公开(公告)号：US10823070B2

公开(公告)日：2020-11-03

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 ,  F02C3/04 ,  F02K3/06

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：US20200063657A1

公开(公告)日：2020-02-27

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 ,  F02K3/06 ,  F02C7/32 ,  F02K3/072

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：US11255263B2

公开(公告)日：2022-02-22

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: F02C7/36 ,  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.

公开(公告)号：US11124291B2

公开(公告)日：2021-09-21

申请号：US16219423

申请日：2018-12-13

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  Stuart S. Ochs

IPC: B64C21/08 ,  B64C1/16 ,  B64C21/06 ,  B64D27/20 ,  B64D33/02

Abstract: An aircraft is provided and includes fuselage having a nose, a main section aft of the nose and a tail aft of the main section, an engine nacelle partially embedded in the tail and including a boundary layer ingestion (BLI) propulsor with an inlet directly adjacent to the fuselage and a nozzle element disposed upstream from the inlet and configured to accelerate boundary flows flowing toward the interior side of the engine nacelle.

公开(公告)号：US10773812B2

公开(公告)日：2020-09-15

申请号：US16104288

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  David A. Golfin

IPC: B64D27/02 ,  B60L53/24 ,  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：US10760444B2

公开(公告)日：2020-09-01

申请号：US15979112

申请日：2018-05-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Neil Terwilliger ,  Christopher J Hanlon ,  Sorin Bengea ,  Zubair Ahmed Baig

IPC: F01D11/24

Abstract: A hybrid energy storage and control system for a clearance control system for a gas turbine engine may comprise a hybrid electric power source, a first converter, a second converter configured to receive electric power from the hybrid electric power source via the first converter and configured to send the electric power to a heating element for controlling a blade tip clearance between a rotor blade and an outer structure of the gas turbine engine, and a controller in electronic communication with the second converter. The hybrid electric power source may comprise a battery, a supercapacitor, and/or an ultracapacitor.

公开(公告)号：US20200182113A1

公开(公告)日：2020-06-11

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：US20200031480A1

公开(公告)日：2020-01-30

申请号：US16524752

申请日：2019-07-29

Applicant: United Technologies Corporation

Inventor： Zubair Ahmed Baig ,  Neil Terwilliger ,  Sorin Bengea

IPC: B64D27/02 ,  H02J7/14

Abstract: A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.

公开(公告)号：US11261751B2

公开(公告)日：2022-03-01

申请号：US16511276

申请日：2019-07-15

Applicant: United Technologies Corporation

Inventor： David A. Golfin ,  Neil Terwilliger

IPC: F01D15/10 ,  F01D13/02 ,  F01D15/12 ,  F01D17/08 ,  F02C3/113

Abstract: A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and turbine, and the high speed spool includes a high pressure compressor and turbine. The hybrid electric propulsion system includes an electric generator configured to extract power from the low speed spool, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to determine a target operating condition of the low pressure compressor to achieve a compressor stability margin in the gas turbine engine, determine a current operating condition of the low pressure compressor, and control a power transfer between the electric generator of the low speed spool and the electric motor of the high speed spool to adjust the current operating condition based on the target operating condition.

公开(公告)号：US20210054784A1

公开(公告)日：2021-02-25

申请号：US16549759

申请日：2019-08-23

Applicant: United Technologies Corporation

Inventor： Steven M. O'Flarity ,  Neil Terwilliger

IPC: F02C6/14 ,  H02K11/00 ,  H02K7/116 ,  H02K7/18

Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.