公开(公告)号：WO2015050592A3

公开(公告)日：2015-06-11

申请号：PCT/US2014042130

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA STANISLAV

IPC: F23M5/00 ,  F02C7/12 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.

Abstract translation: 为燃气涡轮发动机的燃烧器提供衬板。 衬板包括多个传热增强器。 多个传热增强器中的至少一个包括凹陷，其中凹陷包括穿过衬垫板的至少一个通道的入口。

公开(公告)号：EP3008388A4

公开(公告)日：2016-07-20

申请号：EP14850876

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  CUNHA FRANK J ,  KOSTKA STANISLAV

IPC: F23M5/00 ,  F02C7/12 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.

Abstract translation: 为燃气涡轮发动机的燃烧器提供衬板。 衬板包括多个传热增强器。 多个传热增强器中的至少一个包括凹陷，其中凹陷包括通过衬垫面板的至少一个通道的入口。

公开(公告)号：EP2963346B1

公开(公告)日：2017-05-03

申请号：EP15175344

申请日：2015-07-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER-HINCKLEY TRACY A ,  MONGILLO DOMINIC J ,  WAGNER JOEL H ,  ZELESKY MARK F ,  KOSTKA STANISLAV ,  SNYDER TIMOTHY S

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A self-cooled orifice structure, for example a dilution hole structure for a combustor of a gas turbine engine, includes a cold side panel spaced from a hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice communicating through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel, in fluid communication with the cavity, and proximate to a first side of the end walls. A plurality of outlet apertures extend through the hot side panel, in fluid communication with the cavity, and associated with an opposite second side of the end walls.

Abstract translation: 自冷却孔口结构（例如用于燃气涡轮发动机的燃烧器的稀释孔结构）包括与热侧面板间隔开的冷侧面板以及在热侧面板和冷侧面板之间延伸的连续内壁， 小孔通过冷热侧板连通。 该结构的多个端壁处于由冷热侧板和内壁部分地限定的冷却腔中。 每个端壁在热侧板和冷侧板之间延伸并与其接合，并与下一个相邻端壁周向间隔开。 多个入口孔延伸穿过冷侧板，与腔体流体连通并靠近端壁的第一侧。 多个出口孔延伸穿过热侧板，与腔体流体连通并且与端壁的相对的第二侧相关联。

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.

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。