公开(公告)号：US20160003083A1

公开(公告)日：2016-01-07

申请号：US14767314

申请日：2014-01-27

Applicant: United Technologies Corporation

Inventor： Robert P. Delisle ,  Paul R. Faughnan, JR. ,  Christopher F. O'Neill ,  Jesse R. Boyer

IPC: F01D11/12 ,  F02C3/04 ,  F02C7/28 ,  F16J15/16

CPC classification number: F01D11/122 ,  F02C3/04 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2300/514 ,  F16J15/16 ,  F16J15/444

Abstract: An abradable seal for a gas turbine engine includes a seal body that has a seal side and a non-seal side. The seal body includes an abradability characteristic that varies by locality.

Abstract translation: 用于燃气涡轮发动机的可磨损密封件包括具有密封侧和非密封侧的密封体。 密封体包括随地点变化的耐磨特性。

公开(公告)号：US20150321422A1

公开(公告)日：2015-11-12

申请号：US14632857

申请日：2015-02-26

Applicant: United Technologies Corporation

Inventor： Jesse R. Boyer

IPC: B29C67/00

CPC classification number: B29C67/0077 ,  B22F3/1055 ,  B22F2003/1056 ,  B22F2003/1057 ,  B22F2203/03 ,  B22F2999/00 ,  B29C64/153 ,  B29C64/386 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02 ,  Y02P10/295

Abstract: A system for additive manufacturing a component includes an additive manufacturing machine for building a component layer by layer and a first sensor configured to collect a first physical property data for each layer of the component as each layer is formed by the additive manufacturing machine. The system also includes a second sensor configured to collect a second physical property data for each layer of the component as each layer is formed by the additive manufacturing machine. A computing device is operatively connected to the first and second sensors and configured to receive the first physical property data and the second physical property data of the component and configured to compare the first physical property data with the second physical property data to determine a potential failure mode in the component.

Abstract translation: 一种用于添加剂制造组件的系统包括用于逐层建造部件的添加剂制造机和构造成当由添加剂制造机形成每层时，为每个部件层收集第一物理属性数据的第一传感器。 该系统还包括第二传感器，该第二传感器被配置为当由添加剂制造机构形成每个层时，为该组件的各层收集第二物理性质数据。 计算设备可操作地连接到第一和第二传感器并且被配置为接收组件的第一物理属性数据和第二物理属性数据，并且被配置为将第一物理属性数据与第二物理属性数据进行比较以确定潜在故障 组件中的模式。

公开(公告)号：US11359543B2

公开(公告)日：2022-06-14

申请号：US16434453

申请日：2019-06-07

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesse R. Boyer ,  Evan J. Butcher ,  Michael Winter ,  Jesus A. Garcia ,  Sean R. Jackson

IPC: F02C7/055

Abstract: A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

公开(公告)号：US11260649B2

公开(公告)日：2022-03-01

申请号：US16533974

申请日：2019-08-07

Applicant: United Technologies Corporation

Inventor： Christopher F. O'Neill ,  Jesse R. Boyer ,  Anthony Pizzola

IPC: B22F12/00 ,  B33Y40/00 ,  B33Y50/02 ,  B29C64/321 ,  B29C64/343 ,  B29C64/336 ,  G01F11/18 ,  B33Y30/00 ,  B28B1/00 ,  B23K26/342 ,  B23K26/70 ,  F16K3/02 ,  F16K3/03 ,  B65G11/20 ,  B22F10/10 ,  B29C64/329 ,  B29C64/153 ,  B33Y10/00

Abstract: An additive manufacturing system can include a powder dispenser; a gate adjacent to the powder dispenser; a recoater blade system; and a control operable to move the gate with respect to the powder dispenser to selectively dispense powder from the powder dispenser.

公开(公告)号：US11199136B2

公开(公告)日：2021-12-14

申请号：US16152848

申请日：2018-10-05

Applicant: United Technologies Corporation

Inventor： Evan Butcher ,  Jesse R. Boyer ,  Om P. Sharma ,  Lawrence Binek ,  Bryan G. Dods ,  Vijay Narayan Jagdale

IPC: F02C7/25 ,  B33Y80/00 ,  B33Y10/00 ,  F02C7/04 ,  B22F10/20

Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

公开(公告)号：US11174744B2

公开(公告)日：2021-11-16

申请号：US16148616

申请日：2018-10-01

Applicant: United Technologies Corporation

Inventor： Lawrence Binek ,  Tommy Skiba ,  Matthew B. Kennedy ,  Evan Butcher ,  Jesse R. Boyer ,  Vijay Narayan Jagdale ,  Dmytro Mykolayovych Voytovych

IPC: F01D5/34 ,  F01D5/14

Abstract: An assembly for use in an attritable engine includes a hub and a blade. The hub is configured to rotate about a centerline axis passing through a center of the hub and is formed with a first type of layer-by-layer additive manufacturing process. The blade is connected to and extends radially outward from the hub. The blade is formed with a second type of layer-by-layer additive manufacturing process that is different than the first layer-by-layer additive manufacturing process. The hub and the blade are integrally formed together as a single piece of material with a layer-by-layer additive manufacturing process. The blade includes a root of a first material, a platform connected to the root, an airfoil connected to and extending from the platform, and a tip connected on a distal end of the airfoil opposite from the root. The platform includes a material that is different from the first.

公开(公告)号：US11156156B2

公开(公告)日：2021-10-26

申请号：US16151728

申请日：2018-10-04

Applicant: United Technologies Corporation

Inventor： Lawrence Binek ,  Jesse R. Boyer ,  Om P. Sharma ,  Evan Butcher ,  Bryan G. Dods ,  Vijay Narayan Jagdale

IPC: F02C7/22 ,  F02K3/10 ,  B33Y80/00 ,  F23R3/20 ,  F02C3/05 ,  F02C3/14 ,  F23R3/34 ,  F23R3/54

Abstract: A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

公开(公告)号：US20210254832A1

公开(公告)日：2021-08-19

申请号：US16791487

申请日：2020-02-14

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Timothy S. Snyder ,  Jesse R. Boyer

IPC: F23R3/28 ,  F02C7/22 ,  F02C7/24 ,  B22F5/00

Abstract: A combustor for a gas turbine engine includes a combustor liner, a fuel swirler integral and conformal with the combustor liner to provide an outlet for fuel into the combustor, and a dilution chute surrounding the fuel swirler outlet and extending into the combustor to provide a wetting surface for fuel exiting the fuel swirler.

公开(公告)号：US11021963B2

公开(公告)日：2021-06-01

申请号：US16403122

申请日：2019-05-03

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesse R. Boyer

IPC: F01D5/08 ,  F01D25/18 ,  B33Y80/00 ,  B33Y10/00 ,  B33Y70/00

Abstract: A component is provided for a gas turbine engine. This component includes a monolithic body configured with an internal passage. The internal passage extends along a centerline within the monolithic body. The internal passage has a cross-sectional geometry perpendicular to the centerline. The cross-sectional geometry of at least a first portion of the internal passage has a teardrop shape.

公开(公告)号：US10989408B2

公开(公告)日：2021-04-27

申请号：US16130837

申请日：2018-09-13

Applicant: United Technologies Corporation

Inventor： Lawrence Binek ,  Evan Butcher ,  Matthew B. Kennedy ,  Vijay Narayan Jagdale ,  Jesse R. Boyer ,  Dmytro Mykolayovych Voytovych

IPC: F23R3/00 ,  F01D25/24 ,  F02C3/14 ,  F23R3/50

Abstract: A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.