公开(公告)号：EP3090208A4

公开(公告)日：2017-01-11

申请号：EP14876414

申请日：2014-12-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  KOSTKA STANISLAV

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

CPC classification number: F23R3/002 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/2214 ,  F23R3/005 ,  F23R3/007 ,  F23R2900/00017 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.

公开(公告)号：EP3052786A4

公开(公告)日：2016-11-09

申请号：EP14851011

申请日：2014-09-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOSTKA STANISLAV ,  CUNHA FRANK J

IPC: F02C7/24 ,  F02C3/14 ,  F02C7/12 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23M5/04 ,  F23R3/005 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and 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。 燃烧器壁包括燃烧器外壳和附接到外壳的燃烧器隔热罩。 隔热罩包括第一面板和第二面板，其在重叠接头中密封地接合第一面板。 冷却腔在外壳和隔热罩之间延伸，并且将外壳中的多个孔流体耦合在隔热罩中的多个孔。

公开(公告)号：EP3039340A4

公开(公告)日：2016-08-24

申请号：EP14848461

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA JR STANISLAV ,  JAUSE JONATHAN M ,  HANSON RUSSELL B

IPC: F23M5/08 ,  F02C7/18 ,  F23R3/04 ,  F23R3/42

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括绕轴线的螺旋形流动引导件。 减少燃气涡轮发动机的燃烧器衬板中的稀释通道的再循环的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

公开(公告)号：EP2946092A4

公开(公告)日：2016-08-24

申请号：EP13871786

申请日：2013-01-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ERBAS-SEN NURHAK

IPC: F23R3/00 ,  F23R3/50

CPC classification number: F23R3/04 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03045 ,  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 support shell with a convex profile which faces the heat shield. A further embodiment of the foregoing embodiment of the present disclosure is where the convex profile is defined by a hyperbolic cosine function. A further embodiment of any of the foregoing embodiments of the present disclosure is where the convex profile provides an approximate 4.5 inlet-to-exit area ratio. A further embodiment of any of the foregoing embodiments, of the present disclosure wherein the convex profile provides a flow acceleration toward approximately 0.5 Mach towards an end of a convergent section.

公开(公告)号：EP2859203A4

公开(公告)日：2016-06-29

申请号：EP13799897

申请日：2013-05-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ERBAS-SEN NURHAK

IPC: F02C3/14 ,  F02C7/12 ,  F23R3/06

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A heat shield for a combustor liner includes first linear film cooling slots through the heat shield and second linear film cooling slots through the heat shield. The first linear film cooling slots are run in a row and each of the first linear film cooling slots is angled from the row in a first direction. The second linear film cooling slots also run in the row and each of the second linear film cooling slots is angled from the row in a second direction opposite the first direction. The second linear film cooling slots alternate with the first linear film cooling slots in the row. The first and second linear film cooling slots are connected to form a single, multi-cornered film cooling slot.

公开(公告)号：EP2859273A4

公开(公告)日：2016-02-24

申请号：EP13800229

申请日：2013-05-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  ERBAS-SEN NURHAK

IPC: F23R3/42 ,  F02C3/14 ,  F23R3/60

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

公开(公告)号：EP3077726A4

公开(公告)日：2017-04-12

申请号：EP14867256

申请日：2014-12-04

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.

公开(公告)号：EP3077641A4

公开(公告)日：2017-04-05

申请号：EP14868231

申请日：2014-12-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  KOSTKA STANISLAV JR

IPC: F02C7/12 ,  F02C7/24 ,  F23M5/00 ,  F23M5/08 ,  F23R3/42

CPC classification number: F02C7/18 ,  F02C7/264 ,  F02C7/266 ,  F05D2260/20 ,  F23R3/005 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.

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燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形体。 主体在内表面和外表面之间横向延伸。 内表面在燃烧器壁中限定点火器孔。 外表面垂直在隔热罩和外壳之间。 壳体限定第一冷却孔，空气通过该第一冷却孔被引导以撞击外表面。

公开(公告)号：EP3102883A4

公开(公告)日：2017-03-01

申请号：EP15743044

申请日：2015-02-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  KOSTKA JR STANISLAV

IPC: F23M5/00 ,  F02C7/12 ,  F02C7/24 ,  F23M5/08 ,  F23R3/42

CPC classification number: F23R3/002 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

公开(公告)号：EP3099975A4

公开(公告)日：2016-12-21

申请号：EP15743529

申请日：2015-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOSTKA STANISLAV ,  CUNHA FRANK J ,  HOKE JAMES B ,  SNYDER TIMOTHY S ,  CHEUNG ALBERT K ,  ADAMOPOULOS CHRISTOS

IPC: F23M5/00 ,  F02C7/12

CPC classification number: F23R3/005 ,  F02C7/18 ,  F02K1/822 ,  F05D2260/20 ,  F05D2260/201 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.