公开(公告)号：US11466574B2

公开(公告)日：2022-10-11

申请号：US16983398

申请日：2020-08-03

Applicant: Raytheon Technologies Corporation

Inventor： JinQuan Xu ,  James Tilsley Auxier

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D9/02 ,  F02C3/04

Abstract: A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.

公开(公告)号：US11280268B2

公开(公告)日：2022-03-22

申请号：US16519471

申请日：2019-07-23

Applicant: Raytheon Technologies Corporation

Inventor： JinQuan Xu

IPC: F02C7/18 ,  F02C6/08 ,  F23R3/28 ,  F02C7/224

Abstract: A cooled fuel injector system of a combustor section of a gas turbine engine is provided. At least a part of the fuel injector system is exposed to core gas flow traveling through the engine. The cooled fuel injector system includes a source of a first cooling fluid and a fuel injector system component. The first cooling fluid is at a temperature lower than a temperature of the core gas flow proximate the fuel injector system. The fuel injector system component includes a vascular engineered structure lattice (VESL) structure, which VESL structure is in fluid communication with the source of the cooling fluid.

公开(公告)号：US11236621B2

公开(公告)日：2022-02-01

申请号：US16526519

申请日：2019-07-30

Applicant: Raytheon Technologies Corporation

Inventor： JinQuan Xu

IPC: B22C9/04 ,  F01D5/28 ,  B22C9/10 ,  B22C7/02 ,  B22D27/04 ,  B22F5/00 ,  B33Y70/00 ,  F01D5/18 ,  C30B29/52 ,  C30B11/00 ,  B22F10/20 ,  B33Y80/00 ,  B22F5/04 ,  B33Y10/00

Abstract: A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

公开(公告)号：US10927851B2

公开(公告)日：2021-02-23

申请号：US16367673

申请日：2019-03-28

Applicant: Raytheon Technologies Corporation

Inventor： JinQuan Xu ,  Frederic Tisdall Tenney

IPC: F04D29/66 ,  F01D5/16 ,  F01D5/14 ,  F04D29/54 ,  F02C3/06

Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.