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    SYSTEMS AND METHODS FOR POWER TURBINE GOVERNING
    1.
    发明申请
    SYSTEMS AND METHODS FOR POWER TURBINE GOVERNING 审中-公开

    公开(公告)号：US20190309689A1

    公开(公告)日：2019-10-10

    申请号：US15945556

    申请日：2018-04-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Richard P. Meisner ,  Chaohong Cai ,  Timothy J. Crowley

    IPC: F02C9/56 ,  F02C9/52 ,  F02C9/54

    Abstract: A power turbine control system for a gas turbine engine may comprise a controller comprising one or more processors in communication with the gas turbine engine. The processors may comprise an engine control module configured to receive a torque request signal and generate a torque achieved signal. A rate of change of power turbine speed estimation module may generate an estimated rate of change of power turbine speed signal. A dynamic inversion power turbine governor module may generate the torque request signal based on the torque achieved signal and estimated rate of change of power turbine speed signal.

    Cascaded multi-variable control system for a turboshaft engine
    2.
    发明授权
    Cascaded multi-variable control system for a turboshaft engine 有权

    公开(公告)号：US10113487B2

    公开(公告)日：2018-10-30

    申请号：US14282544

    申请日：2014-05-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Chaohong Cai ,  Timothy J. Crowley ,  Richard P. Meisner

    IPC: F02C9/54 ,  F02C9/28

    Abstract: A control system for a gas turbine engine is disclosed. The control system may include a computer processor. The control system may also include an outer loop control module programmed into the computer processor to determine a torque request based at least in part on a real-time collective lever angle command. The control system may also include an inner loop control module programmed into the computer processor to receive the torque request from the outer loop control module, to determine fuel flow and inlet guide vane schedules based at least in part on the received torque request, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow and inlet guide vane schedules.

    Optimal Thrust Control of an Aircraft Engine
    3.
    发明申请
    Optimal Thrust Control of an Aircraft Engine 审中-公开
    飞机发动机的最佳推力控制

    公开(公告)号：US20160138523A1

    公开(公告)日：2016-05-19

    申请号：US14921019

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Chaohong Cai ,  Timothy J. Crowley ,  Mark E. Lacour ,  David L. Ma

    IPC: F02K1/17 ,  F02C9/50

    CPC classification number: F02K1/17 ,  F02C9/00 ,  F02C9/50 ,  F02C9/54 ,  F05D2270/20 ,  F05D2270/44 ,  F05D2270/71

    Abstract: A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system may further include a control module for determining a control command for the gas turbine engine. The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal and an estimated thrust value. The control system may further include an actuator for controlling the gas turbine engine based on the control command.

    Abstract translation: 公开了一种燃气轮机的控制系统，燃气轮机的控制方法和燃气轮机。 控制系统可以包括用于基于与飞行条件相关的排气喷嘴位置的喷嘴计划来确定排气喷嘴位置目标的喷嘴调度器。 控制系统还可以包括用于确定燃气涡轮发动机的控制命令的控制模块。 控制命令至少可以包括燃料流量指令和排气喷嘴位置指令，并且控制命令可以至少基于排气喷嘴位置目标和估计推力值。 控制系统还可以包括用于基于控制命令控制燃气涡轮发动机的致动器。

    MACHINE LEARNED AERO-THERMODYNAMIC ENGINE INLET CONDITION SYNTHESIS
    4.
    发明申请
    MACHINE LEARNED AERO-THERMODYNAMIC ENGINE INLET CONDITION SYNTHESIS 审中-公开

    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

    IPC: F02C7/057 ,  G06N3/08 ,  G05B13/02

    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.

    Model predictive control sub-system power management
    5.
    发明授权
    Model predictive control sub-system power management 有权

    公开(公告)号：US10655494B2

    公开(公告)日：2020-05-19

    申请号：US16163277

    申请日：2018-10-17

    Applicant: United Technologies Corporation

    Inventor： Martin Richard Amari ,  Joshua Adams ,  Manuj Dhingra ,  Timothy J. Crowley ,  Coy Bruce Wood

    IPC: F01D25/00 ,  G05B13/04

    Abstract: A system for controlling a plurality of electromechanical effectors operably connected to an engine to control engine parameters. The system also includes a plurality of sensors operably connected to measure a state or parameter of each effector, a power supply configured to supply power to the plurality of effectors, and a controller operably connected to the plurality of sensors, the plurality of effectors, and the power supply. The controller executes a method for an adaptive model-based control for controlling each effector, The method includes receiving a request indicative of a desired state for each effector, receiving a weighting associated each request, obtaining information about a current state of each effector, and updating an adaptive model based control (MBC) based upon the information. The method also includes generating a control command for an effector based upon the adaptive MBC and commanding the effector based upon the control command.

    OPTIMAL THRUST CONTROL OF AN AIRCRAFT ENGINE
    6.
    发明申请
    OPTIMAL THRUST CONTROL OF AN AIRCRAFT ENGINE 审中-公开

    公开(公告)号：US20200025130A1

    公开(公告)日：2020-01-23

    申请号：US16377488

    申请日：2019-04-08

    Applicant: United Technologies Corporation

    Inventor： Chaohong Cai ,  Timothy J. Crowley ,  Mark E. Lacour ,  David Lei Ma

    IPC: F02K1/17 ,  F02C9/00 ,  F02C9/54 ,  F02C9/50

    Abstract: A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system may further include a control module for determining a control command for the gas turbine engine. The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal and an estimated thrust value. The control system may further include an actuator for controlling the gas turbine engine based on the control command.

    Optimal thrust control of an aircraft engine
    7.
    发明授权
    Optimal thrust control of an aircraft engine 有权

    公开(公告)号：US10253725B2

    公开(公告)日：2019-04-09

    申请号：US14921019

    申请日：2015-10-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Chaohong Cai ,  Timothy J. Crowley ,  Mark E. Lacour ,  David L. Ma

    IPC: F02K1/17 ,  F02C9/50 ,  F02C9/00 ,  F02C9/54

    Abstract: A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions. The control system may further include a control module for determining a control command for the gas turbine engine. The control command may include, at least, a fuel flow command and an exhaust nozzle position command and the control command may be based on, at least, the exhaust nozzle position goal and an estimated thrust value. The control system may further include an actuator for controlling the gas turbine engine based on the control command.

    LEAK DETECTION, ISOLATION AND ACCOMMODATION ASSEMBLY FOR GAS TURBINE ENGINES
    8.
    发明申请
    LEAK DETECTION, ISOLATION AND ACCOMMODATION ASSEMBLY FOR GAS TURBINE ENGINES 审中-公开

    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

    IPC: F02C7/22 ,  F02C7/232 ,  F02C7/236

    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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