公开(公告)号：US10094287B2

公开(公告)日：2018-10-09

申请号：US14618298

申请日：2015-02-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka, Jr. ,  Frank J. Cunha

IPC: F02C7/18 ,  F23R3/00 ,  F01D5/18 ,  F01D25/08

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling scheme disposed inside the body portion, the cooling scheme including a vascular engineered lattice structure and a heat transfer device adjacent to the vascular engineered lattice structure.

公开(公告)号：US10088161B2

公开(公告)日：2018-10-02

申请号：US15038906

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： Christopher Drake ,  Stanislav Kostka, Jr. ,  Frank J. Cunha

IPC: F23R3/00 ,  F02C7/18

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.

公开(公告)号：US09976743B2

公开(公告)日：2018-05-22

申请号：US14789557

申请日：2015-07-01

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Stanislav Kostka, Jr.

IPC: F23R3/14 ,  F23R3/06 ,  F23R3/00

CPC classification number: F23R3/14 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A dilution hole assembly is provided for a combustor. The dilution hole assembly includes a first wall and at least one outer vane. The first wall extends continuously about a centerline and defines a radially inward hole. The at least one outer vane projects radially inward from the first wall for swirling at least a portion of air flowing through the hole.

公开(公告)号：US20160370008A1

公开(公告)日：2016-12-22

申请号：US14893819

申请日：2014-06-13

Applicant: United Technologies Corporation

Inventor： Christopher Drake ,  Stanislav Kostka, Jr.

IPC: F23R3/00 ,  F23R3/06 ,  F02C3/04

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 ,  Y02T50/6765

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 through 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; 并引导渗流流过衬板。

公开(公告)号：US20160186998A1

公开(公告)日：2016-06-30

申请号：US14910827

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka, Jr. ,  Randal G. McKinney ,  James B. Hoke ,  Timothy S. Snyder ,  Frank J. Cunha

IPC: F23R3/06 ,  F23R3/00 ,  F02C7/18

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

Abstract: 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 and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

Abstract translation: 用于燃气涡轮发动机的燃烧器的壁组件包括：具有沿着轴线的第一内周边的支撑壳体和具有沿轴线的第二内周边的衬板。 第二内周小于第一内周。 用于燃气涡轮发动机的燃烧器中的另一壁组件包括安装在支撑壳和衬板之间的环形垫圈。 环形垫圈限定了一个轮廓的内壁。