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公开(公告)号：US20250116243A1
公开(公告)日：2025-04-10
申请号：US18982445
申请日：2024-12-16
Applicant: General Electric Company
Inventor： William Joseph Bowden , Keith Edward James Blodgett , Mustafa Dindar , David Cerra , James Hamilton Grooms , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberely Simpson
Abstract: A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.
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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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