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公开(公告)号：US20180216575A1
公开(公告)日：2018-08-02
申请号：US15417745
申请日：2017-01-27
发明人： Brandon Wayne Miller , Matthew Ryan Polakowski , Patrick Michael Marrinan , Joel Francis Kirk , Randy M. Vondrell , Jeffrey Donald Clements
CPC分类号： F02K3/06 , F01D25/26 , F02C3/04 , F02C7/18 , F02C7/36 , F05D2220/36 , F05D2300/20 , Y02T50/672
摘要： A turbofan engine is provided including a fan having a plurality of rotatable fan blades and defining a fan pressure ratio during operation of the turbofan engine. The turbofan engine also includes a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath. The turbofan also includes an outer nacelle at least partially surrounding the fan and the turbomachine, the outer nacelle defining a bypass passage with the turbomachine. A bypass ratio of an amount of airflow through the bypass passage to an amount of airflow through the core air flowpath during operation of the turbofan is less than or equal to about 11 and wherein the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US11673661B2
公开(公告)日：2023-06-13
申请号：US17329312
申请日：2021-05-25
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C27/28 , A61L9/12 , H02J7/00 , H02J50/10 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
CPC分类号： B64C29/0033 , A61L9/122 , B64C21/06 , B64C27/28 , B64C29/00 , B64D27/14 , B64D27/24 , H02J7/0042 , H02J50/10 , H02P9/04 , A61L2209/133 , B64C3/385 , B64C29/0008 , B64D2027/026 , B64D2221/00 , Y02T50/60
摘要： A propulsion system of an aircraft has at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position, and a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan. During a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between the plurality of unducted fans and the plurality of ducted fans such that the at least one unducted fan is a primary source of thrust.
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公开(公告)号：US10392106B2
公开(公告)日：2019-08-27
申请号：US15259564
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
摘要： An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
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公开(公告)号：US20180065741A1
公开(公告)日：2018-03-08
申请号：US15259596
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
CPC分类号： B64C29/0033 , B64C3/32 , B64C11/001 , B64C11/28 , B64C11/46 , B64C27/08 , B64C2201/027 , B64D27/24 , B64D2027/026 , Y02T50/64
摘要： An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly.
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公开(公告)号：US20200085988A1
公开(公告)日：2020-03-19
申请号：US16502913
申请日：2019-07-03
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
摘要： A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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公开(公告)号：US10384774B2
公开(公告)日：2019-08-20
申请号：US15259654
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
摘要： A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.
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公开(公告)号：US10252797B2
公开(公告)日：2019-04-09
申请号：US15259596
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C3/32 , B64C11/28 , B64C27/08 , B64D27/24 , B64C11/00 , B64C11/46 , B64D27/02
摘要： An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly.
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公开(公告)号：US20180065742A1
公开(公告)日：2018-03-08
申请号：US15259622
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
CPC分类号： B64C29/0033 , B64C21/06 , B64C29/0025 , B64C2230/04 , B64D27/14 , B64D27/20 , B64D27/24 , B64D29/04 , B64D2027/026 , H02K7/1823 , Y02T50/166 , Y02T50/64
摘要： An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft.
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公开(公告)号：US20180065740A1
公开(公告)日：2018-03-08
申请号：US15259564
申请日：2016-09-08
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
CPC分类号： B64C29/0033 , B64D27/12 , B64D27/24 , B64D2027/026 , B64D2221/00
摘要： An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
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公开(公告)号：US09764848B1
公开(公告)日：2017-09-19
申请号：US15245257
申请日：2016-08-24
CPC分类号： B64D27/18 , B64C11/30 , B64D27/24 , B64D41/00 , B64D2027/026 , B64D2221/00 , F01D15/10 , Y02T50/62
摘要： A propulsion system for an aircraft includes an electric generator and a turbomachine. The turbomachine is configured to be mounted to a first wing of the aircraft and is operable with the electric generator. The propulsion system additionally includes a first propulsor mechanically coupled to a shaft of the turbomachine and a second propulsor assembly configured to be mounted at a location away from the turbomachine and the first propulsor. The electric generator is in electrical communication with the second propulsor assembly for powering the second propulsor assembly.
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