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公开(公告)号：US11774098B2
公开(公告)日：2023-10-03
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
CPC classification number: F23R3/16 , F23R3/002 , F23R3/06 , F23R3/08 , F23R3/346 , F23M5/085 , F23M2900/05002 , F23R2900/00014 , F23R2900/03042
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 a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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公开(公告)号：US20220390110A1
公开(公告)日：2022-12-08
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
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 a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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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：US20230417415A1
公开(公告)日：2023-12-28
申请号：US18464550
申请日：2023-09-11
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R. , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
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 a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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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：US12085283B2
公开(公告)日：2024-09-10
申请号：US17340764
申请日：2021-06-07
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
CPC classification number: F23R3/42 , F02C3/02 , F02C3/14 , F05D2220/32 , F05D2240/35
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：US20220390115A1
公开(公告)日：2022-12-08
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
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：US20220390114A1
公开(公告)日：2022-12-08
申请号：US17340764
申请日：2021-06-07
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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