公开(公告)号：EP3047110A4

公开(公告)日：2017-07-19

申请号：EP14844169

申请日：2014-09-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER ,  LYONS CHRISTOPHER B

IPC: F01D9/06 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/187 ,  F01D9/065 ,  F01D11/005 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/04

公开(公告)号：EP3022491A4

公开(公告)日：2016-11-09

申请号：EP14852165

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旋流器外部体，其具有围绕旋流器中心纵向轴线限定的旋流器螺纹部分。 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：EP3052862A4

公开(公告)日：2016-11-02

申请号：EP14850438

申请日：2014-08-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER

IPC: F23R3/60 ,  F02C7/24 ,  F23M5/04 ,  F23R3/00

CPC classification number: F23R3/007 ,  F02C7/24 ,  F23M5/04 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/00017 ,  Y02T50/671

公开(公告)号：EP3008392A4

公开(公告)日：2016-07-20

申请号：EP14811706

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER

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

CPC classification number: F23R3/002 ,  F02C7/18 ,  F05D2250/611 ,  F23R3/005 ,  F23R3/44 ,  F23R3/50 ,  F23R3/60

Abstract: A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.

Abstract translation: 用于燃气涡轮发动机的燃烧器的面板包括限定至少一个凸部和至少一个凹部的冷侧。 凹部与通道连通。 一种操作燃气涡轮发动机的燃烧器部分的方法包括：将冲击流引向面板冷侧的多个峰; 将来自多个峰的冲击流引导到面板的冷侧具有多个入口的多个槽; 并引导冲击流通过多个入口和相应的多个通过面板的渗出通道。

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：EP3022422A4

公开(公告)日：2016-11-30

申请号：EP14832788

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多个突出部。 周向布置的突片的多个从螺纹部分径向偏移。

公开(公告)号：EP3044421A4

公开(公告)日：2016-10-12

申请号：EP14863615

申请日：2014-09-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DRAKE CHRISTOPHER

IPC: F01D9/02 ,  F01D9/04 ,  F01D11/00 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F23R3/00

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。 圆周载荷传递组件相对于发动机静态结构周向地固定叶片。 保持组件固定到圆周载荷传递组件。

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

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。