公开(公告)号：US11952911B2

公开(公告)日：2024-04-09

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

CPC classification number: F01D5/18 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/22141

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：US11268526B2

公开(公告)日：2022-03-08

申请号：US14903996

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Roach ,  Barry Barnett ,  Grant O. Cook, III ,  Charles R. Watson ,  Shari L. Bugaj ,  Glenn LeVasseur ,  Wendell V. Twelves, Jr. ,  Christopher J. Hertel ,  Colin J. Kling ,  Matthew A. Turner ,  JinQuan Xu ,  Steven Clarkson ,  Michael Caulfield

IPC: F01D5/28 ,  F04D19/00 ,  F01D5/14 ,  B32B27/34 ,  B32B1/08 ,  B32B1/00 ,  B32B27/28 ,  B32B27/36 ,  F01D5/26 ,  F01D9/04 ,  F01D25/02 ,  F01D25/24 ,  F04D29/38 ,  F04D29/54

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：US11020954B2

公开(公告)日：2021-06-01

申请号：US16703467

申请日：2019-12-04

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: B33Y50/02 ,  G01N29/12 ,  G01N29/44 ,  G01N29/04 ,  B33Y10/00 ,  G01H13/00 ,  B22F10/00 ,  B33Y30/00 ,  B22F3/24 ,  F01D5/00 ,  F01D5/28 ,  B23K15/00 ,  F01D5/14 ,  F01D9/02 ,  F01D11/08 ,  B22F10/10

Abstract: A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis.
An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.

公开(公告)号：US20200232390A1

公开(公告)日：2020-07-23

申请号：US16251492

申请日：2019-01-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ramons A. Reba ,  Bruce L. Morin ,  Daniel L. Gysling ,  Carson A. Roy Thill ,  Jose R. Paulino ,  JinQuan Xu ,  Stephen A. Morford

IPC: F02C7/24 ,  F01D25/04 ,  F01D11/00

Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.

公开(公告)号：US10663168B2

公开(公告)日：2020-05-26

申请号：US15666958

申请日：2017-08-02

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F23M5/08 ,  F23R3/06 ,  F02C7/18 ,  F23R3/00 ,  F23R3/04

Abstract: A combustor assembly for a turbine engine includes a liner panel defining a portion of an inner surface of a combustor chamber. The liner panel includes an end face transverse the inner surface and at least one diffuser through the end face. A method of assembling a combustor for a turbine engine is also disclosed.

公开(公告)号：US20200063573A1

公开(公告)日：2020-02-27

申请号：US16659876

申请日：2019-10-22

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

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

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：US10539026B2

公开(公告)日：2020-01-21

申请号：US15710874

申请日：2017-09-21

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F01D11/08 ,  F01D5/28

Abstract: A gas turbine engine component has an engine component body and at least one hole formed within the engine component body and extends between a hole inlet and a hole outlet. The hole has a first portion with a first roughness and a second portion having a second roughness that is less than the first roughness. The first portion is upstream of the second portion. A gas turbine engine and a method of forming a cooling hole are also disclosed.

公开(公告)号：US20200018234A1

公开(公告)日：2020-01-16

申请号：US16519471

申请日：2019-07-23

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

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

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：US10519778B2

公开(公告)日：2019-12-31

申请号：US15007775

申请日：2016-01-27

Applicant: United Technologies Corporation

Inventor： JinQuan Xu ,  Glenn Levasseur

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

Abstract: A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.

公开(公告)号：US10371381B2

公开(公告)日：2019-08-06

申请号：US14805963

申请日：2015-07-22

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F02C1/00 ,  F23R3/00 ,  F23M20/00 ,  F02C7/24 ,  F23R3/04

Abstract: A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air plenum, and a vascular lattice structure located between the first and second faces for distributing cooling air from the plenum and to the chamber. The vascular lattice structure may be configured to enhance cooling air flow where needed whiling providing structural support. The orientation of the vascular lattice structure may further contribute toward acoustic dampening.