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    COMPACT AERO-THERMO MODEL BASED CONTROL SYSTEM
    21.
    发明申请
    COMPACT AERO-THERMO MODEL BASED CONTROL SYSTEM 审中-公开

    公开(公告)号：US20190093566A1

    公开(公告)日：2019-03-28

    申请号：US16203995

    申请日：2018-11-29

    Applicant: United Technologies Corporation

    Inventor： Boris Karpman ,  Thomas Niemczycki ,  Ian Michael Dinsmore ,  David Sembiante ,  Robert H. Luppold

    IPC: F02C7/26 ,  F02C9/16 ,  G05B13/04 ,  F04D29/32 ,  F02C3/04 ,  F02C9/20 ,  G05D7/06 ,  G05B17/02 ,  F01D21/00 ,  G05B23/02

    Abstract: Systems and methods for controlling a fluid-based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, where the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based a series of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.

    COMPACT AERO-THERMO MODEL BASED ENGINE POWER CONTROL
    22.
    发明申请
    COMPACT AERO-THERMO MODEL BASED ENGINE POWER CONTROL 审中-公开

    公开(公告)号：US20190040798A1

    公开(公告)日：2019-02-07

    申请号：US16163687

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Boris Karpman ,  Richard P. Meisner ,  Matthew Donald ,  Thomas E. Case

    IPC: F02C7/26 ,  F02C9/16 ,  G05B13/04 ,  G05B17/02 ,  G05D7/06 ,  F02C9/20 ,  F02C3/04 ,  F04D29/32 ,  G05B23/02 ,  F01D21/00

    Abstract: Systems and methods for controlling a fluid-based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, where the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the current state derivatives and solver state errors is based on mathematical abstractions of physical laws that govern behavior of a component of a cycle of a control device. The model processor may further include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.

    Compact Aero-Thermo Model Based Degraded Mode Control
    27.
    发明申请
    Compact Aero-Thermo Model Based Degraded Mode Control 审中-公开
    基于紧凑型航空 - 热模型的降级模式控制

    公开(公告)号：US20160017813A1

    公开(公告)日：2016-01-21

    申请号：US14767818

    申请日：2014-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Boris Karpman ,  Richard P. Meisner

    IPC: F02C9/16 ,  G05B17/02

    CPC classification number: F02C7/26 ,  F01D21/003 ,  F02C3/04 ,  F02C9/16 ,  F02C9/20 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/81 ,  F05D2260/85 ,  G05B13/04 ,  G05B17/02 ,  G05B23/0254 ,  G05D7/0629

    Abstract: Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The system may include a control law for directing the actuator as a function of a model output and for determining if the control device is operating with deteriorated conditions. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of an open loop model.

    Abstract translation: 公开了用于控制基于流体的工程系统的系统和方法。 系统和方法可以包括用于生成模型输出的模型处理器，模型处理器包括用于设置模型处理器的动态状态的设置状态模块，基于模型操作模式输入到开环模型的动态状态。 系统可以包括用于根据模型输出来引导致动器的控制规则，并且用于确定控制装置是否在劣化条件下运行。 模型处理器还可以包括用于基于先前状态模型输出和开环模型的当前状态模型来确定模型的估计状态的估计状态模块。

    COMPACT AERO-THERMO MODEL STABILIZATION WITH COMPRESSIBLE FLOW FUNCTION TRANSFORM
    28.
    发明申请
    COMPACT AERO-THERMO MODEL STABILIZATION WITH COMPRESSIBLE FLOW FUNCTION TRANSFORM 审中-公开
    具有可压缩流动函数变换的紧凑型AERO-THERMO模型稳定

    公开(公告)号：US20160003164A1

    公开(公告)日：2016-01-07

    申请号：US14769860

    申请日：2014-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Boris Karpman ,  Serge L. Shishkin

    IPC: F02C9/16 ,  F01D21/00

    CPC classification number: F02C7/26 ,  F01D21/003 ,  F02C3/04 ,  F02C9/16 ,  F02C9/20 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/81 ,  F05D2260/85 ,  G05B13/04 ,  G05B17/02 ,  G05B23/0254 ,  G05D7/0629

    Abstract: Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates a current state model as a function of the dynamic states and the model input, wherein a constraint on the current state model is based a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control system and including a series of utilities, the utilities are based on mathematical abstractions of physical properties associated with the component. The series of cycle synthesis modules may include a flow module for mapping a flow curve relating a compressible flow function to a pressure ratio and for defining a solution point located on the flow curve and a base point located off the flow curve.

    Abstract translation: 公开了用于控制基于流体的工程系统的系统和方法。 系统和方法可以包括用于生成模型输出的模型处理器，模型处理器包括用于设置模型处理器的动态状态的设置状态模块，基于模型操作模式输入到开环模型的动态状态，其中， 开环模型生成作为动态和模型输入的函数的当前状态模型，其中对当前状态模型的约束基于一系列循环综合模块，该系列循环综合模块的每个成员对 控制系统的一个循环并且包括一系列实用程序，该实用程序基于与组件相关联的物理属性的数学抽象。 一系列循环合成模块可以包括流模块，用于将与可压缩流函数相关联的流量曲线映射到压力比，并且用于定义位于流量曲线上的解点和位于流量曲线外的基点。

    MODEL BASED ENGINE INLET CONDITION ESTIMATION
    29.
    发明申请
    MODEL BASED ENGINE INLET CONDITION ESTIMATION 有权
    基于模型的发动机入口条件估计

    公开(公告)号：US20140090456A1

    公开(公告)日：2014-04-03

    申请号：US13631359

    申请日：2012-09-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Richard P. Meisner ,  Alexandra I. Britten ,  Stefan M. Poth, JR. ,  Boris Karpman

    IPC: G01M15/14

    CPC classification number: G01M15/14 ,  G05B23/0254 ,  G05B23/0297

    Abstract: A gas turbine engine inlet sensor fault detection and accommodation system comprises an engine model, an engine parameter comparison block, an inlet condition estimator, control laws, and a fault detection and accommodation system. The engine model is configured to produce a real-time model-based estimate of engine parameters. The engine parameter comparison block is configured to produce residuals indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters. The inlet condition estimator is configured to iteratively adjust an estimate of inlet conditions based on the residuals. The control laws are configured to produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions. The fault detection and accommodation system is configured to detect faults in inlet condition sensors, select sensed inlet conditions for use by the control laws in the event of no fault, and select estimated inlet conditions for use by the control laws in the event of inlet condition sensor fault.

    Abstract translation: 燃气涡轮发动机入口传感器故障检测和调节系统包括发动机模型，发动机参数比较块，入口状态估计器，控制规律以及故障检测和调节系统。 引擎模型被配置为产生基于实时模型的发动机参数估计。 引擎参数比较块被配置为产生指示基于实时模型的发动机参数估计与发动机参数的感测值之间的差异的残差。 入口条件估计器被配置为基于残差迭代地调整入口条件的估计。 控制规则被配置为基于入口条件来生成用于控制燃气涡轮发动机执行器的发动机控制参数。 故障检测和调试系统被配置为检测入口状态传感器中的故障，选择在无故障情况下由控制规则使用的感应入口条件，并在入口条件下选择控制规则使用的估计入口条件 传感器故障。

    MODEL BASED FUEL-AIR RATIO CONTROL
    30.
    发明申请
    MODEL BASED FUEL-AIR RATIO CONTROL 审中-公开
    基于模型的燃油比控制

    公开(公告)号：US20140090392A1

    公开(公告)日：2014-04-03

    申请号：US13631394

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： Richard P. Meisner ,  Brian V. Winebrenner ,  Matthew R. Feulner ,  Boris Karpman ,  David L. Ma

    IPC: F02C9/54

    CPC classification number: F02C9/54 ,  F02C9/26 ,  F05D2270/092 ,  F05D2270/71 ,  F23N2023/40 ,  F23N2041/20 ,  Y02T50/677

    Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estimate combustor fuel-air ratio based on a realtime model-based estimate of combustor airflow, and commands engine actuators to correct for a difference between the estimated combustor fuel-air ratio and a limit fuel-air ratio selected to avoid lean blowout.

    Abstract translation: 燃气涡轮发动机包括压缩机，燃烧器，涡轮机和电子发动机控制系统。 压缩机，燃烧器和涡轮机以流动系列布置。 电子发动机控制系统被配置为基于燃烧器空气流的基于实时模型的估计来估计燃烧器燃料空气比，并且命令发动机执行器来校正估计的燃烧器燃料空气比和极限燃料空气比之间的差 选择避免精益井喷。

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