公开(公告)号：US20180010797A1

公开(公告)日：2018-01-11

申请号：US15203914

申请日：2016-07-07

Applicant: General Electric Company

Inventor： Mark Willard Marusko ,  Michael Alan Stieg ,  Brian Christopher Towle

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00014

Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

公开(公告)号：US20170059160A1

公开(公告)日：2017-03-02

申请号：US14842883

申请日：2015-09-02

Applicant: General Electric Company

Inventor： Nicholas John Bloom ,  Daniel Kirtley ,  Michael Alan Stieg ,  Brian Christopher Towle ,  Chad Holden Sutton

IPC: F23R3/00

CPC classification number: F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00012

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括至少部分地限定燃烧室并且在后端大致沿轴向方向的前端之间延伸的衬套。 燃烧器组件还包括环形圆顶，其包括限定用于接收衬套的前端的槽的封闭表面。 盖子定位在衬套的前端并且至少部分地定位在由环形圆顶的封闭表面限定的槽内。 盖包括被配置为接触环形圆顶的封闭表面和衬垫的前端中的至少一个的表面。 这种构造可以在衬套的前端和环形圆顶之间形成基本上气密的密封，尽管组件之间相对热膨胀。