engine at a rated speed, the fan pressure ratio of the fan is less than 1.5 and the fan tip speed of each of the fan blades is greater than 1,250 feet per second.
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公开(公告)号：US10724435B2
公开(公告)日：2020-07-28
申请号：US15625186
申请日：2017-06-16
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
摘要： A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide vanes cantilevered from the outer nacelle at a location forward of the plurality of fan blades along the axial direction. Each of the plurality of inlet guide vanes defines an inner end along the radial direction and it is unconnected with an adjacent part-span inlet guide vane at the inner end.
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公开(公告)号：US10711797B2
公开(公告)日：2020-07-14
申请号：US15625212
申请日：2017-06-16
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
摘要： A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.
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公开(公告)号：US20180363676A1
公开(公告)日：2018-12-20
申请号：US15625291
申请日：2017-06-16
摘要： A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and defining an nacelle inlet, the outer nacelle including an inner wall defining a plurality of openings located aft of the nacelle inlet and forward of the plurality of fan blades of the fan along an axial direction for providing a swirl airflow upstream of the plurality of fan blades of the fan at a swirl angle greater than zero relative to a radial direction.
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