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：US20220290862A1

公开(公告)日：2022-09-15

申请号：US17199244

申请日：2021-03-11

Applicant: General Electric Company

Inventor： Vishal Sanjay Kediya ,  Pradeep Naik ,  Gregory A. Boardman ,  Manampathy G. Giridharan

IPC: F23R3/28 ,  F02C7/22

Abstract: A mixer for providing a fuel-air mixer to a combustor of an engine. The mixer may include a fuel flow and an air flow entering an interior passage of the mixer. The air flow may be comprised of three separate air flows. The first air flow may be parallel to a central axis of the mixer for pulling the fuel into the interior passage. The second air flow may be inclined with respect to the central axis of the mixer and the third air flow may be tangential to the mixer body. The second air flow and the third air flow may push the fuel flow toward the interior passage and away from the boundary layer flow.

公开(公告)号：US20220282870A1

公开(公告)日：2022-09-08

申请号：US17192613

申请日：2021-03-04

Applicant: General Electric Company

Inventor： Kwanwoo Kim ,  Clayton Cooper ,  Steven Vise ,  Shai Birmaher ,  Pradeep Naik ,  Andrew Wickersham

IPC: F23R3/28 ,  F23M20/00 ,  F02C7/22

Abstract: A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.

公开(公告)号：US11286884B2

公开(公告)日：2022-03-29

申请号：US16217625

申请日：2018-12-12

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Clayton Stuart Cooper

IPC: F23R3/34 ,  F02C9/26 ,  F23R3/28 ,  F02K3/10 ,  F23R3/10 ,  F02C3/04

Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage. The fuel-oxidizer mixing passage is configured to provide a flow of fuel-oxidizer mixture to a combustion chamber via the outlet opening.

公开(公告)号：US11073114B2

公开(公告)日：2021-07-27

申请号：US16217546

申请日：2018-12-12

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Clayton Stuart Cooper ,  Joseph Zelina

IPC: F02M29/06 ,  F02M61/14 ,  F23R3/14 ,  F23R3/28

Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage. The fuel-oxidizer mixing passage is configured to provide a flow of fuel-oxidizer mixture to a combustion chamber via the outlet opening.

公开(公告)号：US10890329B2

公开(公告)日：2021-01-12

申请号：US15909211

申请日：2018-03-01

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Jacob Foster ,  Kediya Vishal Sanjay

IPC: F23R3/28 ,  F23D14/64

Abstract: The present disclosure is directed to a fuel injector including a centerbody defining an air inlet opening defined substantially radially through the centerbody; an outer sleeve surrounding the centerbody, and an end wall coupled to the centerbody and the outer sleeve. The outer sleeve defines a radially oriented first air inlet port defined radially outward of the air inlet opening at the centerbody. A mixing passage is defined between the outer sleeve and the centerbody. A first fuel injection port is defined substantially axially through the end wall to the mixing passage. The first fuel injection port defines a first fuel injection opening at the mixing passage between the first air inlet port at the outer sleeve and the air inlet opening at the centerbody.

公开(公告)号：US20200173662A1

公开(公告)日：2020-06-04

申请号：US16203997

申请日：2018-11-29

Applicant: General Electric Company

Inventor： Randall Charles Boehm ,  Gregory Allen Boardman ,  Ajoy Patra ,  David Albin Lind ,  Pradeep Naik ,  Ranjeet Kumar Mishra

IPC: F23R3/28 ,  F23R3/14

Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.

公开(公告)号：US20200158342A1

公开(公告)日：2020-05-21

申请号：US16191850

申请日：2018-11-15

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik

IPC: F23R3/00 ,  F23R3/12 ,  F23R3/28

Abstract: A gas turbine engine including a trapped vortex combustor assembly is generally provided. The combustor assembly includes an inner liner wall extended annularly around a combustor centerline, and an outer liner wall extended annularly around the combustor centerline. The inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The involute wall defines an involute combustion chamber. One or more of the inner liner wall and the outer liner wall each define a first dilution opening and a shaped dilution opening.