公开(公告)号：US10072846B2

公开(公告)日：2018-09-11

申请号：US14791684

申请日：2015-07-06

Applicant: General Electric Company

Inventor： Sarah Marie Monahan ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Matthieu Marc Masquelet

IPC: F23R3/28 ,  F23R3/34 ,  F23C5/08 ,  F23R3/58 ,  F23R3/12 ,  F23R3/04 ,  F23C5/00 ,  F23R3/42 ,  F23C5/32 ,  F23R3/02 ,  F23R3/10 ,  F23C5/24 ,  F23R3/06

CPC classification number: F23R3/286 ,  F05D2240/35 ,  F23C5/00 ,  F23C5/08 ,  F23C5/10 ,  F23C5/24 ,  F23C5/32 ,  F23R3/02 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/10 ,  F23R3/12 ,  F23R3/34 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F23R2900/00015 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.

公开(公告)号：US20170009993A1

公开(公告)日：2017-01-12

申请号：US14791684

申请日：2015-07-06

Applicant: General Electric Company

Inventor： Sarah Marie Monahan ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Matthieu Marc Masquelet

IPC: F23R3/28 ,  F23R3/34

CPC classification number: F23R3/286 ,  F05D2240/35 ,  F23C5/00 ,  F23C5/08 ,  F23C5/10 ,  F23C5/24 ,  F23C5/32 ,  F23R3/02 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/10 ,  F23R3/12 ,  F23R3/34 ,  F23R3/346 ,  F23R3/42 ,  F23R3/58 ,  F23R2900/00015 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675

Abstract: A combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two annular trapped vortex cavities are located on the combustor liner and staged axially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities spaced apart from a radially outer wall and extending between an aft wall and a forward wall of each cavity. A plurality of injectors are configured tangentially relative to the circular radially outer wall to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid. A gas turbine engine including the combustor assembly is disclosed.

Abstract translation: 一种燃烧器组件，其包括在其中限定用于主流体的下游流动的燃烧室的燃烧器衬套。 至少两个环形的被捕获的涡流腔位于燃烧器衬套上并且沿轴向间隔分开。 空腔开口位于与径向外壁间隔开并在每个空腔的后壁和前壁之间延伸的至少两个环形捕获涡流腔中的每一个的径向内端。 多个喷射器相对于圆形径向外壁切向配置，以提供空气和燃料的喷射，以在相应的环形捕获的涡流空腔内形成燃料和空气混合物的环形旋转捕获涡流。 空腔开口处的燃料和空气混合物的环形旋转捕获的涡流基本上垂直于主流体的下游流动。 公开了一种包括燃烧器组件的燃气涡轮发动机。

公开(公告)号：US09803552B2

公开(公告)日：2017-10-31

申请号：US14927578

申请日：2015-10-30

Applicant: General Electric Company

Inventor： Yuxin Zhang ,  Obulesu Chatakonda ,  Soumya Gudiyella ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Matthieu Marc Masquelet ,  Shashank Yellapantula

IPC: F23R3/28 ,  F02C7/22 ,  F02C7/04

CPC classification number: F02C7/222 ,  F02C7/04 ,  F23R3/28 ,  F23R3/286 ,  F23R2900/00004

Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.

公开(公告)号：US20170122211A1

公开(公告)日：2017-05-04

申请号：US14927578

申请日：2015-10-30

Applicant: General Electric Company

Inventor： Yuxin Zhang ,  Obulesu Chatakonda ,  Soumya Gudiyella ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Matthieu Marc Masquelet ,  Shashank Yellapantula

IPC: F02C7/22 ,  F23R3/28 ,  F02C7/04

CPC classification number: F02C7/222 ,  F02C7/04 ,  F23R3/28 ,  F23R3/286 ,  F23R2900/00004

Abstract: A fuel injection system for use in a combustor of a turbine assembly includes a substantially annular fuel injection housing at least partially defining an annular cavity. The fuel injection system also includes a fuel manifold and an air manifold. The fuel manifold includes a plurality of fuel injection ports extending through the fuel injection housing. The air manifold includes a first plurality of air injection ports and a second plurality of air injection ports that each extends through the fuel injection housing.

公开(公告)号：US10712002B2

公开(公告)日：2020-07-14

申请号：US14801962

申请日：2015-07-17

Applicant: General Electric Company

Inventor： Matthieu Marc Masquelet ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Sarah Marie Monahan

IPC: F23R3/00 ,  F23R3/28 ,  F23R3/60 ,  F23R3/10 ,  F23R3/26 ,  F23R3/20 ,  F23R3/04

Abstract: A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.

公开(公告)号：US20170016620A1

公开(公告)日：2017-01-19

申请号：US14801962

申请日：2015-07-17

Applicant: General Electric Company

Inventor： Matthieu Marc Masquelet ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Sarah Marie Monahan

IPC: F23R3/00 ,  F23R3/28

Abstract: A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括圆顶组件，联接到圆顶组件的燃料喷嘴和整流罩组件。 整流罩组件包括联接到圆顶组件的径向内部整流罩，以及包括第一整流罩构件和每个围绕燃料喷嘴定位的第二整流罩构件的径向外罩。 第一和第二整流罩构件基本上对准以限定基本上连续的流动路径，其构造成引导围绕圆顶组件的空气流。