公开(公告)号：US10724131B2

公开(公告)日：2020-07-28

申请号：US15096685

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B22F7/00 ,  B22F3/11 ,  C22C1/08 ,  B32B5/18 ,  C23C4/129 ,  F02C7/12 ,  B32B15/01 ,  F02K1/78 ,  B32B5/20 ,  F02K1/04 ,  B23K26/40 ,  B23K26/361 ,  C23C4/134 ,  C23C14/22 ,  C23C16/06 ,  C23C24/04 ,  B23K103/02 ,  B23K103/08

Abstract: A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; and applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration.

公开(公告)号：US20200182088A1

公开(公告)日：2020-06-11

申请号：US16213395

申请日：2018-12-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D25/14 ,  F01D25/00

Abstract: A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.

公开(公告)号：US20200173307A1

公开(公告)日：2020-06-04

申请号：US16207799

申请日：2018-12-03

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D25/14 ,  F01D25/12 ,  F01D25/18 ,  F02K3/06 ,  B22F5/00 ,  B22F3/105

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

公开(公告)号：US10648084B2

公开(公告)日：2020-05-12

申请号：US15388172

申请日：2016-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge ,  William J. Brindley

IPC: C23C24/04 ,  F01D25/00 ,  C23C24/08 ,  B33Y10/00 ,  C25D7/00 ,  B22F3/105 ,  B33Y80/00

Abstract: A method for forming a sheet structure includes providing a tool having a formation surface corresponding to a shape of the sheet structure. The method also includes depositing at least one layer of material on the formation surface using a cold-spray deposition technique. The method also includes removing the at least one layer of material from the formation surface to create the sheet structure.

公开(公告)号：US10563577B2

公开(公告)日：2020-02-18

申请号：US15242674

申请日：2016-08-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor. The high pressure compressor has a downstream most location. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor and a heat exchanger, which passes the air back to a location to be cooled. The boost compressor is driven by a shaft which drives the lower pressure compressor.

公开(公告)号：US10563537B2

公开(公告)日：2020-02-18

申请号：US15017127

申请日：2016-02-05

Applicant: United Technologies Corporation

Inventor： Wendell V. Twelves, Jr. ,  Evan Butcher ,  Lexia Kironn ,  Joe Ott ,  Gary D. Roberge

IPC: F01D25/00 ,  F01D25/24 ,  B32B15/01 ,  F01D21/04 ,  F01D21/10 ,  F41H5/04 ,  B32B15/00 ,  B32B15/18 ,  B32B27/34 ,  B32B15/14 ,  B32B15/04 ,  B32B9/04 ,  B32B15/20 ,  B32B3/08 ,  B32B3/02 ,  B32B15/088 ,  B32B9/00

Abstract: An apparatus includes first, second, and third layers. The first layer includes a plurality of flanges. The second layer includes a deformable membrane. The second layer is connected to the first layer along a first major surface of the deformable membrane. The third layer is connected to the second layer along a second major surface of the deformable membrane opposite the first major surface. The third layer includes a first series of internal structures.

公开(公告)号：US10458255B2

公开(公告)日：2019-10-29

申请号：US14761029

申请日：2014-02-04

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  George J. Kramer

IPC: F01D5/28 ,  B64D15/00 ,  F01D25/00 ,  F01D25/02 ,  F02C3/04 ,  F01D5/02 ,  F01D17/14 ,  B64D45/00 ,  F01D9/04 ,  F01D25/24

Abstract: A fan section to be incorporated into a gas turbine engine has a rotor and a plurality of fan blades. The fan blades deliver air into a bypass duct defined inwardly of the nacelle and into a core engine. There are static vanes inward of the nacelle. A surface of the fan section is provided with a removable film material. A gas turbine engine and a method of refurbishing a surface are also disclosed.

公开(公告)号：US10400709B2

公开(公告)日：2019-09-03

申请号：US14458619

申请日：2014-08-13

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C3/13 ,  F02C7/36 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F02K3/10 ,  F02K3/075 ,  F02K3/077

Abstract: A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

公开(公告)号：US20190195139A1

公开(公告)日：2019-06-27

申请号：US15851089

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F02C7/36

CPC classification number: F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2220/50 ,  F05D2240/14 ,  F05D2260/4031

Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a high rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, a first gearbox operably connected to the high rotor towershaft, a low rotor towershaft operably connected to and driven by a second spool of the gas turbine engine, and a second gearbox operably connected to the low rotor towershaft. The high rotor towershaft is located at a first case of the gas turbine engine and the low rotor towershaft is located at a second case of the gas turbine engine axially forward of the first case.

公开(公告)号：US20190003392A1

公开(公告)日：2019-01-03

申请号：US15417257

申请日：2017-01-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F02C7/143 ,  F02C7/18

Abstract: A gas turbine engine comprises a fan delivering air into a bypass duct as bypass air and into a core engine. The core engine includes a high pressure compressor, a combustor, and a turbine section including a fan drive turbine driving a fan rotor through a gear reduction. The high pressure compressor having a downstream most location and air in a chamber radially outward of the combustor being air downstream of the downstream most location in the high pressure compressor. A tap taps compressed air and moves compressed air through a heat exchanger, then returns the compressed air back into a core engine housing and passes the returned air through a conduit radially outwardly of the combustor. The air is passed ng from the conduit radially inwardly to cool the turbine section.