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    Dynamic and automatic tuning of a gas turbine engine using exhaust temperature and inlet guide vane angle
    4.
    发明授权
    Dynamic and automatic tuning of a gas turbine engine using exhaust temperature and inlet guide vane angle 有权
    使用排气温度和入口导叶角度对燃气涡轮发动机进行动态和自动调谐

    公开(公告)号：US09328669B2

    公开(公告)日：2016-05-03

    申请号：US14213263

    申请日：2014-03-14

    申请人： Hany Rizkalla ,  Donald Gauthier ,  Peter John Stuttaford ,  Sumit Soni

    发明人： Hany Rizkalla ,  Donald Gauthier ,  Peter John Stuttaford ,  Sumit Soni

    IPC分类号： F02C9/22 ,  G05B15/02 ,  F02C9/00 ,  F02C9/48

    CPC分类号： F02C9/22 ,  F02C9/00 ,  F02C9/48 ,  F05D2260/964 ,  G05B15/02

    摘要： Methods and systems are provided for dynamically auto-tuning a gas turbine engine. Initially, parameters of the gas turbine engine are monitored to determine that they are within predefined upper and lower limits such that a margin exists. A first incremental adjustment of an inlet guide vane (IGV) angle is performed. If the monitored parameters are still within the predefined upper and lower limits, a second incremental adjustment of the IGV angle is performed. It is determined that the monitored parameters are still within the predefined upper and lower limits. Additionally, it is determined that a predefined value of the IGV angle has been reached such that the IGV angle is not to be further increased or decreased.

    摘要翻译： 提供了用于动态自动调节燃气涡轮发动机的方法和系统。 首先，监测燃气涡轮发动机的参数以确定它们在预定义的上限和下限内，使得存在余量。 执行入口导叶（IGV）角度的第一增量调节。 如果监视的参数仍处于预定义的上限和下限范围内，则执行IGV角度的第二增量调整。 确定监控的参数仍然在预定义的上限和下限之内。 此外，确定已经达到了IGV角度的预定值，使得IGV角度不被进一步增加或减小。

    Stabilizing A Gas Turbine Engine Via Incremental Tuning During Transients
    5.
    发明申请
    Stabilizing A Gas Turbine Engine Via Incremental Tuning During Transients 有权
    在瞬态期间通过增量调节来稳定燃气轮机发动机

    公开(公告)号：US20140200721A1

    公开(公告)日：2014-07-17

    申请号：US14213122

    申请日：2014-03-14

    申请人： Hany Rizkalla ,  Donald Gauthier ,  Sumit Soni ,  Peter John Stuttaford

    发明人： Hany Rizkalla ,  Donald Gauthier ,  Sumit Soni ,  Peter John Stuttaford

    IPC分类号： G05D7/06

    CPC分类号： G05D7/0676 ,  F02C7/228 ,  F02C9/28 ,  F02C9/34 ,  F05D2270/082 ,  F05D2270/301 ,  F05D2270/31 ,  F23N2041/20 ,  F23R3/343 ,  F23R3/346

    摘要： Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored. A stability bias is applied to the system if either the state is changing or if lean blowout is imminent until the lean blowout is no longer determined to be imminent. The stability bias monitors operating conditions of the gas turbine engine and determines when one of the operating conditions has overcome a threshold value. Once a threshold value is overcome, a fuel flow fraction is adjusted by a predefined increment. The application of the stability bias is gradually terminated once it is determined that the lean blowout is no longer imminent.

    摘要翻译： 提供了用于在诸如燃气涡轮发动机的状态正在改变的过渡期间自动调节燃气涡轮发动机的燃烧器的方法和系统。 一旦确定了燃气涡轮发动机的状态是否正在改变，则确定是否迫在眉睫，这是基于监视的基础条件。 如果状态正在改变，或者如果精密喷吹即将到来，直到不再确定即将来临的稀薄喷射，系统就会施加稳定偏差。 稳定偏差监测燃气涡轮发动机的运行状况，并确定其中一个运行条件是否克服了阈值。 一旦克服了阈值，则燃料流量分数被调整预定的增量。 一旦确定稀薄井喷不再迫在眉睫，稳定性偏差的应用逐渐终止。

    AUTOMATED EXTENDED TURNDOWN OF A GAS TURBINE ENGINE COMBINED WITH INCREMENTAL TUNING TO MAINTAIN EMISSIONS AND DYNAMICS
    6.
    发明申请
    AUTOMATED EXTENDED TURNDOWN OF A GAS TURBINE ENGINE COMBINED WITH INCREMENTAL TUNING TO MAINTAIN EMISSIONS AND DYNAMICS 有权
    气动涡轮发动机自动延伸的涡轮增压器结合增量调节维持排放和动力学

    公开(公告)号：US20150159563A1

    公开(公告)日：2015-06-11

    申请号：US14610760

    申请日：2015-01-30

    申请人： Sumit Soni ,  Nicolas Roger Demougeot ,  Peter John Stuttaford

    发明人： Sumit Soni ,  Nicolas Roger Demougeot ,  Peter John Stuttaford

    IPC分类号： F02C9/28 ,  F02C7/22

    CPC分类号： F02C9/28 ,  F02C7/228 ,  F02C9/34 ,  F05D2260/80 ,  F05D2270/05 ,  F05D2270/082 ,  F05D2270/301 ,  F05D2270/31 ,  F23N2041/20 ,  F23R3/343 ,  F23R3/346 ,  F23R2900/00013

    摘要： An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine. Additionally, a method of automated extended turndown of a GT engine to find a minimum load is provided.

    摘要翻译： 提供了一种自动调谐控制器和调谐过程，用于相对于预定的上限来测量和调整GT发动机的燃烧动态和排放。 最初，调整过程包括监测多个燃烧器的燃烧动力学和多个条件下的排放。 在确定一个或多个条件超过预定上限时，分配到发动机上的所有燃烧器上的燃料回路的燃料流量被调节预定量。 控制系统继续监测燃烧动力学，并且将燃料流量分开递归地调整预定量，直到燃烧动力学和/或排放物在GT发动机的规定范围内运行。 另外，提供了GT发动机的自动扩展调节以找到最小负载的方法。

    Apparatus for adjusting combustor cycle
    8.
    发明授权
    Apparatus for adjusting combustor cycle 有权
    用于调节燃烧器循环的装置

    公开(公告)号：US06609362B2

    公开(公告)日：2003-08-26

    申请号：US09903641

    申请日：2001-07-13

    申请人： Peter John Stuttaford ,  Aleksandar Kojovic

    发明人： Peter John Stuttaford ,  Aleksandar Kojovic

    IPC分类号： F23R306

    CPC分类号： F23R3/005 ,  F02C7/08 ,  F05D2260/201 ,  F23R3/26 ,  F23R2900/00016 ,  F23R2900/03044

    摘要： A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine. In an embodiment of the present invention, the changing of the geometry of the air flow passage by changing the number and size of perforations in an impingement cooling skin so that with minimal changes the impingement cooling skin serves duel purposes both as a cooling device for cooling the combustor wall and as a valve means for combustor cycle air flow adjustment, which makes the method simple and economical.

    摘要翻译： 根据本发明的用于燃气涡轮发动机的燃烧器循环空气流量调节方法解决了燃烧器中火焰温度较高的问题，从而当使用热回收空气流循环来增加压缩空气时影响排放水平 温度。 在低排放燃烧器中，这种影响是严重的，因为排放水平显着取决于主燃烧区火焰温度。 本发明的方法包括改变空气流路的几何形状，从而改变用于燃烧的空气质量流与冷却空气质量流之间的总空气质量流的分布，以确保火焰温度在 无论燃气涡轮发动机是否被制造成作为简单的气流循环发动机或作为热回收空气流循环发动机来操作，燃烧器的主燃烧区域保持基本相同。 在本发明的一个实施例中，通过改变冲击冷却皮肤中的穿孔的数量和尺寸来改变空气流动通道的几何形状，使得在最小变化的情况下，冲击冷却皮肤作为用于冷却的冷却装置的决斗 燃烧器壁和用于燃烧器循环空气流量调节的阀装置，这使得该方法简单和经济。