公开(公告)号：US10317080B2

公开(公告)日：2019-06-11

申请号：US15037484

申请日：2014-12-03

Applicant: United Technologies Corporation

Inventor： John S. Tu, Jr. ,  Timothy S. Snyder ,  James B. Hoke ,  James P. Bangerter ,  Dennis J. Duhamel ,  David A. Burns

IPC: F23R3/00 ,  F23R3/06

Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

公开(公告)号：US20160281988A1

公开(公告)日：2016-09-29

申请号：US15037484

申请日：2014-12-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John S. Tu, JR. ,  Timothy S. Snyder ,  James B. Hoke ,  James P. Bangerter ,  Dennis J. Duhamel ,  David A. Burns

IPC: F23R3/06 ,  F23R3/00

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

Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

Abstract translation: 用于燃气涡轮发动机的燃烧器中的衬板包括一个包括多个喷射通道的前部区域，每个喷射通道以与燃烧气体的局部涡流方向一致的方向指向。 用于燃气涡轮发动机的燃烧器中的另一衬里面板包括稀释通道前方的前部区域和前部区域的尾部后部区域。 前部区域包括多个通常沿周向引导的排出通道。 后部区域包括多个通过轴向大体定向的排出通道。 一种冷却燃气涡轮发动机的燃烧器内的壁组件的方法包括在与燃烧气体的局部涡流方向一致的前向区域内定向多个排出通道。

公开(公告)号：EP2141329A2

公开(公告)日：2010-01-06

申请号：EP09250927.2

申请日：2009-03-30

Applicant: United Technologies Corporation

Inventor： Smith, Craig F. ,  David A. Burns

IPC: F01D9/02 ,  F23R3/00

CPC classification number: F23R3/002 ,  F01D5/186 ,  F01D9/023 ,  F05D2260/201 ,  F23R2900/03044

Abstract: An impingement cooling sleeve (50) includes a sleeve body (51) having an inner surface (52) to face a transition duct (30) and an outer surface (54) facing opposite the inner surface (52). At least one cooling hole (58) is formed within the sleeve body (51) and is used to direct cooling air toward the transition duct (30). At least one conduit member (60) is attached to the sleeve body (51) and is associated with the at least one cooling hole (58). The conduit member (60) has a first opening (62) to define an air inlet and a second opening (64) to define an air outlet. In one example, the first opening (62) is spaced apart from the outer surface (54) of the sleeve body (51) by a distance (D). In one example, the first opening (62) comprises an annular end face surface (78) that defines a plane (P) that is obliquely orientated relative to the outer surface (54) of the sleeve body (51).

Abstract translation: 冲击冷却套筒（50）包括具有面向过渡管道（30）的内​​表面（52）和与内表面（52）相对的外表面（54）的套筒主体（51）。 至少一个冷却孔（58）形成在套管主体（51）内，用于将冷却空气引向过渡管道（30）。 至少一个导管构件（60）附接到套筒主体（51）并与至少一个冷却孔（58）相关联。 导管构件（60）具有限定空气入口的第一开口（62）和限定空气出口的第二开口（64）。 在一个示例中，第一开口（62）与套筒主体（51）的外表面（54）间隔开距离（D）。 在一个示例中，第一开口（62）包括限定相对于套筒主体（51）的外表面（54）倾斜定向的平面（P）的环形端面表面（78）。

公开(公告)号：EP2141329A3

公开(公告)日：2013-03-06

申请号：EP09250927.2

申请日：2009-03-30

Applicant: United Technologies Corporation

Inventor： Smith, Craig F. ,  David A. Burns

IPC: F01D9/02 ,  F23R3/00

CPC classification number: F23R3/002 ,  F01D5/186 ,  F01D9/023 ,  F05D2260/201 ,  F23R2900/03044

Abstract: An impingement cooling sleeve (50) includes a sleeve body (51) having an inner surface (52) to face a transition duct (30) and an outer surface (54) facing opposite the inner surface (52). At least one cooling hole (58) is formed within the sleeve body (51) and is used to direct cooling air toward the transition duct (30). At least one conduit member (60) is attached to the sleeve body (51) and is associated with the at least one cooling hole (58). The conduit member (60) has a first opening (62) to define an air inlet and a second opening (64) to define an air outlet. In one example, the first opening (62) is spaced apart from the outer surface (54) of the sleeve body (51) by a distance (D). In one example, the first opening (62) comprises an annular end face surface (78) that defines a plane (P) that is obliquely orientated relative to the outer surface (54) of the sleeve body (51).