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公开(公告)号：US10093428B2
公开(公告)日：2018-10-09
申请号：US15242844
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell
Abstract: A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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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
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Matthew Ryan Polakowski , Patrick Michael Marrinan , Joel Francis Kirk , Randy M. Vondrell , Jeffrey Donald Clements
CPC classification number: F02K3/06 , F01D25/26 , F02C3/04 , F02C7/18 , F02C7/36 , F05D2220/36 , F05D2300/20 , Y02T50/672
Abstract: 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：US20180050810A1
公开(公告)日：2018-02-22
申请号：US15241157
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko
IPC: B64D33/08 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/32 , F04D29/056 , F04D29/063 , F04D29/58
Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
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公开(公告)号：US20170291693A1
公开(公告)日：2017-10-12
申请号：US15095262
申请日：2016-04-11
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
CPC classification number: B64C21/06 , B64C2230/04 , B64D27/24 , B64D33/02 , B64D2027/026 , B64D2033/0226 , F02K5/00 , Y02T50/166 , Y02T50/62
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a fan rotatable about a central axis of the electric propulsion engine. The fan includes a fan shaft mechanically coupled to a power gearbox. The electric propulsion engine also includes an electric motor having a driveshaft, with the electric motor coupled to the power gearbox through the drive shaft. The electric motor rotates the fan through the power gearbox. The driveshaft includes a flexible element for accommodating a misalignment of the electric motor and the power gearbox.
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公开(公告)号：US20160201503A1
公开(公告)日：2016-07-14
申请号：US14596804
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow , Raymond Anthony Humble
CPC classification number: F01D5/282 , F01D5/147 , F01D21/04 , F01D21/045 , F04D29/324 , Y02T50/672
Abstract: A frangible airfoil that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided, the airfoil having provisions for dissipating energy, self-shredding, and predetermined release trajectory.
Abstract translation: 提供了一种减轻与由复合叶片的冲击损坏引起的材料释放有关的不利条件的易碎翼型，翼型件具有用于耗散能量，自切碎和预定释放轨迹的规定。
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Patent Agency Ranking
公开(公告)号：US20160200085A1
公开(公告)日：2016-07-14
申请号：US14596841
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow
CPC classification number: B29C70/34 , B29D99/0025
Abstract: A method of manufacturing a frangible laminate is provided. The method comprises constructing a reinforced polymer matrix, cutting the reinforced polymer matrix into a plurality of laminae, forming a laminate via stacking the plurality of laminae and at least one energy dissipating member, and consolidating the laminate.
Abstract translation: 提供了制造易碎层压体的方法。 该方法包括构建增强的聚合物基体，将增强的聚合物基体切割成多个层，通过堆叠多个层和至少一个能量消散构件并固结层压体形成层压体。
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公开(公告)号：US20160146115A1
公开(公告)日：2016-05-26
申请号：US14919825
申请日：2015-10-22
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow , Randy M. Vondrell , Tsuguji Nakano , Jeffrey Anthony Hamel , Darek Tomasz Zatorski
CPC classification number: F02C9/20 , F01D7/00 , F01D15/12 , F01D17/085 , F01D17/105 , F01D17/162 , F02C3/04 , F02C3/13 , F02C7/042 , F02C7/36 , F02C9/18 , F02K1/66 , F02K3/04 , F02K3/075 , F05D2220/36 , F05D2270/101 , F05D2270/303 , F05D2300/30 , Y02T50/672
Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
Abstract translation: 提供了一种涡轮风扇燃气涡轮发动机系统的方法和系统。 燃气涡轮发动机系统包括耦合到第一可旋转轴的变桨距风扇（VPF）组件和耦合到第二可旋转轴的低压压缩机LPC。 LPC包括多个可变桨距定子叶片，其与LPC的转子的叶片行相互指向。 燃气涡轮发动机系统还包括联接到所述第一可旋转轴和所述第二可旋转轴的减速装置。 燃气涡轮发动机系统还包括位于所述LPC的出口和旁路管道之间的调节压力释放阀，以及被配置为响应于操作来调度所述多个变桨距定子叶片和所述调节压力释放阀的位置的控制器 所述涡轮风扇燃气涡轮发动机系统的状态和与所述LPC相关联的温度。
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公开(公告)号：US20250146454A1
公开(公告)日：2025-05-08
申请号：US19017029
申请日：2025-01-10
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson , Syed Arif Khalid
Abstract: A gas turbine engine includes: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct, the gas turbine engine defining a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US20250122849A1
公开(公告)日：2025-04-17
申请号：US18991142
申请日：2024-12-20
Applicant: General Electric Company
Inventor： Brandon W. Miller , Randy M. Vondrell , David M. Ostdiek , Craig W. Higgins , Alexander Simpson , William Bowden
Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10. The thrust to power airflow ratio is a ratio of airflow through a bypass passage over the turbomachine plus airflow through the fan duct to airflow through the core duct. The core bypass ratio is a ratio of airflow through the fan duct to airflow through the core duct. The fan duct includes an exhaust nozzle having a plurality of chevrons disposed at its aft end to define an exhaust outlet.
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公开(公告)号：US20250020070A1
公开(公告)日：2025-01-16
申请号：US18517878
申请日：2023-11-22
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Brandon W. Miller , Andrew Hudecki , Randy M. Vondrell , Jeffrey D. Rambo
Abstract: A lubrication system for a turbine engine. The turbine engine includes a fan having a fan shaft and one or more rotating components. The lubrication system includes one or more tanks that stores lubricant therein, a primary lubrication system, and an auxiliary lubrication system. The primary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump that is coupled to the fan shaft. The auxiliary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components based on a pressure of the lubricant in the primary lubrication system. Rotation of the fan shaft causes the auxiliary pump to pump the lubricant to the one or more rotating components.
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