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17 条记录 (耗时 0.008 秒)

    Aircraft gas turbine engine blade tip clearance control
    3.
    发明公开
    Aircraft gas turbine engine blade tip clearance control 审中-公开
    Schaufelspitzen-Abstandssteuerungfüreinen Flugzeuggasturbenenotors

    公开(公告)号：EP2025878A2

    公开(公告)日：2009-02-18

    申请号：EP08161497.6

    申请日：2008-07-30

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Hershey, John Erik ,  Osborn, Brock Estel ,  Gardner, Donald Lee ,  Ruiz, Rafael Jose ,  Herron, William Lee

    IPC分类号： F01D11/02 ,  F01D11/20

    CPC分类号： F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

    摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

    摘要翻译： 一种方法和系统预计在改变发动机转速的发动机命令之前和之前调整旋转的飞机燃气涡轮发动机叶片尖端和周围的护罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调节顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞行器机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定什么时候开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或在其他飞行器上的其它喷气发动机的操作经验和/或操作经验。

    Gas turbine generator having reserve capacity controller
    4.
    发明公开
    Gas turbine generator having reserve capacity controller 有权
    Gasturbinenkraftzentrale mit Regelung derReservekapazität

    公开(公告)号：EP1036924A2

    公开(公告)日：2000-09-20

    申请号：EP00302117.7

    申请日：2000-03-15

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Rowen, William Irwin ,  Anand, Raj Kumar ,  Wooding, Richard John

    IPC分类号： F02C9/54

    CPC分类号： F02C9/54 ,  F05D2270/70

    摘要： A controller (200) is disclosed that operates a gas turbine such that a desired reserve power capacity is maintained. The inlet guide vane angle (210) of the compressor is applied as an indicator of the reserve capacity (214) of the gas turbine. The actual inlet guide vane angle (210) is continuously compared to an intended inlet guide vane angle that corresponds to a desired reserve capacity (214). A controller (200) adjusts the fuel flow to the gas turbine to adjust the turbine output power and thereby maintain the actual inlet guide vane angle (210) at the intended value corresponding to the desired reserve capacity.

    摘要翻译： 公开了一种控制器（200），其操作燃气涡轮机使得保持期望的备用电力容量。 压缩机的入口引导叶片角（210）作为燃气轮机的储备容量（214）的指示器。 实际的入口引导叶片角度（210）与对应于期望的储备容量（214）的预期入口导叶角度连续地进行比较。 控制器（200）调节到燃气轮机的燃料流量，以调整涡轮机输出功率，从而将实际的入口引导叶片角度（210）维持在对应于期望的储备容量的预定值。

    Systems and Methods for Controlling Compressor Extraction Cooling
    7.
    发明公开
    Systems and Methods for Controlling Compressor Extraction Cooling 有权
    Systeme und Verfahren zur Steuerung derVerdichterabzugskühlung

    公开(公告)号：EP2239438A2

    公开(公告)日：2010-10-13

    申请号：EP10158225.2

    申请日：2010-03-29

    申请人： General Electric Company

    发明人： Davis, Jr., Lewis Berkley ,  Henahan, James

    IPC分类号： F02C7/16 ,  F02C9/18 ,  F02C9/28

    CPC分类号： F02C7/16 ,  F01D25/12 ,  F02C7/18 ,  F02C9/18 ,  F02C9/28 ,  F05D2270/30 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/70

    摘要： Embodiments of methods and apparatus for providing compressor extraction cooling are provided. According to one example embodiment, a method is disclosed for controlling compressor extraction cooling. The method can include providing a cooling medium (122). The method can include extracting air (114) from a compressor (102) associated with a gas turbine (100). The method can also include introducing the cooling medium (122) to the compressor extraction air (114), wherein the compressor extraction air (114) is cooled by the cooling medium (122) prior to or during introduction to the turbine (104) section. Furthermore, method can include selectively controlling at least one of the compressor extraction air (114) or the cooling medium (122) based at least in part on a characteristic associated with the gas turbine (100).

    摘要翻译： 提供了用于提供压缩机提取冷却的方法和装置的实施例。 根据一个示例性实施例，公开了一种用于控制压缩机提取冷却的方法。 该方法可以包括提供冷却介质（122）。 该方法可以包括从与燃气轮机（100）相关联的压缩机（102）中提取空气（114）。 该方法还可以包括将冷却介质（122）引入压缩机抽出空气（114），其中压缩机抽出空气（114）在引入涡轮机（104）部分之前或期间由冷却介质（122）冷却 。 此外，方法可以包括至少部分地基于与燃气涡轮机（100）相关联的特性来选择性地控制压缩机抽出空气（114）或冷却介质（122）中的至少一个。

    Turbine engine arrangements and control
    8.
    发明公开
    Turbine engine arrangements and control 审中-公开
    Turbinentriebwerksanordnungen und Regelung

    公开(公告)号：EP1788223A2

    公开(公告)日：2007-05-23

    申请号：EP06255333.4

    申请日：2006-10-17

    申请人： Rolls-Royce plc

    发明人： Zewde, Netsebrak Tadesse ,  Rowe, Arthur Laurance

    IPC分类号： F02C9/18

    CPC分类号： F02C9/18 ,  F05D2270/023 ,  F05D2270/06 ,  F05D2270/301 ,  F05D2270/64 ,  F05D2270/70

    摘要： It is known that power is normally extracted within a gas turbine engine from a shaft in order to drive auxiliary devices such as electrical power generators. With high extraction rates from such shafts there is mismatching in rotational speeds between the shafts which must be adjusted through leakage taken from valves (8,9). By measuring parameters and in particular pressure at a number of positions or parts within an engine arrangement (1) and comparing those parameters either through ratios or directly with reference values a controller can be configured in order to choose the correct sequence and scheduling of the valves (8,9) opening to balance shaft speed. In such circumstances more efficient operation of the engine arrangement can be achieved over a wider range of engine speeds including idling.

    摘要翻译： 众所周知，通常在燃气涡轮发动机内从轴提取动力，以驱动诸如发电机之类的辅助装置。 由于这种轴的提取速度很高，轴之间的转速不匹配，必须通过从阀（8,9）获取的泄漏来调节。 通过测量参数，特别是在发动机装置（1）内的多个位置或部件上的压力，并且通过比例或直接与参考值比较这些参数，可以配置控制器以便选择阀的正确顺序和调度 （8,9）打开以平衡轴速度。 在这种情况下，可以在更宽范围的发动机速度（包括空转）下实现发动机装置的更有效的操作。

    Turbine performance diagnositic system and methods
    10.
    发明公开
    Turbine performance diagnositic system and methods 有权
    System zur Diagnose der Turbinenleistung und Verfahren

    公开(公告)号：EP2458178A2

    公开(公告)日：2012-05-30

    申请号：EP11190153.4

    申请日：2011-11-22

    申请人： General Electric Company

    发明人： Panley, Achalesh Kumar ,  Nanda, Subrat ,  Mazzaro, Maria Cecilia ,  Talukdar, Atanu

    IPC分类号： F02C9/00

    CPC分类号： F02C9/00 ,  F05D2260/80 ,  F05D2270/44 ,  F05D2270/70 ,  F05D2270/71 ,  G06N7/005

    摘要： A turbine performance diagnostic system (50) creates a performance report for one or more turbines (60) and includes an assessment module that receives operating data from at least one turbine and produces a performance report (70) from the operating data. The assessment module includes a change detection module (308) configured to determine when at least one parameter has changed beyond an associated threshold and generate an alarm and a root cause analyzer (312) coupled to the change detection module that predicts a root cause of the alarm utilizing a Bayesian Belief Network (BBN). The performance report includes an indication of the predicted root cause.

    摘要翻译： 涡轮性能诊断系统（50）为一个或多个涡轮机（60）创建性能报告，并且包括评估模块，其从至少一个涡轮机接收操作数据，并从操作数据产生性能报告（70）。 评估模块包括改变检测模块（308），其被配置为确定何时至少一个参数已经改变超过相关联的阈值并且生成报警和耦合到所述变化检测模块的根本原因分析器（312），所述变化检测模块预测所述 利用贝叶斯信仰网络（BBN）进行报警。 绩效报告包括预测根本原因的指示。