公开(公告)号：EP2956647A4

公开(公告)日：2016-11-02

申请号：EP13874867

申请日：2013-11-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J

IPC: F02C7/18 ,  F23R3/00 ,  F23R3/04 ,  F23R3/42

CPC classification number: F23R3/04 ,  F02C7/18 ,  F02C7/185 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F23R3/002 ,  F23R3/005 ,  F23R3/02 ,  F23R3/06 ,  F23R3/08 ,  F23R3/42 ,  F23R3/425 ,  F23R3/44 ,  F23R3/46 ,  F23R3/50 ,  F23R3/52 ,  F23R3/54 ,  F23R3/56 ,  F23R3/58 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A combustor having U-shaped cooling channels is disclosed. The combustor may include a shell having an impingement hole, a liner spaced from the shell and having an effusion hole; a first partition spanning between the shell and the liner, a second partition spaced from the first partition and spanning between the shell and the liner; and a U-shaped channel defined between the shell and the liner and defined in part by the wall, the channel having upstream and downstream ends both adjacent the first partition and separated by the wall, wherein the impingement hole communicates with the upstream end and the effusion hole communicates with the downstream end.

Abstract translation: 公开了一种具有U形冷却通道的燃烧器。 燃烧器可以包括具有冲击孔的壳体，与壳体间隔开并具有渗出孔的衬套; 跨越所述壳体和所述衬套之间的第一分隔件，与所述第一分隔件隔开并跨越所述壳体和所述衬套之间的第二分隔件; 以及U形通道，其限定在所述壳体和所述衬套之间并且部分地由所述壁限定，所述通道具有邻近所述第一隔板的所述上游和下游端部，并且被所述壁分隔，其中所述冲击孔与所述上游端连通， 渗出孔与下游端连通。

公开(公告)号：EP3039347A4

公开(公告)日：2016-09-21

申请号：EP14841046

申请日：2014-08-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BANGERTER JAMES P ,  LOW KEVIN J ,  HANSON RUSSELL B ,  ERBAS-SEN NURHAK ,  CUNHA FRANK J

IPC: F23R3/42 ,  F02C3/14 ,  F02C7/12 ,  F23M5/04 ,  F23R3/60

CPC classification number: F23R3/002 ,  F02C3/14 ,  F02C7/12 ,  F23R3/005 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03043 ,  Y02T50/675

公开(公告)号：EP2904238A4

公开(公告)日：2016-07-06

申请号：EP13856137

申请日：2013-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  SNYDER TIMOTHY S ,  ERBAS-SEN NURHAK ,  WILLIAMS ALEXANDER W ,  MULE NICHOLAS

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/16 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner. The combustor liner may reduce NOx production and the temperature of the combustion chamber of a gas turbine engine or the like.

Abstract translation: 公开了一种减少到燃烧室的冷却流动并增加冲击孔和渗出孔之间的压降分配的燃烧器衬套。 燃烧器衬套还可以包括加速通道，跳闸条，基座和锥形排出孔，以提供衬套的进一步冷却。 燃烧器衬套可以减少燃气涡轮发动机等的NOx产生和燃烧室的温度。

公开(公告)号：EP2859205A4

公开(公告)日：2015-07-01

申请号：EP13801071

申请日：2013-05-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ERBAS-SEN NURHAK

IPC: F02C3/14 ,  F02C7/12 ,  F23R3/06 ,  F23R3/42

CPC classification number: F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A combustor liner is arcuate in shape and defines an axis and a circumferential direction. The combustor liner includes a first row of dilution openings and a second row of dilution openings. The first row runs in the circumferential direction. The second row runs parallel to the first row and is axially spaced from the first row. Each dilution opening of the second row overlaps in an axial direction a portion of each of two adjacent dilution openings of the first row.

Abstract translation: 燃烧器衬套的形状为弓形并且限定了轴线和圆周方向。 燃烧器衬套包括第一排稀释开口和第二排稀释开口。 第一列沿圆周方向延伸。 第二排平行于第一排延伸并且与第一排轴向间隔开。 第二排的每个稀释开口在轴向上与第一排的两个相邻的稀释开口中的每一个的一部分重叠。

公开(公告)号：EP3102884A4

公开(公告)日：2017-03-01

申请号：EP15743262

申请日：2015-02-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCKINNEY RANDAL G ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV

IPC: F23M5/00 ,  F02C3/14 ,  F02C7/24 ,  F23M5/08 ,  F23R3/42

CPC classification number: F23R3/002 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.

Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括具有外壳和隔热罩的燃烧器壁。 燃烧器壁限定穿过其中的骤冷孔。 燃烧器壁还在外壳和隔热罩之间限定一个空腔。 壳体限定空气被引导到空腔中的第一孔。 隔热罩包括至少部分地限定第二孔的导轨，该第二孔构造成将腔内的至少一些空气引导出燃烧器壁并且朝向骤冷孔。

公开(公告)号：EP3084310A4

公开(公告)日：2017-01-04

申请号：EP14871741

申请日：2014-08-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  KOSTKA JR STANISLAV ,  CUNHA FRANK J

IPC: F23R3/42 ,  F02C3/14 ,  F16B35/04 ,  F23M5/04 ,  F23R3/60

CPC classification number: F23R3/002 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/31 ,  F16B33/004 ,  F23R3/005 ,  F23R3/007 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.

Abstract translation: 一种用于燃气涡轮发动机的衬板。 衬板具有热侧和冷侧。 衬板包括从冷侧延伸的导轨和从冷侧延伸的多个螺柱。 多个螺柱中的至少一个从部分地延伸到轨道。

公开(公告)号：EP3077727A4

公开(公告)日：2016-12-07

申请号：EP14868497

申请日：2014-12-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOSTKA JR STANISLAV ,  CUNHA FRANK J

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/50

CPC classification number: F23R3/005 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.

Abstract translation: 提供了一种用于涡轮发动机的组件。 涡轮发动机组件的燃烧器壁包括壳体，隔热罩和环形体。 环形体延伸穿过燃烧器壁。 环形体至少部分地沿着穿过燃烧器壁的中心线限定了淬火孔。 环形体限定了流体耦合在冷却腔和淬火孔之间的第一冷却孔。 冷却腔位于外壳和隔热罩之间。

公开(公告)号：EP2900925A4

公开(公告)日：2016-11-02

申请号：EP13864570

申请日：2013-09-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ERBAS-SEN NURHAK

IPC: F01D5/14 ,  F02C7/18

CPC classification number: F23R3/16 ,  F23R3/06 ,  F23R3/26 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.

Abstract translation: 用于燃气涡轮发动机的燃烧器部分包括至少部分地延伸到燃烧室中的燃烧器叶片。

公开(公告)号：EP3055537A4

公开(公告)日：2016-10-19

申请号：EP14852050

申请日：2014-10-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ERBAS-SEN NURHAK ,  CUNHA FRANK J

IPC: F02C7/24 ,  F02C3/14 ,  F02C7/12 ,  F23M5/00 ,  F23R3/06 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/08 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.

Abstract translation: 为涡轮发动机提供燃烧器壁，并且包括燃烧器壳体和隔热罩。 隔热罩安装在外壳上，第一和第二腔在外壳和隔热罩之间延伸。 第一腔体将壳体中限定的孔与第二腔流体耦合。 第二腔将第一空腔与限定在隔热罩中的孔流体连接。 壳体和隔热罩围绕第二腔体彼此会聚。

公开(公告)号：EP3008386A4

公开(公告)日：2016-08-03

申请号：EP14820269

申请日：2014-04-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  KOSTKA STANISLAV JR ,  CUNHA FRANK J

IPC: F23M5/00 ,  F02C7/12 ,  F23M5/08 ,  F23R3/00 ,  F23R3/06 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675