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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
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.
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公开(公告)号：US20200079517A1
公开(公告)日：2020-03-12
申请号：US16126200
申请日：2018-09-10
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Sorin Bengea
Abstract: An aspect includes a variable cycle system of a gas turbine engine. The variable cycle system includes an actuation system, an electric component, and a controller. The actuation system is configured to adjust a variable cycle of turbomachinery of the gas turbine engine. The electric component is operable to provide a shaft power supply or a load corresponding respectively to an adjustment of the turbomachinery. The controller is operable to adjust an output of either or both of the actuation system and the electric component for separate control of thrust and cycle responses.
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公开(公告)号：US20200248622A1
公开(公告)日：2020-08-06
申请号：US16265319
申请日：2019-02-01
Applicant: United Technologies Corporation
Inventor： Timothy J. Crowley , Ramesh Rajagopalan , Sorin Bengea
Abstract: A system for neural network compensated aero-thermodynamic gas turbine engine parameter/inlet condition synthesis. The system includes an aero-thermodynamic engine model configured to produce a real-time model-based estimate of engine parameters, a machine learning model configured to generate model correction errors indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters, and a comparator configured to produce residuals indicating a difference between the real-time model-based estimate of engine parameters and the sensed values of the engine parameters. The system also includes an inlet condition estimator configured to iteratively adjust an estimate of inlet conditions based on the residuals and adaptive control laws configured to produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions.
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公开(公告)号：US20170321608A1
公开(公告)日：2017-11-09
申请号：US15147173
申请日：2016-05-05
Applicant: United Technologies Corporation
Inventor： Timothy J. Crowley , Tyler J. Selstad , Sorin Bengea , Robert H. Luppold
CPC classification number: F02C7/222 , F02C7/22 , F02C7/232 , F02C7/236 , F02C9/00 , F02C9/28 , F05D2220/32 , F05D2260/80
Abstract: A fuel system for a gas turbine engine includes, among other things, a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters. One or more fuel sensors are configured to measure at least one fuel condition relating to flow through the fuel flow path. A fuel observation assembly is coupled to one or more engine sensors configured to measure at least one engine condition. The fuel observation assembly comprises an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon the set of failure parameters, an observation module operable to calculate an observed condition of each of the plurality of localized nodes, the observed condition based on present values of the at least one fuel condition and the at least one engine condition, and a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and the observed condition for each of the plurality of localized nodes.
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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
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.
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Patent Agency Ranking
6.发明授权公开(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.
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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
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.
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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
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.
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公开(公告)号：US11555455B2
公开(公告)日：2023-01-17
申请号：US16783512
申请日：2020-02-06
Applicant: United Technologies Corporation
Inventor： Timothy J. Crowley , Sorin Bengea , Manuj Dhingra , David Gelwan , Kevin Hendricks , Joshua Adams , Martin Richard Amari , Richard P. Meisner , David Lei Ma
Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.
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公开(公告)号：US11167858B2
公开(公告)日：2021-11-09
申请号：US16126200
申请日：2018-09-10
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Sorin Bengea
Abstract: An aspect includes a variable cycle system of a gas turbine engine. The variable cycle system includes an actuation system, an electric component, and a controller. The actuation system is configured to adjust a variable cycle of turbomachinery of the gas turbine engine. The electric component is operable to provide a shaft power supply or a load corresponding respectively to an adjustment of the turbomachinery. The controller is operable to adjust an output of either or both of the actuation system and the electric component for separate control of thrust and cycle responses.
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