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公开(公告)号：US20240229664A1
公开(公告)日：2024-07-11
申请号：US18152904
申请日：2023-01-11
Applicant: General Electric Company
Inventor： Kudum Shinde , Yashpal Patel , Sesha Subramanian , Brandon C. Clarke
CPC classification number: F01D9/065 , F01D9/041 , F02C6/08 , F05D2220/3218 , F05D2240/121 , F05D2240/122 , F05D2260/606
Abstract: A gas turbine engine includes a compressor section having rotor shaft assembly and a stator shroud assembly including a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A compressor bleed air system includes a compressor bleed air duct that includes a sloped inlet portion, such as a NACA submerged inlet portion, in the stator shroud casing. Alternatively, stator vanes at a compressor bleed air passage may have a NACA inlet scoop and an airflow passage through the stator vane providing a bleed airflow to a cavity, which has airflow passages providing bleed air to an upstream side of the bleed air passage.
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公开(公告)号：US12146423B2
公开(公告)日：2024-11-19
申请号：US18152904
申请日：2023-01-11
Applicant: General Electric Company
Inventor： Kudum Shinde , Yashpal Patel , Sesha Subramanian , Brandon C. Clarke
Abstract: A gas turbine engine includes a compressor section having rotor shaft assembly and a stator shroud assembly including a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A compressor bleed air system includes a compressor bleed air duct that includes a sloped inlet portion, such as a NACA submerged inlet portion, in the stator shroud casing. Alternatively, stator vanes at a compressor bleed air passage may have a NACA inlet scoop and an airflow passage through the stator vane providing a bleed airflow to a cavity, which has airflow passages providing bleed air to an upstream side of the bleed air passage.
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公开(公告)号：US11975847B2
公开(公告)日：2024-05-07
申请号：US17655100
申请日：2022-03-16
Applicant: General Electric Company
Inventor： Brandon C. Clarke , Scott Alan Schimmels
CPC classification number: B64D15/12 , B64D27/10 , B64D29/00 , F02C9/00 , G05D23/1919
Abstract: An ice protection system for an external surface for an aircraft. The external surface is configured to have air flow over the external surface and has a plurality of zones. At least one heat source is thermally coupled to the external surface in each zone of the plurality of zones. A controller is configured to selectively control the at least one heat source in each zone of the plurality of zones based on an operating condition related to the air flowing over the external surface.
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公开(公告)号：US20230294833A1
公开(公告)日：2023-09-21
申请号：US17655100
申请日：2022-03-16
Applicant: General Electric Company
Inventor： Brandon C. Clarke , Scott Alan Schimmels
CPC classification number: B64D15/12 , B64D27/10 , B64D29/00 , F02C9/00 , G05D23/1919
Abstract: An ice protection system for an external surface for an aircraft. The external surface is configured to have air flow over the external surface and has a plurality of zones. At least one heat source is thermally coupled to the external surface in each zone of the plurality of zones. A controller is configured to selectively control the at least one heat source in each zone of the plurality of zones based on an operating condition related to the air flowing over the external surface.
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