公开(公告)号：WO2015053818A3

公开(公告)日：2015-06-18

申请号：PCT/US2014038214

申请日：2014-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  MAX SETH A ,  HARRIS MEGGAN

IPC: F23R3/14

CPC classification number: F23R3/14 ,  B23P19/00 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/00012 ,  Y02T50/675

Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.

Abstract translation: 用于燃气涡轮发动机的燃烧器的旋流器包括围绕旋流器中心纵向轴线限定的旋流器螺纹部分的旋流器外部主体。 用于燃气涡轮发动机的燃烧器的隔板支撑壳包括旋流器凸台，其具有围绕旋流器中心纵向轴线限定的凸起螺纹部分。 燃气涡轮发动机的燃烧器包括具有旋流器凸台的隔板支撑壳体。 燃烧器还包括旋流器，其可以围绕旋流器中心纵向轴线限定的螺纹接口安装到旋流器凸台。

公开(公告)号：WO2015017002A3

公开(公告)日：2015-04-16

申请号：PCT/US2014038198

申请日：2014-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  MAX SETH A ,  HARRIS MEGGAN

IPC: F02C7/22 ,  F23R3/28

CPC classification number: F23R3/28 ,  B23P19/04 ,  F02C7/22 ,  F02C7/2365 ,  F23R3/14 ,  F23R2900/00012 ,  Y02T50/671 ,  Y02T50/675

Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.

Abstract translation: 为燃气涡轮发动机提供旋流器。 旋流器包括具有螺纹部分的旋流器主体和可操作以径向向外弯曲的周向布置的凸片的多个。 周向布置的突片的多个从螺纹部分径向偏移。

公开(公告)号：WO2015002686A3

公开(公告)日：2015-03-19

申请号：PCT/US2014034009

申请日：2014-04-14

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F23M5/00 ,  F02C3/14 ,  F02C7/12 ,  F02C7/24 ,  F23M5/08 ,  F23R3/42

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  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 hemi-spherical protuberance.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬垫面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半球形凸起。

公开(公告)号：WO2015076896A3

公开(公告)日：2015-08-06

申请号：PCT/US2014053807

申请日：2014-09-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER

IPC: F01D9/02 ,  F01D25/28 ,  F02C7/20

CPC classification number: F01D25/28 ,  F01D9/023 ,  F01D9/041 ,  F01D11/003 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/30 ,  F05D2260/36 ,  F23R3/002

Abstract: A gas turbine engine includes a vane and a combustor housing that are supported relative to an engine static structure. A retaining assembly clamps the combustor housing and the vane to one another in an axial direction. A circumferential load transfer assembly circumferentially affixes the vane relative to the engine static structure. The retaining assembly is secured to the circumferential load transfer assembly.

Abstract translation: 燃气涡轮发动机包括相对于发动机静态结构支撑的叶片和燃烧器壳体。 保持组件将燃烧器壳体和叶片沿轴向方向彼此夹紧。 圆周载荷传递组件周向地相对于发动机静态结构固定叶片。 保持组件固定到周向负载传递组件。

公开(公告)号：WO2015047472A3

公开(公告)日：2015-06-04

申请号：PCT/US2014042284

申请日：2014-06-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  KOSTKA JR STANISLAV

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

CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/611 ,  F23M2900/05004 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side of the substrate of a material different than a material of the substrate. A wall assembly for use in a combustor of a gas turbine engine includes a shell with a multiple of impingement flow passages; and a liner panel mounted to the shell, where the panel includes a convective feature which faces the shell. A method of cooling a liner panel for a combustor section of a gas turbine engine includes directing an impingement flow towards a convective feature of a liner panel; and directing an effusion flow though the liner panel.

Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括具有热侧和冷侧的衬底; 在基板的热侧和冷侧中的至少一个上的粘合涂层; 以及在衬底的冷侧与不同于衬底的材料的材料的对流特征。 用于燃气涡轮发动机的燃烧器的壁组件包括具有多个冲击流动通道的壳体; 以及安装到壳体上的衬板，其中面板包括面向壳体的对流特征。 一种冷却燃气涡轮发动机的燃烧器部分的衬板的方法包括将冲击流引向衬板的对流特征; 并引导渗液流过衬垫面板。

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：WO2015047509A2

公开(公告)日：2015-04-02

申请号：PCT/US2014044873

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 ,  F23R3/42

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，其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，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道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。