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公开(公告)号：US20250003375A1
公开(公告)日：2025-01-02
申请号：US18740613
申请日：2024-06-12
Applicant: General Electric Company
Inventor： Joseph George Rose , Thomas Ory Moniz , Tsuguji Nakano , Jeffrey S. Spruill , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson
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, a secondary fan located downstream of the primary fan within the inlet duct, a heat exchanger disposed in the fan duct, and a booster upstream of the heat exchanger, the booster including a booster cowl extending into the fan duct, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet.
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Patent Agency Ranking
公开(公告)号：US20240309829A1
公开(公告)日：2024-09-19
申请号：US18675270
申请日：2024-05-28
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：US20240044304A1
公开(公告)日：2024-02-08
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：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：US20220003128A1
公开(公告)日：2022-01-06
申请号：US16920783
申请日：2020-07-06
Applicant: General Electric Company
Inventor： Mohamed Osama , Darek Tomasz Zatorski , Alexander Kimberley Simpson , Joseph John Zierer, JR.
Abstract: An engine includes: a first rotating component; a second rotating component separate from the first rotating component; and an electric machine, the electric machine including a first rotor rotatable with the first rotating component; a second rotor rotatable with the second rotating component; and a stator assembly arranged between the first rotor and the second rotor, the stator assembly including a first set of windings arranged adjacent to the first rotor, a second set of windings arranged adjacent to the second rotor, and a non-ferromagnetic inner housing arranged between the first set of windings and the second set of windings.
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