公开(公告)号：WO2015147932A3

公开(公告)日：2015-11-26

申请号：PCT/US2014071615

申请日：2014-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： EASTWOOD JONATHAN J ,  MOURA DENNIS M ,  BOULDIN LEE E ,  PACHECO-TOUGAS MONICA

IPC: F23R3/02 ,  F23M5/00 ,  F23R3/04 ,  F23R3/26

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03041 ,  Y02T50/675

Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.

Abstract translation: 提供用于燃气涡轮发动机的燃烧器的衬垫面板。 衬垫面板包括具有唇部和第一密封凸台的主要稀释通道。 衬垫面板还包括具有邻近第一密封凸台的第二密封凸台的小稀释通道。

公开(公告)号：WO2014055887A3

公开(公告)日：2014-08-28

申请号：PCT/US2013063494

申请日：2013-10-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BANGERTER JAMES P ,  WILLIAMS ALEXANDER W ,  MULE NICHOLAS ,  PACHECO-TOUGAS MONICA

IPC: F02C7/12 ,  F01D25/12 ,  F02C7/20 ,  F02C7/24

CPC classification number: F23R3/06 ,  F23R3/10 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and an effusion hole that communicates through the liner

Abstract translation: 用于涡轮发动机的燃烧器的衬套包括从后侧突出的冷却特征和通过衬套连通的渗出孔

公开(公告)号：WO2015112220A3

公开(公告)日：2015-10-08

申请号：PCT/US2014063849

申请日：2014-11-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOURA DENNIS M ,  PACHECO-TOUGAS MONICA ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E

IPC: F23M5/08 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/06 ,  F23R3/005 ,  F23R3/007 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attached to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧器壁包括外壳和附接到外壳的隔热罩。 隔热罩包括一个导轨和一个连接到空腔中的导轨的冷却元件。 空腔在外壳和隔热罩之间沿垂直方向延伸。 空腔将壳体中的多个孔与隔热罩中的多个孔流体耦合。

公开(公告)号：WO2014197045A2

公开(公告)日：2014-12-11

申请号：PCT/US2014023504

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ERBAS-SEN NURHAK ,  HOKE JAMES B ,  TU JOHN S ,  PACHECO-TOUGAS MONICA

IPC: F02C7/12 ,  F02C3/14 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F02C7/18 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.

Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的燃烧器的衬套组件包括具有多个索环冷却通道的索环。

公开(公告)号：WO2015116269A3

公开(公告)日：2015-10-08

申请号：PCT/US2014063440

申请日：2014-10-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOURA DENNIS M ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E ,  PACHECO-TOUGAS MONICA

IPC: F23M5/00 ,  F23M5/08 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/045 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.

Abstract translation: 涡轮发动机的组件包括燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形区域。 隔热罩连接在外壳上。 土地在壳体和隔热罩之间垂直延伸。 焊盘在焊盘外表面和内表面之间横向延伸，其至少部分地限定燃烧器壁中的淬火孔。 焊盘外表面和内表面之间的横向距离在淬火孔周围变化。

公开(公告)号：WO2015112221A2

公开(公告)日：2015-07-30

申请号：PCT/US2014063859

申请日：2014-11-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOURA DENNIS M ,  PACHECO-TOUGAS MONICA ,  EASTWOOD JONATHAN J ,  BOULDIN LEE E

IPC: F23M5/08 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/202 ,  F23R3/005 ,  F23R3/007 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and a heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.

Abstract translation: 提供了一种用于涡轮发动机的燃烧器，其包括燃烧器壁。 燃烧器壁包括壳体和连接到壳体的隔热罩。 一个或多个冷却空腔限定在壳体和隔热罩之间，并且将壳体中限定的多个孔与限定在隔热罩中的多个孔流体地联接。 隔热罩中的孔包括第一孔和第二孔。 第一孔与隔热屏表面之间的入射角不同于第二孔与表面之间的入射角。

公开(公告)号：DE60323426D1

公开(公告)日：2008-10-23

申请号：DE60323426

申请日：2003-05-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PACHECO-TOUGAS MONICA ,  COSTIGAN FRANCIS K ,  STONER MATTHEW D

IPC: F23R3/12 ,  F23R3/60 ,  F02C7/18 ,  F23R3/00 ,  F23R3/04 ,  F23R3/10 ,  F23R3/28 ,  F23R3/52

公开(公告)号：DE60336954D1

公开(公告)日：2011-06-16

申请号：DE60336954

申请日：2003-05-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PACHECO-TOUGAS MONICA ,  HOKE JAMES B ,  COUGHLAN JOSEPH D III ,  GOETSCHIUS ALAN J

IPC: F23R3/04 ,  F23R3/42 ,  F23R3/00 ,  F23R3/06 ,  F23R3/60

公开(公告)号：EP3047127A4

公开(公告)日：2017-01-18

申请号：EP14843603

申请日：2014-09-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOULDIN LEE E ,  MOURA DENNIS M ,  EASTWOOD JONATHAN J ,  PACHECO-TOUGAS MONICA

IPC: F02C7/12 ,  F02C7/18 ,  F23M5/04 ,  F23R3/00 ,  F23R3/06 ,  F23R3/42 ,  F23R3/60

CPC classification number: F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F23R3/002 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03041 ,  Y02T50/675

公开(公告)号：EP3047128A4

公开(公告)日：2016-08-24

申请号：EP14844554

申请日：2014-09-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOULDIN LEE E ,  EASTWOOD JONATHAN J ,  MOURA DENNIS M ,  PACHECO-TOUGAS MONICA

IPC: F02C7/12 ,  F02C7/24 ,  F23M5/04 ,  F23R3/04 ,  F23R3/06 ,  F23R3/42

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/04 ,  F23R3/60 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.