公开(公告)号：US11267576B2

公开(公告)日：2022-03-08

申请号：US14903987

申请日：2014-07-09

Applicant: United Technologies Corporation

Inventor： James T. Roach ,  Colin J. Kling ,  Grant O. Cook, III ,  James J. McPhail ,  Shari L. Bugaj ,  James F. O'Brien ,  Majidullah Dehlavi ,  Scott A. Smith ,  Matthew R. Rader ,  Matthew A. Turner ,  JinQuan Xu

IPC: B64D29/00 ,  B29D22/00 ,  F02K3/04 ,  F01D5/02 ,  F01D25/28

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

公开(公告)号：US20210148235A1

公开(公告)日：2021-05-20

申请号：US16683640

申请日：2019-11-14

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack ,  JinQuan Xu

IPC: F01D5/18

Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.

公开(公告)号：US10731469B2

公开(公告)日：2020-08-04

申请号：US15696307

申请日：2017-09-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： JinQuan Xu ,  James Tilsley Auxier

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

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：US10605092B2

公开(公告)日：2020-03-31

申请号：US15207472

申请日：2016-07-11

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F02K1/82 ,  F01D11/08 ,  F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F01D9/04 ,  F01D25/12 ,  F01D25/24 ,  F04D29/32 ,  F04D29/52 ,  F04D29/54 ,  F04D29/58 ,  F01D9/02 ,  F01D9/06

Abstract: A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.

公开(公告)号：US20200070250A1

公开(公告)日：2020-03-05

申请号：US16673062

申请日：2019-11-04

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: B22F7/08 ,  F23R3/00 ,  F01D9/06 ,  B28B1/00 ,  B23K26/00 ,  B23K15/00 ,  B23K26/342 ,  F01D5/18

Abstract: A method for forming a diffusion cooling hole in a substrate includes removing material from the substrate to form a metering section having an inlet on a first side of the substrate and removing material from the substrate to form a diffusing section that extends between the metering section and an outlet located on a second side of the substrate generally opposite the first side. The method also includes forming a feature on a substrate surface within one of the metering section and the diffusing section. Forming the feature includes depositing a material on the substrate surface and selectively heating the material to join the material with the substrate surface and form the feature.

公开(公告)号：US20190353039A1

公开(公告)日：2019-11-21

申请号：US16526519

申请日：2019-07-30

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/28 ,  C30B29/52 ,  B22C7/02 ,  C30B11/00 ,  B22C9/04 ,  B22D27/04 ,  B33Y70/00 ,  B22C9/10 ,  F01D5/18 ,  B22F3/105 ,  B22F5/00 ,  B33Y80/00

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：US10323522B2

公开(公告)日：2019-06-18

申请号：US15231159

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D25/12

Abstract: A component for a gas turbine engine includes a gas path wall having a first surface, a second surface exposed to hot gas flow, and a cooling hole extending through the gas path wall. The cooling hole includes an inlet formed in the first surface, an outlet formed in the second surface, cooling hole surfaces that define the cooling hole between the inlet and the outlet, and a longitudinal ridge formed along at least one of the cooling hole surfaces. The longitudinal ridge separates the cooling hole into first and second lobes. The cooling hole diverges through the gas path wall, such that cross-sectional area of the cooling hole increases continuously from the inlet through the cooling hole to the outlet.

公开(公告)号：US10280764B2

公开(公告)日：2019-05-07

申请号：US15237416

申请日：2016-08-15

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F23R3/06 ,  F01D9/06

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.

公开(公告)号：US10215030B2

公开(公告)日：2019-02-26

申请号：US14766475

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F01D9/02 ,  F01D11/08 ,  F23R3/02 ,  F01D5/28

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface, an outer skin and a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. At least two lobes are embedded within the diffusion section of the cooling hole. At least one surface of each of the at least two lobes is at least partially cylindrical.

公开(公告)号：US10208603B2

公开(公告)日：2019-02-19

申请号：US14942025

申请日：2015-11-16

Applicant: United Technologies Corporation

Inventor： JinQuan Xu ,  Scott D. Lewis

IPC: F01D5/18 ,  F01D9/06

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. The plurality of crossover passages are arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity.