公开(公告)号：US09400110B2

公开(公告)日：2016-07-26

申请号：US13656219

申请日：2012-10-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Terrel Kuhn ,  Vinayender Kuchana ,  Veeraraghava Raju Hasti ,  Raymond Gage ,  Sunil James

IPC: F02C1/00 ,  F23R3/00 ,  F23R3/06 ,  F23R3/16 ,  F23R3/54

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/16 ,  F23R3/54 ,  F23R2900/00015 ,  F23R2900/03041 ,  Y02T50/675

Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和连接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。

公开(公告)号：US20140338347A1

公开(公告)日：2014-11-20

申请号：US13747938

申请日：2013-01-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Raymond Gage ,  Nagaraja S. Rudrapatna

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/16 ,  F23R3/50 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675 ,  Y10T29/49231

Abstract: A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight.

Abstract translation: 为涡轮发动机提供燃烧器。 燃烧器包括具有第一侧和第二侧的第一衬套和具有第一侧和第二侧的第二衬套。 第二衬套的第二侧形成具有第一衬里的第二侧的燃烧室，并且燃烧室构造成容纳用于在其中燃烧的空气 - 燃料混合物。 第一衬套限定多个排出冷却孔，其构造成在第一衬里的第二侧上形成冷却空气膜。 多个排出冷却孔包括从第一侧向第二侧以非线性视线延伸的第一渗出冷却孔。