公开(公告)号：US10907256B2

公开(公告)日：2021-02-02

申请号：US15388392

申请日：2016-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge ,  William J. Brindley

IPC: C23C24/04 ,  F01D25/00 ,  B33Y10/00 ,  C23C4/18 ,  C23C4/08 ,  C23C4/02 ,  C23C4/06 ,  C23C4/134 ,  B22F5/00 ,  C22C47/06 ,  B22F3/00 ,  B22F3/105

Abstract: A method for forming a reinforced metallic structure includes providing a tool having a formation surface corresponding to a desired structure shape of the reinforced metallic structure. The method also includes positioning a plurality of fibers on the formation surface of the tool. The method also includes depositing a layer of material on the plurality of fibers using a cold-spray technique. The method also includes removing the layer of material with the plurality of fibers from the tool to create the reinforced metallic structure.

公开(公告)号：US10822999B2

公开(公告)日：2020-11-03

申请号：US16044268

申请日：2018-07-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Gary D. Roberge

IPC: F01D25/02 ,  F01D5/28 ,  F02K3/06 ,  H05B6/10

Abstract: An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.

公开(公告)号：US20200095941A1

公开(公告)日：2020-03-26

申请号：US16141382

申请日：2018-09-25

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F02C7/36 ,  F02C3/06 ,  H02P9/00

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a first spool including a first compressor coupled to a first turbine through a first shaft; a second spool including a second compressor coupled to a second turbine through a second shaft; a first tower shaft coupled to the first shaft through a first gear assembly; a second tower shaft couple to the second shaft through a second gear assembly; and a first load generating device driven by the first tower shaft, wherein the first load generating device generates a first load on the first spool through the first tower shaft; a second load generating device driven by the second tower shaft, wherein the second load generating device generates a second load on the second spool through the second tower shaft and the first load and the second load combine to apply a total load on the first spool and the second spool; and a controller controlling each of the first load generating device and the second load generating device to vary a proportion of the total load applied to each of the first spool and the second spool to bias a direction of an axial load on each of the first spool and the second spool.

公开(公告)号：US20200088102A1

公开(公告)日：2020-03-19

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：US20200088098A1

公开(公告)日：2020-03-19

申请号：US16131712

申请日：2018-09-14

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/143 ,  F02C7/224 ,  F02C3/22 ,  F02C9/40

Abstract: A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system.

公开(公告)号：US20200063600A1

公开(公告)日：2020-02-27

申请号：US16111739

申请日：2018-08-24

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D25/02 ,  F01D21/12 ,  G10K9/18

Abstract: A gas turbine engine includes an airfoil and a deicing system. The airfoil radially extends from a hub towards a case disposed about a central longitudinal axis of the gas turbine engine. The deicing system includes an acoustic driver assembly arranged to apply acoustic energy to the airfoil to excite a predetermined vibratory mode of the airfoil.

公开(公告)号：US20190316484A1

公开(公告)日：2019-10-17

申请号：US16424641

申请日：2019-05-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D21/00 ,  F04D29/32 ,  F02K3/06 ,  F02C7/32 ,  F02C7/36 ,  F16D63/00 ,  F04D29/053 ,  F01D15/12

Abstract: A gas turbine engine has an engine static structure and at least one component rotatable relative to the engine static structure about an engine axis of rotation. A fan is coupled to at least one component for rotation about the engine axis of rotation. An actuator is mounted to the engine static structure, wherein the actuator is activated to prevent the fan from rotation and is inactivated to allow the fan to rotate. A method for preventing rotation of a fan in a gas turbine engine is also disclosed.

公开(公告)号：US10323325B2

公开(公告)日：2019-06-18

申请号：US15096664

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B23H1/08 ,  B23H9/00 ,  B32B5/18 ,  B32B5/32 ,  C23C4/02 ,  C23C4/08 ,  C25D3/12 ,  C25D3/38 ,  C25D3/42 ,  C25D3/44 ,  C25D3/54 ,  C25D3/56 ,  B23K26/36 ,  B22F5/00 ,  B22F7/00 ,  B32B5/20 ,  C22C1/08 ,  C23C4/10 ,  C23C28/00 ,  B23K26/40 ,  C23C14/02 ,  C23C14/06 ,  C23C14/16 ,  C23C14/22 ,  C23C4/129 ,  C23C4/134 ,  C23C16/06 ,  B32B15/04 ,  B32B15/01 ,  F01D25/00 ,  B23K26/402 ,  B22F3/16 ,  F28F1/12 ,  B23K101/18 ,  B23K103/04 ,  B23K103/08 ,  B23K103/14 ,  B23K103/00 ,  F28F13/00 ,  B23K103/18

Abstract: A method of making a light weight housing for an internal component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; forming a second metallic foam core into a desired configuration; inserting an internal component into the first metallic foam core; placing the second metallic foam adjacent to the first metallic core in order to secure the internal component between the first metallic foam core and the second metallic foam core; and applying an external metallic shell to an exterior surface of the first metallic foam core and the second metallic foam core.

公开(公告)号：US20190153959A1

公开(公告)日：2019-05-23

申请号：US16178959

申请日：2018-11-02

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/36 ,  F02C3/073

Abstract: A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan. A method of adjusting rotational speeds within a gas turbine engine is also disclosed.

公开(公告)号：US10252292B2

公开(公告)日：2019-04-09

申请号：US15096631

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: 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 ,  B32B5/18 ,  B32B5/20 ,  B32B15/01 ,  C22C1/08 ,  F02C7/12 ,  B29C70/68 ,  B23K26/362 ,  B23K26/40 ,  C22C14/00 ,  B22F3/26 ,  B22F7/08 ,  B29C45/14 ,  B22F3/105 ,  B33Y10/00 ,  B23K103/02 ,  B23K103/08 ,  B29K705/00 ,  B29K105/12

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