公开(公告)号：US10399117B2

公开(公告)日：2019-09-03

申请号：US15096631

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B05D7/22 ,  C23F17/00 ,  B29C45/14 ,  C25D7/00 ,  C23C4/129 ,  C23C4/134 ,  C23C24/02 ,  C23C14/16 ,  C22F1/18 ,  C22F1/16 ,  C22F1/10 ,  C22F1/08 ,  C22F1/06 ,  C22F1/04 ,  B29C70/68 ,  B23K26/362 ,  B23K26/40 ,  C22C14/00 ,  B22F3/26 ,  B22F7/08 ,  B23H9/00 ,  B32B5/18 ,  B32B5/20 ,  B32B15/01 ,  C22C1/08 ,  F02C7/12 ,  B05D7/14 ,  B22F3/105 ,  B33Y10/00 ,  B23K103/08 ,  B23K103/02 ,  B29K105/12 ,  B29K705/00

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.

公开(公告)号：US10378478B2

公开(公告)日：2019-08-13

申请号：US15864297

申请日：2018-01-08

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C1/00 ,  F02K1/38 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105

Abstract: A method of communicating flow through a gas turbine engine having multiple flow paths according to an exemplary embodiment of the present disclosure includes moving core flow along a core flow path from a compressor section to an exhaust section, selectively communicating a first amount of bypass flow from a bypass flow path defined by a bypass duct to the exhaust section or a second amount of bypass flow from the bypass flow path to the exhaust section, the first amount different than the second amount.

公开(公告)号：US10337349B2

公开(公告)日：2019-07-02

申请号：US15139403

申请日：2016-04-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D15/12 ,  F01D21/00 ,  F04D29/053 ,  F04D29/32 ,  F02K3/06 ,  F02C7/32 ,  F02C7/36 ,  F16D63/00 ,  F01D21/04 ,  F16D11/16 ,  F16D11/00

Abstract: A gas turbine engine has an engine static structure. 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：US20190153877A1

公开(公告)日：2019-05-23

申请号：US16251308

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D5/28 ,  F01D5/18 ,  F01D5/14 ,  F04D29/32 ,  F01D25/12 ,  F01D25/00 ,  F01D9/04

Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100° F. higher than that of the second material. A gas turbine engine is also disclosed.

公开(公告)号：US10119412B2

公开(公告)日：2018-11-06

申请号：US14768769

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D11/20 ,  F16J15/43

Abstract: An air seal includes a sealing gland configured to retain a ferro-fluid and one or more seals. A portion of the one or more seals is configured to extend into the sealing gland. A gas turbine engine, includes the air seal. A method of sealing low pressure air from high pressure air, includes the steps of providing a sealing gland configured to retain a ferro-fluid, distributing the ferro-fluid into the sealing gland, providing one or more seals, wherein a portion of the one or more seals is configured to extend into the sealing gland, and removing the ferro-fluid from the sealing gland.

公开(公告)号：US20180238270A1

公开(公告)日：2018-08-23

申请号：US15953791

申请日：2018-04-16

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02K3/115 ,  F02C7/06 ,  F01D9/06 ,  F02K3/06 ,  F02C7/14 ,  F02C7/18 ,  F02K3/105

CPC classification number: F02K3/115 ,  F01D9/065 ,  F02C7/06 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/105 ,  F05D2210/12 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2250/182 ,  F05D2250/60 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/4031 ,  F05D2260/98 ,  Y02T50/676

Abstract: An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.

公开(公告)号：US20180179640A1

公开(公告)日：2018-06-28

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

CPC classification number: C23C24/04 ,  B22F3/008 ,  B22F3/1055 ,  B22F5/003 ,  B33Y10/00 ,  C22C47/068 ,  C23C4/02 ,  C23C4/06 ,  C23C4/08 ,  C23C4/134 ,  C23C4/185 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/6032 ,  Y02P10/295

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：US20180179637A1

公开(公告)日：2018-06-28

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 ,  C25D7/00 ,  B33Y10/00

CPC classification number: C23C24/04 ,  B22F3/1055 ,  B33Y10/00 ,  B33Y80/00 ,  C23C24/087 ,  C25D7/00 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/10

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：US20180156057A1

公开(公告)日：2018-06-07

申请号：US15882051

申请日：2018-01-29

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D15/10 ,  F02C3/107 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F01D25/02

CPC classification number: F01D15/10 ,  F01D25/02 ,  F02C3/107 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/76 ,  F05D2230/72 ,  F05D2260/40311 ,  F05D2260/60 ,  Y02T50/671

Abstract: A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.

公开(公告)号：US20170314411A1

公开(公告)日：2017-11-02

申请号：US15139403

申请日：2016-04-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F01D21/00 ,  F04D29/32 ,  F01D15/12 ,  F04D29/053

CPC classification number: F01D21/006 ,  F01D15/12 ,  F01D21/04 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2260/902 ,  F05D2260/903 ,  F05D2270/62 ,  F16D11/16 ,  F16D63/002 ,  F16D63/006 ,  F16D2011/006

Abstract: A gas turbine engine has an engine static structure. 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.