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公开(公告)号：US20250012235A1
公开(公告)日：2025-01-09
申请号：US18888873
申请日：2024-09-18
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberely Simpson
Abstract: A gas turbine engine is provided. The 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, 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, and 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：US20240318613A1
公开(公告)日：2024-09-26
申请号：US18680469
申请日：2024-05-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberley Simpson , Syed Arif Khalid , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Kevin Edward Hinderliter
Abstract: A gas turbine engine is provided. The 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, 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, and 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：US12031504B2
公开(公告)日：2024-07-09
申请号：US17879384
申请日：2022-08-02
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine is provided. The 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, 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, and 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：US20210107676A1
公开(公告)日：2021-04-15
申请号：US16599430
申请日：2019-10-11
Applicant: General Electric Company
Abstract: An aircraft extending between a forward end and an aft end is provided. The aircraft includes an auxiliary power unit positioned proximate the aft end of the aircraft, the auxiliary power unit having an auxiliary power unit inlet duct and an auxiliary power unit exhaust duct, and a boundary layer ingestion fan positioned proximate the aft end of the aircraft, the boundary layer ingestion fan having a support shaft, wherein the auxiliary power unit exhaust duct extends through a portion of the support shaft of the boundary layer ingestion fan.
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公开(公告)号：US20200324906A1
公开(公告)日：2020-10-15
申请号：US16914635
申请日：2020-06-29
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Anthony Austin Bouvette , Glenn David Crabtree
IPC: B64D27/24 , B60L50/16 , B64C21/06 , B64D27/12 , B64D27/18 , F02C6/20 , F02K3/04 , H02G5/10 , H02K7/18
Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.
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Patent Agency Ranking
公开(公告)号：US10800539B2
公开(公告)日：2020-10-13
申请号：US15241168
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
Abstract: A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.
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公开(公告)号：US10538337B2
公开(公告)日：2020-01-21
申请号：US15493623
申请日：2017-04-21
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Anthony Austin Bouvette , Robert Charles Hon
IPC: B64D33/08 , B60L50/16 , B64C21/06 , B64D27/18 , B64D27/24 , F02K3/04 , H02G5/10 , H02K9/19 , H02K7/18 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric power source, an electric propulsor assembly having an electric motor and a propulsor configured to generate thrust for the aircraft, and a power bus electrically connecting the electric power source to the electric propulsor assembly such that the electric power source powers the electric propulsor assembly. The power bus includes an electric line and a fluid cooling system, the fluid cooling system extending along at least a portion of a length of the electric line. The fluid cooling system is in thermal communication with the electric line for cooling the electric line during operation and is further in thermal communication with the electric motor of the electric propulsor assembly for cooling the electric motor of the electric propulsor assembly.
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公开(公告)号：US20190322377A1
公开(公告)日：2019-10-24
申请号：US16503943
申请日：2019-07-05
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
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 power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.
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公开(公告)号：US10308366B2
公开(公告)日：2019-06-04
申请号：US15242789
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US10137981B2
公开(公告)日：2018-11-27
申请号：US15475401
申请日：2017-03-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , Patrick Michael Marrinan , Paul Robert Gemin , Nicholas Taylor Moore
Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole p = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.
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