公开(公告)号：US11002187B2

公开(公告)日：2021-05-11

申请号：US16561249

申请日：2019-09-05

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C6/08 ,  F02C7/32 ,  F02C7/36 ,  F02C7/18 ,  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：US10883380B2

公开(公告)日：2021-01-05

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：US10823081B2

公开(公告)日：2020-11-03

申请号：US15851010

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/36 ,  F02C7/32 ,  F16H1/22

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：US20200088099A1

公开(公告)日：2020-03-19

申请号：US16131716

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 turbo-generator. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow or exhaust gas flow) to a fuel to produce a gaseous fuel. The turbo-generator includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, a fuel pump configured to be driven by the fuel turbine and fluidly coupled to the heat exchange system, and a motor/generator configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor. The motor/generator includes a cooling jacket, which is fluidly coupled to the fuel pump.

公开(公告)号：US20200087793A1

公开(公告)日：2020-03-19

申请号：US16688824

申请日：2019-11-19

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  William J. Brindley

IPC: C23C24/04 ,  B33Y80/00 ,  B22F7/08 ,  B22F3/24 ,  B22F5/00 ,  B22F5/04 ,  F01D25/00

Abstract: A method for forming a metallic structure having a secondary component includes positioning the secondary component on a main formation surface of a main tool, the main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing a layer of material on the secondary component and the main formation surface using a cold-spray technique such that the layer of material bonds to the secondary component. The method also includes removing the layer of material and the secondary component to form the metallic structure.

公开(公告)号：US20200047895A1

公开(公告)日：2020-02-13

申请号：US16057362

申请日：2018-08-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gary D. Roberge

IPC: B64D27/24 ,  B64D35/08 ,  B64D35/04 ,  H02K7/02 ,  H02J15/00

Abstract: An aircraft power system according to an exemplary embodiment of this disclosure includes, among other possible things, a battery, a motor/generator coupled to the battery, an inertial drum rotatable about an axis of rotation and coupled to the motor/generator, wherein the motor/generator drives rotation of the inertial drum in a first operating mode and is driven by the inertial drum in a second operating mode; and a housing defining a chamber for the inertial drum, the chamber filled with low-viscosity medium to reduce friction on the inertial drum.

公开(公告)号：US10550764B2

公开(公告)日：2020-02-04

申请号：US15104100

申请日：2014-09-09

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C3/04 ,  F02C7/32 ,  F02K3/077 ,  F02C3/073 ,  F02K1/48 ,  F02K3/115 ,  F02C3/10 ,  F02K3/068 ,  F02C3/14 ,  F02K3/06 ,  F02K3/072

Abstract: A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator, and a second portion, configured to receive air from an exit of the gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.

公开(公告)号：US20200032670A1

公开(公告)日：2020-01-30

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：US10526913B2

公开(公告)日：2020-01-07

申请号：US15089835

申请日：2016-04-04

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/36 ,  F02C3/107 ,  F01D21/00 ,  F02C7/32 ,  F02K3/06 ,  F02C7/06 ,  F02C9/00

Abstract: A gas turbine engine includes a compressor having a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine has a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. A low speed accessory gearbox is interfaced with the first shaft via a mechanical interface. The low speed accessory gearbox includes a mechanical brake.

公开(公告)号：US20190353103A1

公开(公告)日：2019-11-21

申请号：US15980814

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F02C7/18 ,  F02C7/32 ,  F02C3/04

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a compressor section including an aft most exit, an air tap configured to draw air from a point upstream of the aft most exit, an auxiliary compressor configured to receive air from the air tap and discharge air to a turbine section, an electric motor configured to drive the auxiliary compressor, a first heat exchanger within an inlet passage between the air tap and an inlet to the auxiliary compressor, and a second heat exchanger disposed within an outlet passage between an outlet of the auxiliary compressor and the turbine section.