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公开(公告)号：US12297750B2
公开(公告)日：2025-05-13
申请号：US18105393
申请日：2023-02-03
Applicant: General Electric Company
Inventor： Nishita Deshmukh , Deepak Ghiya , Reddi Hari Prasad Reddy Mylapalli
Abstract: A fluid duct includes a body and an elongate rib. The body extends along a central axis and defines a lumen configured to receive a first fluid extending therethrough. The body has an inner surface and an outer surface. The central axis defines an axial direction along the central axis, a radial direction perpendicular to the central axis, and a circumferential direction oriented rotationally about the central axis. The elongate rib is positioned on the inner surface of the body and extends radially inward from the inner surface of the body. The elongate rib defines a channel extending through the elongate rib in a primary direction. The channel is configured to receive a second fluid and isolate the second fluid from the first fluid.
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公开(公告)号：US20240191630A1
公开(公告)日：2024-06-13
申请号：US18105393
申请日：2023-02-03
Applicant: General Electric Company
Inventor： Nishita Deshmukh , Deepak Ghiya , Reddi Hari Prasad Reddy Mylapalli
CPC classification number: F01D9/023 , F01D25/12 , F05D2260/22141
Abstract: A fluid duct includes a body and an elongate rib. The body extends along a central axis and defines a lumen configured to receive a first fluid extending therethrough. The body has an inner surface and an outer surface. The central axis defines an axial direction along the central axis, a radial direction perpendicular to the central axis, and a circumferential direction oriented rotationally about the central axis. The elongate rib is positioned on the inner surface of the body and extends radially inward from the inner surface of the body. The elongate rib defines a channel extending through the elongate rib in a primary direction. The channel is configured to receive a second fluid and isolate the second fluid from the first fluid.
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公开(公告)号：US20240247807A1
公开(公告)日：2024-07-25
申请号：US18585509
申请日：2024-02-23
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rample Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US20220333501A1
公开(公告)日：2022-10-20
申请号：US17234371
申请日：2021-04-19
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas J. Kray , Veeraraju V , Deepak Ghiya , Sreekanth Kumar Dorbala , Kishore Budumuru , Apostolos Karafillis , Thomas Chadwick Waldman , Theodore E. Anderson , Joel F. Kirk , Edward A. Rainous , Michael E. Eriksen , Mojibur Rahman
Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.
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公开(公告)号：US20240133552A1
公开(公告)日：2024-04-25
申请号：US18314418
申请日：2023-05-08
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Rimple Rangrej , Pradeep Naik , Saket Singh , Deepak Ghiya , Perumallu Vukanti
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00014
Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.
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Patent Agency Ranking
公开(公告)号：US11959643B2
公开(公告)日：2024-04-16
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US11920796B2
公开(公告)日：2024-03-05
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US20230358237A1
公开(公告)日：2023-11-09
申请号：US17840416
申请日：2022-06-14
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Sriram K , Mohandas Nayak , Anantharaman M , Mohan Kannaiah Raju , Prachi Anand Tappu , Deepak Ghiya , Adam Joseph Wangler
CPC classification number: F04D13/0606 , F04D29/70 , F04D29/044 , F04D25/026 , H02K5/10 , H02K9/19
Abstract: Layered barrier cans and methods of producing the same are disclosed herein. An example shroud disclosed herein includes an inner shell including a first non-metallic material, an outer shell including the first non-metallic material or a second non-metallic material, and a metal core shell positioned between the inner shell and the outer shell.
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公开(公告)号：US20240410586A1
公开(公告)日：2024-12-12
申请号：US18808558
申请日：2024-08-19
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Veeraraju Vanapalli , Karthikeyan Sampath , Deepak Ghiya , Perumallu Vukanti , Rajendra Mahadeorao Wankhade , Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.
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公开(公告)号：US12055054B2
公开(公告)日：2024-08-06
申请号：US17234371
申请日：2021-04-19
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas J. Kray , Veeraraju V , Deepak Ghiya , Sreekanth Kumar Dorbala , Kishore Budumuru , Apostolos Karafillis , Thomas Chadwick Waldman , Theodore E Anderson , Joel F. Kirk , Edward A. Rainous , Michael E Eriksen , Mojibur Rahman
CPC classification number: F01D21/045 , F01D25/24 , F05D2220/36 , F05D2240/20
Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.
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