公开(公告)号：US10724739B2

公开(公告)日：2020-07-28

申请号：US15468172

申请日：2017-03-24

Applicant: General Electric Company

Inventor： Kwanwoo Kim ,  Owen Graham ,  Clayton Stuart Cooper

IPC: F23R3/10 ,  F23R3/00

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.

公开(公告)号：US10088165B2

公开(公告)日：2018-10-02

申请号：US14680995

申请日：2015-04-07

Applicant: General Electric Company

Inventor： Quoc Hoai Nguyen ,  Kwanwoo Kim ,  Whitney Epperson ,  Patrick Edward Pastecki ,  Mark Anthony Mueller

IPC: F23M20/00 ,  F23R3/28 ,  F01N1/02 ,  F23R3/00

Abstract: A system includes a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber. The system also includes a resonator configured to receive at least a portion of the fluid flow. The resonator comprises a frequency adjuster configured to change an attenuation frequency of the resonator.

公开(公告)号：US10041676B2

公开(公告)日：2018-08-07

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 Andrew Stowers ,  Shanwu Wang ,  Anquan Wang

IPC: F23R3/02 ,  F23R3/00 ,  F23R3/50 ,  F23R3/60 ,  F02C3/04

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.

公开(公告)号：US20170321895A1

公开(公告)日：2017-11-09

申请号：US15145175

申请日：2016-05-03

Applicant: General Electric Company

Inventor： Kwanwoo Kim ,  Changjin Yoon ,  John Thomas Herbon

IPC: F23M20/00 ,  F23R3/00

CPC classification number: F23M20/005 ,  F05D2260/963 ,  F23R3/002 ,  F23R2900/00014

Abstract: An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

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。