公开(公告)号：US20210207497A1

公开(公告)日：2021-07-08

申请号：US16736392

申请日：2020-01-07

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesus A. Garcia ,  Faramarz M. Zarandi ,  Evan J. Butcher ,  Jesse R. Boyer

IPC: F01D25/26

Abstract: A double walled stator housing includes a first stator housing wall, a second stator housing wall located radially outward from the first stator housing wall, and an air gap located between the first and the second stator housing walls. The housing also includes at least one support structure attached to the first stator housing wall and the second stator housing wall, spanning the air gap and configured to minimize heat transfer between the first wall and the second wall.

公开(公告)号：US11320145B2

公开(公告)日：2022-05-03

申请号：US16577396

申请日：2019-09-20

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Sean R. Jackson ,  Evan J. Butcher

IPC: F23R3/00 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/00

Abstract: A method for forming a combustor of a gas turbine engine includes additively manufacturing a combustor wall of the combustor. The combustor wall includes a component, projecting from a surface of the combustor wall, and a support structure in communication with the component and the surface of the combustor wall. The support structure is a lattice structure.

公开(公告)号：US11180997B2

公开(公告)日：2021-11-23

申请号：US16577385

申请日：2019-09-20

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesus A. Garcia ,  Evan J. Butcher ,  Faramarz Zarandi ,  Matthew B. Kennedy ,  Jesse R. Boy

IPC: F01D5/04 ,  B22F3/15 ,  F02C3/05 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/34 ,  B22F5/04

Abstract: A method of making a rotor assembly of a turbojet includes building the rotor assembly via layer-by-layer additive manufacturing. A turbine portion is formed and a compressor portion is integrally formed with the turbine portion. A shaft portion is integrally formed with the compressor portion. A material of the rotor assembly includes a nickel based alloy.

公开(公告)号：US11136901B2

公开(公告)日：2021-10-05

申请号：US16415327

申请日：2019-05-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lawrence A. Binek ,  Jesse R. Boyer ,  Evan J. Butcher ,  Dmytro Mykolayovych Voytovych

IPC: F01D25/00

Abstract: A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.

公开(公告)号：US20210156563A1

公开(公告)日：2021-05-27

申请号：US16692077

申请日：2019-11-22

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Evan J. Butcher ,  Sean R. Jackson

IPC: F23R3/00 ,  F02C7/12 ,  F02C7/32

Abstract: A gas turbine engine includes an engine casing and a combustor liner enclosed within the engine casing. The engine includes a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner. The engine includes an inspection port penetrating the engine casing, the flow path, and the combustor liner and wherein the inspection port is positioned to allow an operator to view sacrificed zones of a sacrificial support structure.

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：US20210207495A1

公开(公告)日：2021-07-08

申请号：US16736385

申请日：2020-01-07

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Leslie F. Guzman ,  Sean R. Jackson ,  Evan J. Butcher

IPC: F01D25/18 ,  F16C27/04 ,  F01D25/16

Abstract: A gas turbine engine with a lubrication system includes a ball bearing assembly and a rotor circumscribing a rotational axis and journaled within the ball bearing assembly. The gas turbine engine also includes a lubrication system located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly, which includes a lubrication channel having an inlet and an outlet and a dispersion cone adjacent to the outlet of the lubrication channel.

公开(公告)号：US20210087955A1

公开(公告)日：2021-03-25

申请号：US16577526

申请日：2019-09-20

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Sean R. Jackson ,  Evan J. Butcher

IPC: F01M1/16 ,  F01M11/03 ,  F01M11/02 ,  F01M9/04 ,  F01D25/18 ,  B33Y80/00

Abstract: A lubrication system for an attritable engine includes a bearing chamber, a fluid filtering inlet configured to receive a fluid, and a fluid filtering outlet located downstream of the fluid filtering inlet and configured to deliver the fluid to the bearing chamber. The lubrication system also includes a lattice, integral and conformal with the attritable engine, configured to filter the fluid, and located between the fluid filtering inlet and the fluid filtering outlet. The lubrication system also includes a metering port, configured to meter the fluid and located downstream of the lattice and upstream of the fluid filtering outlet.

公开(公告)号：US20210087935A1

公开(公告)日：2021-03-25

申请号：US16577385

申请日：2019-09-20

Applicant: United Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesus A. Garcia ,  Evan J. Butcher ,  Faramarz Zarandi ,  Matthew B. Kennedy ,  Jesse R. Boy

IPC: F01D5/04 ,  F02C3/05 ,  B22F3/15 ,  B22F5/04

Abstract: A method of making a rotor assembly of a turbojet includes building the rotor assembly via layer-by-layer additive manufacturing. A turbine portion is formed and a compressor portion is integrally formed with the turbine portion. A shaft portion is integrally formed with the compressor portion. A material of the rotor assembly includes a nickel based alloy.

公开(公告)号：US20200003639A1

公开(公告)日：2020-01-02

申请号：US16534703

申请日：2019-08-07

Applicant: United Technologies Corporation

Inventor： Lyutsia Dautova ,  Wendell V. Twelves, JR. ,  Joe Ott ,  Evan J. Butcher ,  Gary A. Schirtzinger ,  Rainer J. Hebert

IPC: G01L1/25 ,  G01N23/20 ,  B22F3/105 ,  B33Y10/00 ,  B33Y40/00 ,  B23K26/342 ,  B23K26/70

Abstract: A method of monitoring the residual stress in surface and near surface regions of a component includes identifying predetermined locations on the surface of a component that are expected to experience high stress during normal operating conditions of the component. Marker particles are introduced into the component during additive manufacture of the component at the predetermined locations. Then, the residual stress of the component is measured at a location corresponding with the marker material using x-ray techniques.