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    Shaft break detection
    11.
    发明授权
    Shaft break detection 有权
    轴断裂检测

    公开(公告)号：US09410444B2

    公开(公告)日：2016-08-09

    申请号：US13667220

    申请日：2012-11-02

    Applicant: ROLLS-ROYCE PLC

    Inventor： Marko Bacic

    IPC: F01D21/04 ,  F01D17/04 ,  F01D17/06 ,  F01D17/08 ,  F01D21/00

    CPC classification number: F01D21/04 ,  F01D17/04 ,  F01D17/06 ,  F01D17/08 ,  F01D17/085 ,  F01D21/003 ,  F01D21/045

    Abstract: The present invention provides a method of detecting shaft break in a shaft system comprising a shaft coupled between two masses. The method comprises a number of steps. Firstly, to define a time-dependent rotational speed equation for the shaft in terms of system inertia for an engine transient event. Then to discretize the rotational speed equation in terms of a discrete time constant in the discrete domain. Then to recursively define the discretized equation to give a recursive equation and to solve the recursive equation to determine the discrete time constant. Then to define a threshold as a function of engine power and then to set a shaft break signal to TRUE if the discrete time constant is greater than the threshold. A shaft break detection system is also provided by the present invention.

    Abstract translation: 本发明提供了一种在轴系中检测轴断裂的方法，该轴系包括联接在两个质量块之间的轴。 该方法包括多个步骤。 首先，根据发动机瞬态事件的系统惯性来定义轴的时间相关转速方程。 然后根据离散域中的离散时间常数离散转速方程。 然后递归地定义离散方程以给出递归方程，并求解递归方程以确定离散时间常数。 然后定义阈值作为发动机功率的函数，然后如果离散时间常数大于阈值，则将轴断点信号设置为TRUE。 本发明还提供了轴断裂检测系统。

    Gas turbine engine having a multi-variable closed loop controller for regulating tip clearance
    12.
    发明授权
    Gas turbine engine having a multi-variable closed loop controller for regulating tip clearance 有权
    具有用于调节顶端间隙的多变量闭环控制器的燃气涡轮发动机

    公开(公告)号：US09255492B2

    公开(公告)日：2016-02-09

    申请号：US13682122

    申请日：2012-11-20

    Applicant: ROLLS-ROYCE PLC

    Inventor： Marko Bacic

    IPC: F01D5/08 ,  F02C7/18 ,  F01D25/14 ,  F01D11/24 ,  F01D17/02 ,  F01D17/08 ,  F02C6/08 ,  F02C3/13 ,  F02C9/18

    CPC classification number: F01D11/24 ,  F01D5/081 ,  F01D17/02 ,  F01D17/085 ,  F01D25/14 ,  F02C3/13 ,  F02C6/08 ,  F02C7/18 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/205 ,  F05D2270/303 ,  F05D2270/305 ,  F05D2270/44

    Abstract: A gas turbine engine has, in flow series, a compressor section, a combustor, and a turbine section. The gas turbine engine further has a system (i) for cooling the turbine section and (ii) for providing tip clearance control between turbine blades of the turbine section and a plurality of circumferentially distributed segments which form an annular shroud surrounding the outer tips of the turbine blades. The system includes a turbine section cooling sub-system which diverts a first cooling air flow received from the compressor section to a heat exchanger and then to the turbine section to cool components thereof. The first cooling air flow by-passes the combustor and is cooled in the heat exchanger. The turbine section cooling subsystem has a first valve arrangement which regulates the first cooling air flow. The system further includes a tip clearance control sub-system which supplies a second cooling air flow to an engine case to which the segments are mounted. The second cooling air flow regulates thermal expansion of the case and thereby controls the clearance between the segments and the outer tips. The tip clearance control sub-system has a second valve arrangement which regulates the second cooling air flow. The system further includes a closed-loop controller which issues first and second demand signals to respectively the first and the second valve arrangements. Each of the first and second demand signals are determined on the basis of: (i) a value of the first demand signal at a previous time step, and a measurement or estimate of turbine section component temperature, and (ii) a value of the second demand signal at a previous time step, and a measurement or estimate of tip clearance.

    Abstract translation: 燃气涡轮发动机以流动方式具有压缩机部分，燃烧器和涡轮部分。 燃气涡轮发动机还具有用于冷却涡轮机部分的系统（i）和（ii）用于在涡轮机部分的涡轮机叶片之间提供顶端间隙控制和多个周向分布的节段，其形成围绕 涡轮叶片。 该系统包括涡轮部分冷却子系统，其将从压缩机部分接收的第一冷却空气流转移到热交换器，然后转移到涡轮部分以冷却其部件。 第一冷却空气流绕过燃烧器并在热交换器中被冷却。 涡轮部分冷却子系统具有调节第一冷却空气流的第一阀装置。 该系统还包括一个顶部间隙控制子系统，其将第二冷却空气流提供给安装有该段的发动机壳体。 第二冷却空气流调节壳体的热膨胀，从而控制段和外端之间的间隙。 顶端间隙控制子系统具有调节第二冷却空气流的第二阀装置。 该系统还包括一个闭环控制器，其分别发出第一和第二需求信号给第一和第二阀装置。 第一和第二需求信号中的每一个基于：（i）先前时间步骤中的第一需求信号的值，以及涡轮部分部件温度的测量或估计，以及（ii） 第二需求信号，以及前端间隙的测量或估计。

    Gas turbine engine flow control
    15.
    发明授权
    Gas turbine engine flow control 有权

    公开(公告)号：US11466628B2

    公开(公告)日：2022-10-11

    申请号：US16945061

    申请日：2020-07-31

    Applicant: ROLLS-ROYCE plc

    Inventor： Cerith Davies ,  Marko Bacic

    IPC: F02C9/54 ,  F02C3/06 ,  F02C7/36

    Abstract: A method of controlling a gas turbine engine including receiving an instantaneous thrust demand for current operation of the engine, determining the inlet flow rate and/or the pressure ratio within the compressor of the engine and determining whether the inlet flow rate and/or the pressure ratio match the working line for the compressor. The angle of one or more vane of the compressor is adjusted according to a closed control loop if the inlet flow rate and/or pressure ratio lie outside said desired range in order to adjust the inlet inflow rate and/or pressure ratio to meet the working line. The fuel flow to the engine combustor is adjusted concurrently in order to meet the thrust demand.

    Control system for a cabin blower system
    16.
    发明授权
    Control system for a cabin blower system 有权

    公开(公告)号：US10926882B2

    公开(公告)日：2021-02-23

    申请号：US15704831

    申请日：2017-09-14

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko Bacic ,  Benjamin J. Sellers ,  Rory D. Stieger

    IPC: B64D13/04 ,  F04D27/02 ,  B64D27/16 ,  F02C7/32 ,  F04D25/02 ,  F04D27/00 ,  B64D13/06

    Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

    Turbine tip clearance
    17.
    发明授权
    Turbine tip clearance 有权

    公开(公告)号：US10890083B2

    公开(公告)日：2021-01-12

    申请号：US15133883

    申请日：2016-04-20

    Applicant: ROLLS-ROYCE plc

    Inventor： Arthur Laurence Rowe ,  Marko Bacic

    IPC: F01D11/24 ,  F01D21/12 ,  F01D21/14

    Abstract: A method of controlling turbine tip clearance includes measuring turbine speed; measuring turbine temperature; measuring parameters indicative of current operating conditions; determining limits for the turbine speed and turbine temperature; calculating target tip clearance from the turbine speed, turbine temperature and parameters, to optimise turbine efficiency within the turbine speed and turbine temperature limits; and controlling turbine tip clearance apparatus to the calculated target tip clearance.

    Clearance control
    19.
    发明授权
    Clearance control 有权

    公开(公告)号：US09719365B2

    公开(公告)日：2017-08-01

    申请号：US14031695

    申请日：2013-09-19

    Applicant: ROLLS-ROYCE PLC

    Inventor： Marko Bacic ,  Timothy John Scanlon ,  Ronald William Daniel

    IPC: F01D11/10 ,  F01D11/24 ,  F01D11/06 ,  F01D11/20

    CPC classification number: F01D11/10 ,  F01D11/06 ,  F01D11/20 ,  F01D11/24 ,  F05D2260/16 ,  F05D2270/172 ,  F05D2270/62

    Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

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