公开(公告)号：US20210348761A1

公开(公告)日：2021-11-11

申请号：US17380494

申请日：2021-07-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Carey Clum ,  Dennis M. Moura

IPC: F23R3/00

Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.

公开(公告)号：US20220381434A1

公开(公告)日：2022-12-01

申请号：US17882315

申请日：2022-08-05

Applicant: Raytheon Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/00 ,  F23M5/08 ,  F23R3/06 ,  F01D25/32

Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

公开(公告)号：US11041391B2

公开(公告)日：2021-06-22

申请号：US16852728

申请日：2020-04-20

Applicant: Raytheon Technologies Corporation

Inventor： Steven D. Porter ,  Shawn M. McMahon ,  Kevin Zacchera ,  Noah Wadsworth ,  Christopher Whitfield ,  Sean D. Bradshaw ,  Dennis M. Moura ,  David Bitzko ,  Alex J. Schneider

IPC: F01D9/02 ,  F01D11/00 ,  F01D25/12 ,  F01D9/04

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.

公开(公告)号：US20200300389A1

公开(公告)日：2020-09-24

申请号：US16899197

申请日：2020-06-11

Applicant: Raytheon Technologies Corporation

Inventor： Joe Ott ,  Dennis M. Moura ,  Stanley J. Funk ,  Shawn Stempinski ,  Roger O. Coffey ,  John J. Rup, JR. ,  Lexia Kironn ,  Gary A. Schirtzinger

IPC: F16L11/22 ,  F16L39/00 ,  B23P15/00 ,  F02C7/22

Abstract: A method is provided involving an additive manufacturing system. This method includes a step of forming a first fluid conduit using the additive manufacturing system. The method also includes a step of providing a fluid coupling. The fluid coupling includes the first fluid conduit and a second fluid conduit. The first fluid conduit is connected to and fluidly coupled with the second fluid conduit. The first fluid conduit has a first configuration. The second fluid conduit has a second configuration that is different than the first configuration.

公开(公告)号：US20220316705A1

公开(公告)日：2022-10-06

申请号：US17839188

申请日：2022-06-13

Applicant: Raytheon Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/00 ,  F23M5/08 ,  F23M5/04 ,  F23R3/60

Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.