公开(公告)号：US11434823B2

公开(公告)日：2022-09-06

申请号：US16734925

申请日：2020-01-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F02C7/22 ,  F02C3/22 ,  F04B15/08 ,  F02C7/224 ,  F02C9/30 ,  F04B9/113

Abstract: A fuel power transfer system for an engine may include a cryogenic fuel supply, a fuel pump in fluid communication with the cryogenic fuel supply, a multi-position valve in fluid communication with the fuel pump and a combustion chamber of the engine, a fuel turbine operatively coupled to the fuel pump and having a primary discharge port in fluid communication with the combustion chamber, a primary heat exchanger in fluid communication between the multi-position valve and the fuel turbine, and a gearbox operatively coupled to the fuel turbine and the fuel pump and configured to transfer power from the fuel turbine to the engine.

公开(公告)号：US11286781B2

公开(公告)日：2022-03-29

申请号：US16796205

申请日：2020-02-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/06

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk and a plurality of rotor blades. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. The first rotor blade includes an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion of the first rotor disk extends circumferentially across and covers the attachment.

公开(公告)号：US11208892B2

公开(公告)日：2021-12-28

申请号：US16746321

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/02 ,  F01D5/22 ,  F01D5/30

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. Each of the disk mounts connects the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount that further supports the first rotor blade.

公开(公告)号：US20210222572A1

公开(公告)日：2021-07-22

申请号：US16796268

申请日：2020-02-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/30 ,  F01D5/02

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.

公开(公告)号：US20210222559A1

公开(公告)日：2021-07-22

申请号：US16796241

申请日：2020-02-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/06 ,  F01D5/30

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The disk mounts connect the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount. The first disk mount is integral with the first rotor disk. The first disk mount projects axially through the second rotor disk.

公开(公告)号：US20210222558A1

公开(公告)日：2021-07-22

申请号：US16796205

申请日：2020-02-20

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/06

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk and a plurality of rotor blades. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. The first rotor blade includes an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion of the first rotor disk extends circumferentially across and covers the attachment.

公开(公告)号：US11047307B2

公开(公告)日：2021-06-29

申请号：US16131706

申请日：2018-09-14

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/224 ,  F02C3/04 ,  F02C7/143

Abstract: A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from a first compressed air flow and an exhaust gas flow to a fuel to produce a gaseous fuel. The fuel turbine system includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, and a fuel pump fluidly coupled to the heat exchange system and configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce the gaseous fuel at a lower pressure for delivery to the combustor.

公开(公告)号：US11040372B2

公开(公告)日：2021-06-22

申请号：US16377730

申请日：2019-04-08

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: B32B5/18 ,  B32B5/20 ,  B32B15/01 ,  B05D7/22 ,  C23F17/00 ,  B23H9/00 ,  C25D7/00 ,  C23C4/129 ,  C23C4/134 ,  C23C24/02 ,  C23C14/16 ,  C22F1/18 ,  C22F1/16 ,  C22F1/10 ,  C22F1/08 ,  C22F1/06 ,  C22F1/04 ,  B05D7/14 ,  C22C1/08 ,  F02C7/12 ,  B23K26/40 ,  C22C14/00 ,  B22F3/26 ,  B22F7/08 ,  B29C45/14 ,  B23K26/361 ,  B29C70/68 ,  B23K26/362 ,  B33Y10/00 ,  B23K103/02 ,  B23K103/08 ,  B29K705/00 ,  B29K105/12 ,  B22F10/20

Abstract: A light weight component, the light weight component including: a metallic foam core formed into a desired configuration; an external metallic shell applied to an exterior surface of the metallic foam core after it has been formed into the desired configuration; an inlet opening and an outlet opening formed in the external metallic shell in order to provide a fluid path through the metallic foam core; and a thermoplastic material injected into the metallic foam core via the inlet opening.

公开(公告)号：US11002615B2

公开(公告)日：2021-05-11

申请号：US16355959

申请日：2019-03-18

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: G01K11/12 ,  F16L23/16

Abstract: A gas turbine engine includes a joint and a flexible strip wrapped circumferentially around the joint. The flexible strip includes a lock operable to fasten the flexible strip about the joint. A thermochromatic layer is attached to a surface of the flexible strip and is operable to change color responsive to a change in temperature.

公开(公告)号：US10961865B2

公开(公告)日：2021-03-30

申请号：US16181564

申请日：2018-11-06

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D17/16 ,  F04D29/40

Abstract: A casing assembly for a gas turbine engine includes a case having an outer case wall extending around a central axis, an inner case wall radially offset from the outer case wall, and one or more hydraulic fluid passages embedded in the case between the outer case wall and the inner case wall. A variable pitch stator vane system includes a plurality of stator vanes are located radially inboard of the inner case wall. Each stator vane is rotatable about a central vane axis. An actuation unit is operably connected to the plurality of stator vanes and driven by hydraulic fluid through the one or more hydraulic fluid passages to urge rotation of the plurality of stator vanes about their respective central vane axes.