公开(公告)号：US20200088408A1

公开(公告)日：2020-03-19

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 ,  F02C3/14 ,  F01D25/24 ,  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.

公开(公告)号：US10272382B2

公开(公告)日：2019-04-30

申请号：US15169124

申请日：2016-05-31

Applicant: United Technologies Corporation

Inventor： Ying She ,  Aaron T. Nardi ,  Lawrence Binek ,  Andrzej Ernest Kuczek ,  Zissis A. Dardas

IPC: B01D53/22 ,  B01D53/30 ,  B01D53/053 ,  B01D53/047 ,  B33Y40/00 ,  B29C64/357 ,  C23C24/04

Abstract: A carrier gas recovery system for use in cold spray manufacturing recovers carrier gas utilized during the cold spray process and recycles the carrier gas for immediate use or stores the carrier gas for future use. The carrier gas recovery system includes an enclosure subsystem, a filtration subsystem, a reclamation subsystem, and a compensation subsystem. An article is placed in the enclosure and particulate matter is carried to the article on a carrier gas stream. Carrier gas in the enclosure is filtered through the filtration subsystem to remove particulate from the carrier gas, and the filtered carrier gas is fed to the reclamation subsystem. The carrier gas either flows to a gas separator, to increase the concentration of carrier gas, or to the compensation subsystem if the carrier gas concentration is sufficiently high. The carrier gas can be stored in the compensation subsystem or used in further cold spray manufacturing.

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：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.

公开(公告)号：US20200182155A1

公开(公告)日：2020-06-11

申请号：US16213047

申请日：2018-12-07

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F02C7/26 ,  F02C7/22 ,  B33Y80/00 ,  F23R3/28

Abstract: A propulsion system according to an example of the present disclosure, includes a core engine and an outer casing surrounding the core engine. The outer casing includes an integral injector assembly. The injector assembly includes a wall that defines a cavity, the wall being integral with the outer casing. A method of operating a propulsion system and method of making a component of a propulsion system are also disclosed.

公开(公告)号：US20170173591A1

公开(公告)日：2017-06-22

申请号：US14972199

申请日：2015-12-17

Applicant: United Technologies Corporation

Inventor： Ying She ,  Aaron T. Nardi ,  Lawrence Binek

IPC: B03B4/00 ,  B22F1/00 ,  B03B1/02

CPC classification number: B03B4/00 ,  B03B1/02 ,  B07B4/00 ,  B07B7/01 ,  B07B9/02 ,  B22F1/0081 ,  B22F1/0085 ,  B22F3/008 ,  B22F3/1055 ,  Y02P10/295

Abstract: A fluidized powder heat treatment classification assembly includes a gas source. A fluidized bed is connected to the gas source via a metered connection. The fluidized bed includes a first output connected to a powder classifier via at least a first valve. The powder classifier includes a catch container operable to decelerate a gas flow from the output and operable to catch particles entrained in the gas flow.

公开(公告)号：US11242769B2

公开(公告)日：2022-02-08

申请号：US16221991

申请日：2018-12-17

Applicant: United Technologies Corporation

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

IPC: F01D25/24 ,  B33Y10/00 ,  B33Y80/00

Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

公开(公告)号：US11179895B2

公开(公告)日：2021-11-23

申请号：US16153259

申请日：2018-10-05

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/04 ,  B33Y30/00 ,  B33Y80/00 ,  B33Y10/00

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.