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    System and method for providing efficiency and cost analysis during steam path audits
    4.
    发明授权
    System and method for providing efficiency and cost analysis during steam path audits 失效
    在蒸汽通道审核中提供效率和成本分析的系统和方法

    公开(公告)号：US06980928B1

    公开(公告)日：2005-12-27

    申请号：US09657632

    申请日：2000-09-06

    申请人： Catherine Mary Graichen ,  James Patrick Quaile ,  William James Sumner

    发明人： Catherine Mary Graichen ,  James Patrick Quaile ,  William James Sumner

    IPC分类号： F01D15/10 ,  F01D17/00 ,  F01K13/02 ,  F02C9/00 ,  G05B15/02 ,  G06Q50/06 ,  G06F11/30

    CPC分类号： F01D17/00 ,  F01K13/02 ,  F02C9/00 ,  F05D2220/31 ,  F05D2270/01 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/305 ,  G05B15/02 ,  G06Q50/06 ,  Y02E40/76 ,  Y04S10/545

    摘要： This disclosure describes a system and method for providing efficiency and cost analysis for a power generation unit. The system of this disclosure includes a current condition data acquisition logic that acquires a plurality of current condition variables for the power generation unit. A design constants acquisition logic acquires a plurality of design constants for the power generation unit; and an analysis logic calculates a operational efficiency of the power generation unit. The method provides efficiency and cost analysis for a power generation unit. The method includes the steps of acquiring a plurality of current condition variables for the power generation unit, and acquiring a plurality of design constants for said power generation unit. With the current condition variables and design constants, the method calculates an operational efficiency of the power generation unit.

    摘要翻译： 本公开描述了一种用于为发电单元提供效率和成本分析的系统和方法。 本公开的系统包括获取用于发电单元的多个当前状态变量的当前条件数据获取逻辑。 设计常数采集逻辑获取用于发电单元的多个设计常数; 并且分析逻辑计算发电单元的运行效率。 该方法为发电单元提供效率和成本分析。 该方法包括以下步骤：获取用于发电单元的多个当前状态变量，以及获取用于所述发电单元的多个设计常数。 利用当前条件变量和设计常数，该方法计算出发电单元的运行效率。

    Warm start control of an active clearance control for a gas turbine engine
    5.
    发明授权
    Warm start control of an active clearance control for a gas turbine engine 有权

    公开(公告)号：US11982189B2

    公开(公告)日：2024-05-14

    申请号：US17339604

    申请日：2021-06-04

    申请人： Raytheon Technologies Corporation

    发明人： Patrick D. Couture ,  Norman Cleesattel

    IPC分类号： F01D11/20 ,  F02C9/00

    CPC分类号： F01D11/20 ,  F02C9/00 ,  F05D2220/32 ,  F05D2270/01

    摘要： According to an aspect, a gas turbine engine includes a turbine section with a turbine case and a plurality of turbine blades within the turbine case. The gas turbine engine also includes an active clearance control system with an active clearance control cooling air supply, a valve pneumatically coupled to the active clearance control cooling air supply, and a controller. The controller is configured to determine an active cooling control schedule adjustment based on a condition of the gas turbine engine, operate the active clearance control system according to an active cooling control schedule as modified by the active cooling control schedule adjustment, apply a decay function to the active cooling control schedule adjustment to reduce an effect on the active cooling control schedule adjustment, and resume operating the active clearance control system according to the active cooling control schedule based on an active cooling control condition being met.

    Aircraft hybrid propulsion system
    6.
    发明授权
    Aircraft hybrid propulsion system 有权

    公开(公告)号：US11754001B2

    公开(公告)日：2023-09-12

    申请号：US17444133

    申请日：2021-07-30

    申请人： ROLLS-ROYCE plc

    发明人： Peter Swann

    IPC分类号： F02C6/14 ,  F02C7/36 ,  F02C6/20 ,  F02C9/00

    CPC分类号： F02C7/36 ,  F02C6/20 ,  F02C9/00 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2270/01

    摘要： A control system for an aircraft hybrid propulsion system comprising a gas turbine engine coupled to an electric generator, a propulsor coupled to an electric motor, and an electrical storage device coupled to the motor and the generator. The control system configured to operate the propulsion system in a first descent mode and a second descent mode. In the first descent mode, the gas turbine engine is operated at a first engine power level and the generator is operated at a first generator power level. In the second descent mode, the gas turbine engine is operated at a second engine power level, higher than the first engine power level, and the generator is operated at a second generator power level, higher than the first generator power level. Electric power generated by the electric generator during operation in the second descent mode is stored in the electrical storage device.

    ELECTRICAL POWER GENERATOR FOR A GAS TURBINE ENGINE
    8.
    发明申请
    ELECTRICAL POWER GENERATOR FOR A GAS TURBINE ENGINE 有权
    燃气轮机发电机

    公开(公告)号：US20150244296A1

    公开(公告)日：2015-08-27

    申请号：US14608860

    申请日：2015-01-29

    申请人： ROLLS-ROYCE PLC

    发明人： Huw Llewelyn EDWARDS

    IPC分类号： H02P9/04 ,  F02C9/00 ,  H02P9/00 ,  F02C6/20

    CPC分类号： H02P9/04 ,  F01D15/10 ,  F02C6/20 ,  F02C9/00 ,  F02C9/28 ,  F05D2220/323 ,  F05D2220/764 ,  F05D2220/7642 ,  F05D2220/7646 ,  F05D2270/01 ,  F05D2270/02 ,  F05D2270/061 ,  F05D2270/071 ,  F05D2270/304 ,  F05D2270/309 ,  F05D2270/332 ,  F05D2270/335 ,  H02P9/007 ,  H02P9/48

    摘要： An aircraft electrical power generation system includes an AC generator having a rotor including a plurality of electromagnetic rotor-windings and stator including plurality of electrical stator-windings. The rotor mechanically coupled to a shaft of a gas turbine engine by transmission-system. The generator includes a frequency controller, a torque sensor determining a torque on the transmission-system by the generator and controller to operate the system in first and second modes. In first mode, the power output frequency of the generator controlled by the frequency controller within limits, and reduced idle signal going to a turbine engine controller. In second mode, the power output frequency of the generator not controlled by the frequency controller and increased idle signal going to the turbine engine controller. The controller operates the system in first mode when the torque is below a limit, and in second mode when the torque is above a limit.

    摘要翻译： 飞机发电系统包括具有转子的交流发电机，该转子包括多个电磁转子绕组和包括多个电定子绕组的定子。 转子通过传动系统机械联接到燃气涡轮发动机的轴。 发电机包括频率控制器，扭矩传感器，其通过发电机和控制器确定传动系统上的转矩，以在第一和第二模式下操作系统。 在第一模式中，由频率控制器控制的发电机的功率输出频率在限制内，并且减少空转信号进入涡轮发动机控制器。 在第二模式中，发电机的功率输出频率不受频率控制器控制，并且空载信号增加到涡轮发动机控制器。 当转矩低于极限时，控制器以第一模式运行系统，而当转矩高于极限时，控制器处于第二模式。

    System and method for non-model based control utilizing turbine exit mach number surrogate
    9.
    发明授权
    System and method for non-model based control utilizing turbine exit mach number surrogate 有权

    公开(公告)号：US12031490B2

    公开(公告)日：2024-07-09

    申请号：US17479200

    申请日：2021-09-20

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Harold Lamar Jordan ,  David Spencer Ewens

    IPC分类号： F02C9/20 ,  F02C9/22

    CPC分类号： F02C9/22 ,  F05D2270/01

    摘要： A system includes a gas turbine system including a compressor, a combustor, a turbine, and an exhaust section. The system also includes multiple sensors coupled to components of the gas turbine system. The system further includes a controller communicatively coupled to the gas turbine system and the multiple sensors and configured to control operations of the gas turbine system, wherein the controller is configured to calculate a surrogate value for turbine exit Mach number based on the feedback from the multiple sensors and to utilize the surrogate value to derive a control action for the gas turbine system.