公开(公告)号：US10196931B2

公开(公告)日：2019-02-05

申请号：US15023309

申请日：2014-09-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy A. Romanov

IPC: F01D11/08 ,  F01D11/24 ,  F01D25/12

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body.

公开(公告)号：US10145257B2

公开(公告)日：2018-12-04

申请号：US14885278

申请日：2015-10-16

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Paul M. Lutjen ,  Kevin J. Ryan ,  Ken F. Blaney

IPC: F01D11/08 ,  F01D25/12 ,  F01D11/02 ,  F16J15/44

Abstract: According to various embodiments, disclosed is a blade outer air seal assembly for a turbine engine comprising a main body portion that extends generally axially, with respect to a central axis of the turbine engine, from a leading edge portion of the main body to a trailing edge portion of the main body, wherein the leading edge portion includes a leading edge wall having a undercut profile along at least a portion of the leading edge wall, wherein the main body portion comprises cooling passages comprising a leading edge cooling passage adjacent to the leading edge wall, having a leading edge periphery on a side of the leading edge cooling passage adjacent to the leading edge wall, which generally conforms to the undercut profile of the leading edge wall.

公开(公告)号：US20170051624A1

公开(公告)日：2017-02-23

申请号：US15118521

申请日：2015-02-12

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Jose R. Paulino ,  Ken F. Blaney

IPC: F01D11/08

CPC classification number: F01D11/08 ,  B22C9/10 ,  B22C9/24 ,  F01D11/24 ,  F05D2230/211 ,  F05D2240/11 ,  F05D2260/204 ,  F05D2260/22141 ,  F05D2300/13 ,  Y02T50/676

Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.

Abstract translation: 根据本公开的示例性方面的叶片外部空气密封件尤其包括围绕叶片阵列周向分布的主体。 主体具有多个凹槽，其可以例如改善涡轮机的空气动力学效率。 翅片在多个凹槽的第一凹槽和第二凹槽之间。 翅片从主体径向延伸并且终止于提供一个或多个冷却出口的径向内部翅片面。

公开(公告)号：US20170051623A1

公开(公告)日：2017-02-23

申请号：US14830812

申请日：2015-08-20

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Dominic J. Mongillo, JR. ,  Matthew A. Devore

IPC: F01D11/08 ,  F01D25/12

CPC classification number: F01D11/08 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall portion and a leading edge cooling channel that extends through the wall portion. The leading edge cooling channel includes at least one first cooling passage separated from at least one serpentine cooling passage.

Abstract translation: 燃气涡轮发动机部件包括延伸穿过壁部的壁部和前缘冷却通道。 前缘冷却通道包括与至少一个蛇形冷却通道分离的至少一个第一冷却通道。

公开(公告)号：US20160319698A1

公开(公告)日：2016-11-03

申请号：US15104092

申请日：2014-12-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy A. Romanov

IPC: F01D25/12 ,  F01D11/08

CPC classification number: F01D25/12 ,  F01D11/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is provided in the second wall at the first end. An outlet is provided at the second end.

Abstract translation: 燃气涡轮发动机部件包括包括提供冷却通道的第一壁和第二壁的结构。 冷却通道从第一端延伸到第二端。 冲击入口孔的一组在第一端设置在第二壁上。 在第二端设有出口。

公开(公告)号：US20160237852A1

公开(公告)日：2016-08-18

申请号：US15023309

申请日：2014-09-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy A. Romanov

IPC: F01D25/12 ,  F01D11/08

CPC classification number: F01D25/12 ,  F01D11/08 ,  F01D11/24 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/209 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body.

Abstract translation: 本公开的一个示例性实施例涉及一种包括具有主体的部件的燃气涡轮发动机。 主体包括一个曲折的冷却通道，其提供在主体的第一表面中的入口与主体的第二表面中的出口之间延伸的流动路径。

公开(公告)号：US20160160760A1

公开(公告)日：2016-06-09

申请号：US14216014

申请日：2014-03-17

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Mark F. Zelesky

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01D11/122 ,  F05D2240/11 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine component for a gas turbine engine includes a multiple of self-opening cooling passages each of which defines a self-opening cooling passage axis that extends through a gas path surface.

Abstract translation: 用于燃气涡轮发动机的涡轮机部件包括多个自开式冷却通道，每个冷却通道限定了延伸穿过气体通道表面的自开式冷却通道轴线。

公开(公告)号：US20140127006A1

公开(公告)日：2014-05-08

申请号：US13668398

申请日：2012-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy A. Romanov ,  Brian Duguay ,  Russell E. Keene

IPC: F01D11/08

CPC classification number: F01D25/246 ,  F01D9/04 ,  F01D11/08 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/221 ,  Y02T50/676 ,  Y02T50/6765

Abstract: A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.

Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括第一侧表面，第二侧表面和壁。 该壁在第一侧表面和第二侧表面之间延伸并且在其中形成有一个或多个孔。 孔与第一侧表面和/或第二侧表面间隔开并且具有在叶片外部空气密封件的表面积的约0.005％至0.450％之间的面积。

公开(公告)号：US10920601B2

公开(公告)日：2021-02-16

申请号：US16520874

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Jose R. Paulino ,  Ken F. Blaney

IPC: F01D11/08 ,  B22C9/10 ,  F01D11/24 ,  B22C9/24

Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets. A sacrificial structure for forming internal cooling passages within a blade outer air seal and a method of cooling an interface between a blade outer air seal and a rotating blade array is also disclosed.

公开(公告)号：US20190316479A1

公开(公告)日：2019-10-17

申请号：US15953531

申请日：2018-04-16

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D11/08 ,  F02C3/06

Abstract: A blade outer air seal for a gas turbine engine includes a seal arc-segment that defines a gaspath side, a non-gaspath side, leading and trailing ends, and first and second circumferential sides. A portion of the gaspath side has a geometrically segmented coating section. The geometrically segmented coating section includes a wall that has an array of cells, and a coating disposed in the array of cells.