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公开(公告)号：US20240230100A9
公开(公告)日：2024-07-11
申请号：US18314565
申请日：2023-05-09
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Daniel D. Brown , Sibtosh Pal , Joseph Zelina
CPC classification number: F23R3/60 , F02C7/20 , F23R3/06 , F23R2900/00017 , F23R2900/03042
Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.
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公开(公告)号：US20230112117A1
公开(公告)日：2023-04-13
申请号：US17496126
申请日：2021-10-07
Applicant: General Electric Company
Inventor： Gerardo Antonio Salazar Lois , Daniel D. Brown , Daniel J. Kirtley
Abstract: A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.
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公开(公告)号：US20240133556A1
公开(公告)日：2024-04-25
申请号：US18314565
申请日：2023-05-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Daniel D. Brown , Sibtosh Pal , Joseph Zelina
CPC classification number: F23R3/60 , F02C7/20 , F23R3/06 , F23R2900/00017 , F23R2900/03042
Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.
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公开(公告)号：US11662096B2
公开(公告)日：2023-05-30
申请号：US17496126
申请日：2021-10-07
Applicant: General Electric Company
Inventor： Gerardo Antonio Salazar Lois , Daniel D. Brown , Daniel J. Kirtley
Abstract: A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.
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