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

IPC: F23R3/42 ,  F02C3/02 ,  F02C3/14

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.

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

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/08 ,  F23R3/06 ,  F23R3/34

CPC classification number: F23R3/16 ,  F23R3/002 ,  F23R3/08 ,  F23R3/06 ,  F23R3/346 ,  F23M5/085

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.

公开(公告)号：US11603799B2

公开(公告)日：2023-03-14

申请号：US17130040

申请日：2020-12-22

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade ,  Gurunath Gandikota

IPC: F23R3/28 ,  F02C7/24 ,  F02C7/22

Abstract: 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.

公开(公告)号：US20230003382A1

公开(公告)日：2023-01-05

申请号：US17363088

申请日：2021-06-30

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Rajendra Mahadeorao Wankhade ,  Daniel J. Kirtley ,  Michael Anthony Benjamin

IPC: F23R3/00 ,  F02C7/28

Abstract: 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.

公开(公告)号：US20220390113A1

公开(公告)日：2022-12-08

申请号：US17340816

申请日：2021-06-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Daniel J. Kirtley ,  Shai Birmaher ,  Pradeep Naik

IPC: F23R3/00 ,  F02C3/00 ,  F02C3/14

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 liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

公开(公告)号：US20220390112A1

公开(公告)日：2022-12-08

申请号：US17340703

申请日：2021-06-07

Applicant: General Electric Company

Inventor： 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

IPC: F23R3/00 ,  F02C3/14

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 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.

公开(公告)号：US20220390111A1

公开(公告)日：2022-12-08

申请号：US17340654

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

IPC: F23R3/00 ,  F23R3/60 ,  F02C7/18

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 liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

公开(公告)号：US20200041127A1

公开(公告)日：2020-02-06

申请号：US16051838

申请日：2018-08-01

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Hiranya Kumar Nath ,  Jayanth Sekar ,  Arthur Wesley Johnson ,  Gurunath Gandikota ,  Mayank Krisna Amble ,  Clayton Stuart Cooper

IPC: F23R3/18 ,  F23R3/00

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.

公开(公告)号：US12180890B1

公开(公告)日：2024-12-31

申请号：US18454531

申请日：2023-08-23

Applicant: General Electric Company

Inventor： Nageswar Rao Ganji ,  Ravindra Shankar Ganiger ,  Ambika Shivamurthy ,  Hiranya Kumar Nath ,  Trevor H. Wood

IPC: F02C7/00 ,  F02C9/18

Abstract: Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion.

公开(公告)号：US12049845B2

公开(公告)日：2024-07-30

申请号：US17951619

申请日：2022-09-23

Applicant: General Electric Company

Inventor： Nageswar Rao Ganji ,  Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Ambika Shivamurthy ,  Trevor H. Wood

IPC: F02C6/08 ,  F01D17/10 ,  F01D25/04

CPC classification number: F02C6/08 ,  F01D17/105 ,  F01D25/04 ,  F05D2250/131 ,  F05D2260/606 ,  F05D2260/963

Abstract: Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.