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。