公开(公告)号：US11370556B2

公开(公告)日：2022-06-28

申请号：US16575707

申请日：2019-09-19

Applicant: United Technologies Corporation

Inventor： Zubair Ahmed Baig ,  Sorin Bengea ,  Gary L. Miles

IPC: B64D33/00 ,  B64D31/00 ,  H02J9/06 ,  H02J4/00

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, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.

公开(公告)号：US11565821B2

公开(公告)日：2023-01-31

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 ,  B60L15/20 ,  B60L50/61 ,  H02J7/34

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：US20210394916A1

公开(公告)日：2021-12-23

申请号：US16575707

申请日：2019-09-19

Applicant: United Technologies Corporation

Inventor： Zubair Ahmed Baig ,  Sorin Bengea ,  Gary L. Miles

IPC: B64D33/00 ,  H02J4/00 ,  H02J9/06 ,  B64D31/00

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, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.

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：US10759545B2

公开(公告)日：2020-09-01

申请号：US16012040

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Zubair Ahmed Baig

IPC: B64D31/06 ,  B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  H02K7/18 ,  H02K11/00 ,  F02C6/20 ,  F02C6/14 ,  H02K7/20

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

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：US20190382123A1

公开(公告)日：2019-12-19

申请号：US16012040

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Zubair Ahmed Baig

IPC: B64D31/06 ,  B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  F02C6/20 ,  F02C6/14

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.