公开(公告)号：US10094563B2

公开(公告)日：2018-10-09

申请号：US14644227

申请日：2015-03-11

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Timothy S. Snyder

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/12 ,  F23R3/06 ,  F23R3/14 ,  F02C7/12

Abstract: A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.

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：US09816394B2

公开(公告)日：2017-11-14

申请号：US14221494

申请日：2014-03-21

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Timothy S. Snyder

IPC: F01D25/14 ,  F01D5/18 ,  F01D9/04

CPC classification number: F01D25/14 ,  F01D5/187 ,  F01D9/041 ,  F05D2220/32 ,  F05D2220/328 ,  F05D2220/90 ,  F05D2240/12 ,  F05D2240/128 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/676

Abstract: A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow.

公开(公告)号：US20170159935A1

公开(公告)日：2017-06-08

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

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.

公开(公告)号：US20170108220A1

公开(公告)日：2017-04-20

申请号：US15039071

申请日：2014-12-19

Applicant: United Technologies Corporation

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

IPC: F23R3/00 ,  F02C7/12 ,  F23R3/06

CPC classification number: F23R3/005 ,  F02C7/12 ,  F23R3/06 ,  F23R2900/03042

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell, a heat shield and an annular body. The body at least partially defines a first aperture through the shell and the heat shield. The body also defines one or more second apertures through which air is directed into the first aperture and provides non-uniform cooling to the body.

公开(公告)号：US20170009988A1

公开(公告)日：2017-01-12

申请号：US15113558

申请日：2015-02-03

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/00 ,  F02C7/12

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

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包括外壳和隔热罩的燃烧器壁。 燃烧器壁限定壳体和隔热罩之间的第一和第二腔。 隔热罩限定第一出口和细长的第二出口。 第一出口与第一空腔流体耦合。 第二出口与第二腔流体耦合。 燃烧器壁限定一个具有锥形几何形状的空腔。

公开(公告)号：US20170003027A1

公开(公告)日：2017-01-05

申请号：US15106032

申请日：2015-01-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Stanislav Kostka ,  Frank J. Cunha ,  James B. Hoke ,  Timothy S. Snyder ,  Albert K. Cheung ,  Christos Adamopoulos

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06

CPC classification number: F23R3/005 ,  F02C7/18 ,  F02K1/822 ,  F05D2260/20 ,  F05D2260/201 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.

Abstract translation: 用于燃气涡轮发动机的燃烧器的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锥形销。

公开(公告)号：US20160327273A1

公开(公告)日：2016-11-10

申请号：US15108107

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Timothy S. Snyder

IPC: F23R3/06 ,  F02C3/14 ,  F23R3/14 ,  F23R3/58 ,  F23M5/08

CPC classification number: F23R3/06 ,  F02C3/14 ,  F05D2210/33 ,  F05D2220/32 ,  F05D2240/35 ,  F23M5/085 ,  F23R3/005 ,  F23R3/007 ,  F23R3/14 ,  F23R3/58 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.

Abstract translation: 耐热面板具有邻近燃烧室的隔板和旋流器。 耐热面板包括用于面向燃烧室并且在其上游端限定出第一出口的内板，所述第一出口构造成沿着与隔板相邻的第一方向将冷却空气引导到燃烧室中。 其下游端的第二出口构造成在第二方向上将冷却空气引导到燃烧室中，其中轴向限定在上游和下游端之间。 第一和第二方向具有相反的轴向分量。 还公开了耐热结构和燃烧器。

公开(公告)号：US20160273772A1

公开(公告)日：2016-09-22

申请号：US15034702

申请日：2014-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F05D2240/15 ,  F05D2260/201 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03044

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.

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主体，壳体和隔热板。 面板在外壳和面板之间具有锥形冷却腔连接到外壳。 该面板限定了一个冷却孔，其构造成将空气引导出冷却腔以撞击身体。