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    SYSTEM AND METHOD FOR EFFICIENTLY DETERMINING A PHASE SHIFT IN A PROPULSION SYSTEM
    11.
    发明申请
    SYSTEM AND METHOD FOR EFFICIENTLY DETERMINING A PHASE SHIFT IN A PROPULSION SYSTEM 有权

    公开(公告)号：US20240418131A1

    公开(公告)日：2024-12-19

    申请号：US18335340

    申请日：2023-06-15

    Applicant: General Electric Company

    Inventor： Stefan Joseph Cafaro ,  Kalpesh Singal ,  Eric Richard Westervelt

    IPC: F02C9/00 ,  F02K3/00

    Abstract: A propulsion system includes at least two propulsors. The at least two propulsors each comprising a fan having a plurality of fan blades. A controller includes memory and one or more processors. The memory stores instructions that when executed by the one or more processors cause the system to perform the following: determine a pairwise phase difference between one propulsor of the at least two propulsors and another propulsor of the at least two propulsors; generate a reference phase angle; determine a target phase shift for each propulsor of the at least two propulsors; and adjust a speed of each propulsor of the at least two propulsors based on the target phase shift until the pairwise phase difference is equal to the reference phase angle.

    Fleet Mission Advisor
    14.
    发明申请
    Fleet Mission Advisor 审中-公开

    公开(公告)号：US20190187727A1

    公开(公告)日：2019-06-20

    申请号：US15848693

    申请日：2017-12-20

    Applicant: General Electric Company

    Inventor： James Ryan Reepmeyer ,  Eric Richard Westervelt

    IPC: G05D1/10 ,  G07C5/08 ,  G08G5/00

    CPC classification number: G05D1/104 ,  F41H13/0043 ,  G07C5/0808 ,  G07C5/0816 ,  G08G5/003

    Abstract: A fleet mission control system for a network of aerial vehicles including power thermal management systems is provided. According to examples of the disclosed technology a control system receives one or more mission objectives for a network of aircraft including two or more aerial vehicles. Each aerial vehicle includes a power-thermal management system. The control system receives system state information for the network of aircraft. The system state information includes PTMS state data. The control system determines a set of aircraft commands for the network of aircraft based on the one or more mission objectives and the PTMS state data, and generates an output signal based on the set of aircraft commands.

    Flight path optimization using nonlinear programming
    16.
    发明授权
    Flight path optimization using nonlinear programming 有权
    使用非线性规划的飞行路径优化

    公开(公告)号：US09564056B1

    公开(公告)日：2017-02-07

    申请号：US14844892

    申请日：2015-09-03

    Applicant: General Electric Company

    Inventor： Reza Ghaemi ,  Eric Richard Westervelt ,  Mark Darnell

    IPC: G06F7/70 ,  G06F19/00 ,  G08G5/00 ,  G05D1/04 ,  G06F17/50 ,  G06F17/10

    CPC classification number: G08G5/0095 ,  G05D1/0005 ,  G06F17/13 ,  G06F17/5009 ,  G06F17/5095 ,  G08G5/0034

    Abstract: A method, medium, and system to receive a mathematical model representation of performance characteristics for an aircraft and an engine combination; perform a projection based model order reduction on the mathematical model representation; eliminate, based on the projected model, fast dynamics components of the mathematical model representation; determine a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics; set a flight path angle and a throttle level angle as a control to minimize fuel consumption for the modeled aircraft and engine combination; discretize equations of motion for the modeled aircraft and engine combination and formulate optimization equations as a nonlinear programming problem; and determine an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed.

    Abstract translation: 一种用于接收航空器和发动机组合的性能特征的数学模型表示的方法，介质和系统; 对数学模型表示执行基于投影的模型顺序减少; 消除，基于预测模型，数学模型表示的快速动力学组件; 确定一个降序模型，作为微分代数方程，其中代数方程代替快速动力学; 设置飞行路径角度和节气门水平角作为控制，以最小化建模的飞机和发动机组合的燃料消耗; 对模型飞机和发动机组合的运动方程进行离散化，并将优化方程式设计为非线性规划问题; 并且确定最佳开环控制，其使得建模的飞行器和发动机组合的燃料消耗最小化以爬升到规定的巡航高度和空速。

    CLEARANCE CONTROL FOR ENGINE PERFORMANCE RETENTION
    20.
    发明公开
    CLEARANCE CONTROL FOR ENGINE PERFORMANCE RETENTION 审中-公开

    公开(公告)号：US20230279782A1

    公开(公告)日：2023-09-07

    申请号：US17686537

    申请日：2022-03-04

    Applicant: General Electric Company

    Inventor： Harry Kirk Mathews, JR. ,  Eric Richard Westervelt

    IPC: F01D11/24 ,  F01D21/00

    CPC classification number: F01D11/24 ,  F01D21/003 ,  F05D2260/232 ,  F05D2260/821 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/71

    Abstract: Clearance control schemes for controlling a clearance defined between a first component and a second component of a gas turbine engine are provided. In one aspect, an engine controller of the gas turbine engine implements a clearance control scheme, which includes receiving data indicating a clearance between the first component and the second component, the clearance being at least one of a measured clearance captured by a sensor and a predicted clearance specific to the gas turbine engine at that point in time; comparing the clearance to an allowable clearance; determining a clearance setpoint for a clearance adjustment system based on a clearance difference determined by comparing the clearance to the allowable clearance; and causing the clearance adjustment system to adjust the clearance to the allowable clearance based on the clearance setpoint.

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