公开(公告)号：US20160334103A1

公开(公告)日：2016-11-17

申请号：US15105427

申请日：2014-12-19

Applicant: United Technologies Corporation

Inventor： Jonathan J. Eastwood ,  Dennis M. Moura ,  Lee E. Bouldin ,  Monica Pacheco-Tougas

IPC: F23R3/06 ,  F23R3/60 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03041 ,  Y02T50/675

Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.

Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器中的衬板。 衬板包括具有唇缘和第一密封凸台的主要稀释通道。 衬里面板还包括具有邻近第一密封凸台的第二密封凸台的次要稀释通道。

公开(公告)号：US20160265772A1

公开(公告)日：2016-09-15

申请号：US15031908

申请日：2014-10-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan J. Eastwood ,  Dennis M. Moura

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R3/02 ,  F23R3/04 ,  F23R3/06

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell and a heat shield. The heat shield includes a base and a plurality of panel rails. The panel rails are connected to the base and extend vertically to the shell. The panel rails include first and second rails. A vertical height of the first rail at a first location is less than a vertical height of the second rail at a second location.

Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁，其包括外壳和隔热罩。 隔热罩包括基座和多个面板导轨。 面板导轨连接到底座并垂直延伸到外壳。 面板导轨包括第一和第二导轨。 在第一位置处的第一轨道的垂直高度小于在第二位置处的第二轨道的垂直高度。

公开(公告)号：US20160201913A1

公开(公告)日：2016-07-14

申请号：US14886973

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

IPC: F23R3/06 ,  F23R3/00

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

Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。