公开(公告)号：US10307816B2

公开(公告)日：2019-06-04

申请号：US14922273

申请日：2015-10-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N Slavens ,  James Tilsley Auxier

IPC: B22C9/10 ,  B22F7/08 ,  B22F3/105 ,  B33Y10/00 ,  B33Y80/00 ,  B22D23/06 ,  B22D27/04 ,  B22F5/00 ,  C30B1/02 ,  B28B1/00 ,  B28B7/34

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

公开(公告)号：US20170113265A1

公开(公告)日：2017-04-27

申请号：US14922273

申请日：2015-10-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N Slavens ,  James Tilsley Auxier

IPC: B22C9/10 ,  B33Y80/00 ,  B33Y10/00 ,  B22F7/08 ,  B22F3/105

CPC classification number: B22C9/103 ,  B22D23/06 ,  B22D27/045 ,  B22F3/1055 ,  B22F5/007 ,  B22F7/08 ,  B22F2999/00 ,  B28B1/001 ,  B28B7/346 ,  B33Y10/00 ,  B33Y80/00 ,  Y02P10/292 ,  Y02P10/295 ,  B22F5/04

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

公开(公告)号：US10179948B2

公开(公告)日：2019-01-15

申请号：US14689461

申请日：2015-04-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brooks E Snyder ,  Thomas J Martin ,  Thomas N Slavens

IPC: C23C16/48 ,  F01D5/28 ,  C23C16/455 ,  C23C16/40 ,  C23C16/04

Abstract: A method for coating a turbine engine component, said method includes the steps of: placing the component into a chamber; injecting a non-reactive carrier gas containing a coating material into the chamber; and forming a coating on a desired portion of the component by locally heating the desired portion of the component by redirecting a directed energy beam onto the desired portion of the component.

公开(公告)号：US10935240B2

公开(公告)日：2021-03-02

申请号：US14694086

申请日：2015-04-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hoyt Y Chang ,  Brooks E Snyder ,  Thomas N Slavens

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/06 ,  B33Y10/00 ,  B33Y80/00

Abstract: A heat shield for use in a combustor of a gas turbine engine including a plurality of standoff pins that extend from a cold side, the plurality of standoff pins at least partially surround an attachment stud, the cold side including at least one film cooling hole adjacent to the plurality of standoff pins and the attachment stud.

公开(公告)号：US10226812B2

公开(公告)日：2019-03-12

申请号：US14976333

申请日：2015-12-21

Applicant: United Technologies Corporation

Inventor： James Tilsley Auxier ,  Thomas N Slavens

IPC: B22C9/10 ,  B33Y10/00 ,  B33Y80/00 ,  B22C9/24 ,  B22F3/105 ,  B22F5/00 ,  B22F7/02 ,  B22D23/06 ,  B22D27/04 ,  C30B1/02 ,  B22F7/08 ,  B28B1/00 ,  B28B7/34

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes an additively manufactured skeleton core portion manufactured of a refractory metal, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material and a cooling hole shape that extends from the additively manufactured skeleton core portion through the surround core portion, the cooling hole shape operable to form a cooling hole.

公开(公告)号：US10179362B2

公开(公告)日：2019-01-15

申请号：US15214747

申请日：2016-07-20

Applicant: United Technologies Corporation

Inventor： Thomas N Slavens ,  James T Auxier

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/18 ,  B22C9/24

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.