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：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：US11262077B2

公开(公告)日：2022-03-01

申请号：US16577649

申请日：2019-09-20

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/60 ,  F02C3/04 ,  F23R3/06 ,  F23R3/00 ,  F23R3/04

Abstract: A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.

公开(公告)号：US20210088217A1

公开(公告)日：2021-03-25

申请号：US16577649

申请日：2019-09-20

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F23R3/60 ,  F02C3/04

Abstract: A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.

公开(公告)号：US20210088213A1

公开(公告)日：2021-03-25

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 ,  B22F3/105 ,  B33Y10/00 ,  B33Y80/00

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：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.