公开(公告)号：US10443425B2

公开(公告)日：2019-10-15

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 ,  B22C9/10 ,  B22C9/24 ,  F01D11/24

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.

公开(公告)号：US20180306049A1

公开(公告)日：2018-10-25

申请号：US16017210

申请日：2018-06-25

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D11/16 ,  F01D25/28 ,  F01D25/14 ,  F01D11/18 ,  F01D25/26 ,  F01D25/24

CPC classification number: F01D11/16 ,  F01D11/18 ,  F01D25/14 ,  F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F01D25/26 ,  F01D25/265 ,  F01D25/28 ,  F05D2220/32 ,  F05D2240/10 ,  F05D2240/20 ,  F05D2240/55 ,  Y02T50/675

Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.

公开(公告)号：US09926799B2

公开(公告)日：2018-03-27

申请号：US14881047

申请日：2015-10-12

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Dominic J. Mongillo, Jr. ,  Paul M. Lutjen

IPC: F01D11/08 ,  F01D25/12 ,  F01D5/18 ,  F01D9/02

CPC classification number: F01D11/08 ,  F01D5/187 ,  F01D9/023 ,  F01D25/12 ,  F05D2220/32 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A gas turbine engine component is provided. The gas turbine engine component has an internal cooling passage having first endwall and a second endwall. A primary inlet aperture is in fluid communication with a coolant supply and the first end of the internal cooling passage. An elongated rib is inside the internal cooling passage and proximate the primary inlet aperture. The elongated rib is configured to direct at least a portion of the coolant from the primary inlet aperture against a proximate one of the first or second endwall and then substantially reverse direction to flow downstream toward a second end of the internal cooling passage. A blade outer air seal (“BOAS”) assembly and a BOAS segment thereof are also provided.

公开(公告)号：US20170107841A1

公开(公告)日：2017-04-20

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 ,  F01D11/02 ,  F01D25/12 ,  F16J15/44

CPC classification number: F01D11/08 ,  F01D11/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2250/314 ,  F05D2260/20 ,  F16J15/44 ,  Y02T50/675

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：US10914192B2

公开(公告)日：2021-02-09

申请号：US16141228

申请日：2018-09-25

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D25/12 ,  F01D9/04 ,  F01D11/08

Abstract: An impingement plate for providing cooling to a gas turbine engine component includes a first surface with a second surface opposite the first surface. The first surface and the second surface are surrounded by a perimeter defining an edge. A first plurality of holes extend through the impingement plate. A plurality of protrusions extend outward from one of the first surface or the second surface and have a distal surface transverse to one of the first surface or the second surface. At least one second impingement hole extends through the distal surface.

公开(公告)号：US10584607B2

公开(公告)日：2020-03-10

申请号：US16017210

申请日：2018-06-25

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D11/16 ,  F01D11/18 ,  F01D25/14 ,  F01D25/24 ,  F01D25/26 ,  F01D25/28

Abstract: A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.

公开(公告)号：US10221767B2

公开(公告)日：2019-03-05

申请号：US14841054

申请日：2015-08-31

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Paul M. Lutjen

IPC: F01D11/08 ,  F02C7/18 ,  F02C3/04 ,  F02C7/28 ,  F01D9/04 ,  F01D25/12 ,  F01D5/18 ,  B22C9/10 ,  B22C9/04

Abstract: A turbine component includes a main body with an upstream end and a downstream end. A cooling passage network is interior to the main body and has multiple cooling passages. A shared passage wall in the cooling passage network includes a cross passage opening connecting each passage partially defined by the shared passage wall. The cross passage further including a pressure balancing feature operable to reduce a local pressure differential in a fluid pressure in each adjacent passage at the cross passage.

公开(公告)号：US10060288B2

公开(公告)日：2018-08-28

申请号：US14879416

申请日：2015-10-09

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Paul M. Lutjen

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

CPC classification number: F01D25/12 ,  F01D11/08 ,  F01D11/12 ,  F01D11/24 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2240/11 ,  F05D2240/307 ,  F05D2240/81 ,  F05D2260/20

Abstract: A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.

公开(公告)号：US20180066539A1

公开(公告)日：2018-03-08

申请号：US15257273

申请日：2016-09-06

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D25/12 ,  F02K3/06 ,  F01D5/18 ,  F02C7/18

CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D5/188 ,  F01D9/02 ,  F02C7/18 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/232 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03044 ,  Y02T50/676

Abstract: Impingement assemblies including an impingement plate having an increased cross-flow structure that forms an increased cross-flow area between the impingement plate and an impingement surface when the impingement plate is installed proximate to the impingement surface. The increased cross-flow structure has a first portion having at least one impingement hole passing through the first portion, the first portion being separated from the impingement surface by an impingement hole height, a second portion separated from the first portion by a separation distance and separated from the impingement surface by a cross-flow structure height, and a third portion extending between the first portion and the second portion. The first portion, the second portion, and the third portion define at least one cross-flow cavity between the impingement plate and the impingement surface, and the cross-flow structure height is greater than the impingement hole height.

公开(公告)号：US09784125B2

公开(公告)日：2017-10-10

申请号：US14704752

申请日：2015-05-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian Duguay ,  Dmitriy A. Romanov

IPC: F01D11/08 ,  F01D25/12 ,  F01D5/18

CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D11/08 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2240/11 ,  F05D2260/20 ,  Y02T50/676

Abstract: A blade outer air seal (BOAS) includes a body defining a core having a forward cavity portion and a plurality of forward hooks extending radially from the body, the hooks extending to a hook height. The BOAS includes a seal surface defined between the forward hooks and which includes a forward side, an aft side, and a seal surface height. The seal surface is aft of the forward cavity portion. The BOAS includes a thermal regulation channel defining an inlet aft of the sealing surface and an outlet defined in fluid communication with the forward cavity portion.