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公开(公告)号：US11725817B2
公开(公告)日：2023-08-15
申请号：US17363088
申请日：2021-06-30
发明人： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
CPC分类号： F23R3/08 , F01D9/023 , F23R3/002 , F23R3/06 , F23R3/60 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F23R3/005
摘要： A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
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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
发明人： 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分类号： F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
摘要： 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：US20190285082A1
公开(公告)日：2019-09-19
申请号：US15922153
申请日：2018-03-15
发明人： Veeraraju Vanapalli , Bhaskar Nanda Mondal , Rajendra Mahadeorao Wankhade , Ramana Reddy Kollam
摘要： The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.
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公开(公告)号：US20180231026A1
公开(公告)日：2018-08-16
申请号：US15433366
申请日：2017-02-15
CPC分类号： F02C7/18 , F01D11/001 , F01D11/04 , F04D29/083 , F04D29/542 , F04D29/584 , F05D2240/81 , Y02T50/676
摘要： A compressor for a turbine engine comprises radially spaced inner and outer bands defining a flow path between them, at least one vane extending between the inner and outer bands, a seal adjacent the inner band, and a cooling air circuit through the inner band proximate the seal.
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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
发明人： 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分类号： F23R3/42 , F02C3/02 , F02C3/14 , F05D2220/32 , F05D2240/35
摘要： 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
发明人： 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
摘要： 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
发明人： 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
摘要： 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：US11603799B2
公开(公告)日：2023-03-14
申请号：US17130040
申请日：2020-12-22
发明人： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade , Gurunath Gandikota
摘要： A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.
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公开(公告)号：US20230003382A1
公开(公告)日：2023-01-05
申请号：US17363088
申请日：2021-06-30
发明人： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
摘要： A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
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公开(公告)号：US20220390112A1
公开(公告)日：2022-12-08
申请号：US17340703
申请日：2021-06-07
发明人： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Perumallu Vukanti , Daniel J. Kirtley , Karthikeyan Sampath , Shai Birmaher , Pradeep Naik , Rajendra Mahadeorao Wankhade , Michael Anthony Benjamin , Veeraraju Vanapalli , Deepak Ghiya
摘要： 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 liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.
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