公开(公告)号：US20170009986A1

公开(公告)日：2017-01-12

申请号：US14794016

申请日：2015-07-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nayan Vinodbhai Patel ,  Kwanwoo Kim ,  Chad Holden Sutton ,  Duane Douglas Thomsen ,  Craig Alan Gonyou ,  Harris Daniel Abramson ,  James A. Russo ,  Robert Andrews Stowers ,  Shanwu Wang ,  Anquan Wang

IPC: F23R3/00 ,  F02C3/04

CPC classification number: F23R3/002 ,  F02C3/04 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

Abstract translation: 提供了一种用于限定轴向方向的燃气涡轮发动机的燃烧器组件。 燃烧器组件通常包括衬套，环形圆顶和偏转板。 衬垫至少部分地限定燃烧室。 环形拱顶限定第一腔并且具有多个冲击孔，并且偏转板限定锥形表面和平坦表面，其中多个冷却孔限定穿过偏转板。 环形圆顶和偏转板被定位在一起以限定通过多个冲击孔与第一空腔流体连通的第二腔。 此外，第二空腔通过多个冷却孔与燃烧室流体连通。