公开(公告)号：US20230358170A1

公开(公告)日：2023-11-09

申请号：US17662535

申请日：2022-05-09

Applicant: General Electric Company

Inventor： Juntao Zhang ,  Nicholas R. Overman ,  Steven C. Vise ,  Andrew Wickersham ,  Michael A. Benjamin

IPC: F02C7/04

CPC classification number: F02C7/04 ,  F05D2240/35

Abstract: A diffuser for a combustor of a turbomachine engine. The diffuser includes a body having a first annular surface and a second annular surface that define a passage, the passage being configured to cause air to flow along the passage to a first component of the combustor. The first annular surface includes an opening that is configured to cause air to flow in a direction away from the passage to a second component of the combustor.

公开(公告)号：US20230304414A1

公开(公告)日：2023-09-28

申请号：US17656106

申请日：2022-03-23

Applicant: General Electric Company

Inventor： Nicholas R. Overman

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05D2240/57 ,  F05D2260/38

Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.

公开(公告)号：US20230280034A1

公开(公告)日：2023-09-07

申请号：US17653376

申请日：2022-03-03

Applicant: General Electric Company

Inventor： Nicholas R. Overman ,  Aaron J. Glaser

IPC: F23R3/58 ,  F23R3/12

CPC classification number: F23R3/58 ,  F23R3/12

Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.

公开(公告)号：US20220349581A1

公开(公告)日：2022-11-03

申请号：US17860990

申请日：2022-07-08

Applicant: General Electric Company

Inventor： Brett A. Rich ,  Michael A. Benjamin ,  Nicholas R. Overman ,  Aaron J. Glaser

IPC: F23R3/20 ,  F23R3/28 ,  F02K3/10

Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.

公开(公告)号：US11448175B1

公开(公告)日：2022-09-20

申请号：US17337886

申请日：2021-06-03

Applicant: General Electric Company

Inventor： Nicholas R. Overman

IPC: F02M61/18 ,  F02M45/08 ,  F02M63/02 ,  F02M21/02

Abstract: A fuel nozzle for a combustor includes a fuel body, a primary fuel passage having a primary fuel outlet, and a secondary fuel passage having a secondary fuel outlet, the secondary fuel passage being non-concentric with the primary fuel passage. The primary fuel outlet and the secondary fuel outlet are non-parallel. An axial centerline of the primary fuel outlet is angled with respect to an axial centerline of the primary fuel passage and an axial centerline of the secondary fuel outlet is colinear with an axial centerline of the secondary fuel passage. Also provided is a method of introducing non-concentric, non-parallel fuel flows to a combustor is also provided.

公开(公告)号：US11408610B1

公开(公告)日：2022-08-09

申请号：US17166477

申请日：2021-02-03

Applicant: General Electric Company

Inventor： Brett A. Rich ,  Michael A. Benjamin ,  Nicholas R. Overman ,  Aaron J. Glaser

IPC: F23R3/20 ,  F02K3/10 ,  F23R3/28

Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.