公开(公告)号：US20210025335A1

公开(公告)日：2021-01-28

申请号：US16521633

申请日：2019-07-25

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  Dilip Prasad

IPC: F02C9/16 ,  F02K3/06

Abstract: A method of operating a turbofan engine includes coupling an electric motor to drive a fan rotatable within a nacelle, detecting an in-flight operating condition indicative of an increase in drag, and driving rotation of the fan with the electric motor to redirect a flow of air through the nacelle to reduce drag. A turbofan engine is also disclosed.

公开(公告)号：US20210016888A1

公开(公告)日：2021-01-21

申请号：US16511284

申请日：2019-07-15

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  Victor Pascu

IPC: B64D27/02 ,  B64D31/06 ,  F02C3/06 ,  F02C6/14 ,  F02C9/18 ,  F02C9/28 ,  B64D27/10 ,  B64D27/24

Abstract: A hybrid propulsion system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid propulsion system also includes a motor configured to augment rotational power of the high speed spool, a flow modulation device configured to control a combustor bypass air flow around the combustor to the turbine section, and a controller. The controller is operable to determine a mode of operation, apply supplemental power to the high speed spool using the motor, modulate the combustor bypass air flow using the flow modulation device, and adjust a fuel-air ratio at the combustor based on modulation of the combustor bypass air flow and the supplemental power applied to the high speed spool.

公开(公告)号：US10738694B1

公开(公告)日：2020-08-11

申请号：US16110473

申请日：2018-08-23

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Dmitriy B. Sidelkovskiy ,  Neil Terwilliger ,  William G. Sheridan

IPC: F02C3/067 ,  F02K3/06 ,  F02C7/32 ,  F02K3/072 ,  B64D27/02

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.

公开(公告)号：US20200056497A1

公开(公告)日：2020-02-20

申请号：US16431245

申请日：2019-06-04

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  Daniel Bernard Kupratis ,  Michael M. Romero

IPC: F01D15/10 ,  F02C9/26 ,  F02C7/277

Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.

公开(公告)号：US20200055610A1

公开(公告)日：2020-02-20

申请号：US16104288

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  David A. Golfin

IPC: B64D27/02 ,  B60L11/18 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F02C6/14 ,  H02J7/14

Abstract: An aspect includes a battery charging system for a hybrid electric aircraft. The battery charging system includes a generator, a battery system, and a controller. The controller is operable to charge the battery system up to a first charge level based on receiving a first charging current at a power input. An operational status of a gas turbine engine of the hybrid electric aircraft is monitored. The battery system is charged at a second charging current received from the generator driven by the gas turbine engine responsive to determining that the gas turbine engine is in a taxi state, where the second charging current is less than the first charging current. Charging of the battery system is halted based on detecting a transition of the gas turbine engine from the taxi state to an off-idle throttle state.

公开(公告)号：US20180209343A1

公开(公告)日：2018-07-26

申请号：US15410971

申请日：2017-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Brian Merry ,  Neil Terwilliger

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/04

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02K3/06 ,  F05D2260/213 ,  Y02T50/676

Abstract: An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.

公开(公告)号：US11530635B2

公开(公告)日：2022-12-20

申请号：US16586348

申请日：2019-09-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel B. Kupratis ,  Neil Terwilliger ,  Gary Roberge

IPC: F01N3/04

Abstract: A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.

公开(公告)号：US11149649B2

公开(公告)日：2021-10-19

申请号：US16104281

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  John P. Virtue

IPC: F02C7/268 ,  B64D27/24 ,  B64D33/00 ,  F02C9/26 ,  F02C9/54 ,  F02K5/00 ,  B64D27/02 ,  F02C6/14 ,  B64D27/10 ,  B64D31/06

Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine, an electric motor operable to perform an electric taxiing of the hybrid electric aircraft, and a controller. The controller is operable to prevent fuel flow to the gas turbine engine during at least a portion of the electric taxiing and monitor for a powered warm-up request during the electric taxiing. A powered warm-up state of the gas turbine engine is initiated based on detecting the powered warm-up request. The powered warm-up state adds heat to one or more components of the gas turbine engine prior to transitioning to a takeoff power state. The gas turbine engine transitions from the powered warm-up state to the takeoff power state after reaching a target temperature of the one or more components in the powered warm-up state.

公开(公告)号：US11085371B2

公开(公告)日：2021-08-10

申请号：US16550576

申请日：2019-08-26

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Dmitriy B. Sidelkovskiy ,  Neil Terwilliger ,  William G. Sheridan

IPC: F02C3/067 ,  F02C7/32 ,  F02K3/06 ,  F02K3/072 ,  B64D27/02

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.

公开(公告)号：US20210207530A1

公开(公告)日：2021-07-08

申请号：US16733504

申请日：2020-01-03

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

IPC: F02C6/20

Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.