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公开(公告)号：US20200325849A1
公开(公告)日：2020-10-15
申请号：US16895037
申请日：2020-06-08
Applicant: Raytheon Technologies Corporation
Inventor： Richard M. Marshall
Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.”
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公开(公告)号：US11506128B2
公开(公告)日：2022-11-22
申请号：US17406652
申请日：2021-08-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Andre M. Ajami , Sami Chukrallah , Richard M. Marshall , Ryan W. Hunter
Abstract: A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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公开(公告)号：US11499502B2
公开(公告)日：2022-11-15
申请号：US16895037
申请日：2020-06-08
Applicant: Raytheon Technologies Corporation
Inventor： Richard M. Marshall
Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.
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公开(公告)号：US20210381439A1
公开(公告)日：2021-12-09
申请号：US17406652
申请日：2021-08-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Andre M. Ajami , Sami Chukrallah , Richard M. Marshall , Ryan W. Hunter
Abstract: A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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