公开(公告)号：US20200173365A1

公开(公告)日：2020-06-04

申请号：US16207806

申请日：2018-12-03

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/12 ,  F02C9/18

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured outer engine duct structure, at least a portion of an internal surface of the additively manufactured outer engine duct structure forming an additively manufactured heat exchanger

公开(公告)号：US10598378B2

公开(公告)日：2020-03-24

申请号：US15025012

申请日：2014-10-07

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  Grant O. Cook, III

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.

公开(公告)号：US20190390598A1

公开(公告)日：2019-12-26

申请号：US16561249

申请日：2019-09-05

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C6/08 ,  F02C7/143

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：US20190316486A1

公开(公告)日：2019-10-17

申请号：US15951527

申请日：2018-04-12

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D25/12 ,  F01D15/10 ,  F02C7/18 ,  F02C7/32 ,  H02K7/18 ,  H02K7/116 ,  H02K9/16

Abstract: A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.

公开(公告)号：US20190316477A1

公开(公告)日：2019-10-17

申请号：US15951289

申请日：2018-04-12

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D9/02 ,  F01D11/00

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor having a hub carrying a plurality of blades, the hub rotatable about a longitudinal axis, and a seal extending outwardly from the hub to establish a sealing relationship with a plurality of vanes distributed about the longitudinal axis. A flow guide assembly is secured to an engine static structure such that a flow path is defined between the hub and the flow guide assembly. The flow path has an inlet portion defined along the seal and an outlet portion, and the flow guide assembly includes an acoustic liner that extends along the flow path.

公开(公告)号：US10335850B2

公开(公告)日：2019-07-02

申请号：US15096671

申请日：2016-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B21J5/02 ,  B44C1/22 ,  B21J5/00 ,  B23H9/00 ,  B23H1/08 ,  B23K26/40 ,  B23K26/362 ,  C25D3/12 ,  C25D5/40 ,  C25D5/48 ,  C25D7/04 ,  C23C14/16 ,  C23C14/02 ,  C23C14/22 ,  C23C4/08 ,  C23C4/129 ,  C23C4/134 ,  B23P15/02 ,  C23C24/04 ,  C23C16/44 ,  B32B5/18 ,  B32B5/20 ,  B32B15/01 ,  F01D25/00 ,  C23F1/04 ,  B22F7/00 ,  C22C1/08 ,  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; inserting a pre-machined component into an opening in the metallic foam core; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration and after the pre-machined component has been inserted into the metallic foam core; introducing an acid into an internal cavity defined by the external metallic shell; dissolving the metallic foam core; and removing the dissolved metallic foam core from the internal cavity, wherein the component and the external metallic shell are resistant to the acid.

公开(公告)号：US20190195138A1

公开(公告)日：2019-06-27

申请号：US15851010

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F16H1/22

CPC classification number: F02C7/32 ,  F02C7/36 ,  F05D2250/311 ,  F05D2250/36 ,  F05D2260/4031 ,  F16H1/222

Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a low rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, and a high rotor towershaft operably connected to and driven by a second spool of the gas turbine engine. The high rotor towershaft and the low rotor towershaft are concentric and extend to a common gearbox housing.

公开(公告)号：US10294870B2

公开(公告)日：2019-05-21

申请号：US14765685

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: F02C7/32 ,  F02C7/36 ,  F01D25/28 ,  B64D29/08

Abstract: An accessory drive system for an aircraft gas turbine engine is disclosed. The system may comprise an engine case including a core engine cowl and at least a first accessory drive gearbox disposed within the core engine cowl. The at least first accessory drive gearbox may be operatively connected to one or more accessories remotely located therefrom.

公开(公告)号：US10221771B2

公开(公告)日：2019-03-05

申请号：US14950326

申请日：2015-11-24

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F01D25/16

Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism.

公开(公告)号：US20190048889A1

公开(公告)日：2019-02-14

申请号：US15673635

申请日：2017-08-10

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F04D29/38 ,  F04D29/32 ,  F04D29/52 ,  F04D29/66

Abstract: A fan blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, and extends radially between a root portion and a tip portion. A tip pocket is defined by collapsible external walls of the tip portion, and has a pocket opening at a radially outer face of the tip portion.