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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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Patent Agency Ranking
公开(公告)号：US11828226B2
公开(公告)日：2023-11-28
申请号：US17827180
申请日：2022-05-27
Applicant: General Electric Company
Inventor： Sesha Subramanian , Ravikanth Avancha , Atanu Saha
Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.
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公开(公告)号：US20230349324A1
公开(公告)日：2023-11-02
申请号：US17841876
申请日：2022-06-16
Inventor： Rajani Bhanu Poornima M , Vilas Kawaduji Bokade , Subramani Adhiachari , Sesha Subramanian , Pankaj Sharma , Ashish Sharma , Scott Alan Schimmels
CPC classification number: F02C7/047 , F01D25/08 , F05D2220/36 , F05D2260/20
Abstract: A turbofan engine is provided. The turbofan engine includes a fan; a turbomachine operably coupled to the fan for driving the fan, wherein the turbomachine, the fan, or both include an engine component; a heat source; and a heat transfer system configured to reduce ice buildup or ice formation in the engine component, the heat transfer system in communication with the heat source, the heat transfer system comprising: a first heat transfer component in communication with the heat source; and a second heat transfer component that extends from the first heat transfer component to or through the engine component, wherein the first heat transfer component comprises one of a heat pipe or a graphene rod, and wherein the second heat transfer component comprises the other of the heat pipe or the graphene rod.
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公开(公告)号：US20230332539A1
公开(公告)日：2023-10-19
申请号：US17827180
申请日：2022-05-27
Applicant: General Electric Company
Inventor： Sesha Subramanian , Ravikanth Avancha , Atanu Saha
CPC classification number: F02C9/18 , F02C7/00 , F05D2240/127
Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.
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公开(公告)号：US20200011347A1
公开(公告)日：2020-01-09
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
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公开(公告)号：US10323571B2
公开(公告)日：2019-06-18
申请号：US14971354
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Sesha Subramanian , Bhaskar Nanda Mondal , Sushilkumar Gulabrao Shevakari , Mayank Krisna Amble
Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.
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