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公开(公告)号：US07186090B2
公开(公告)日：2007-03-06
申请号：US10986162
申请日：2004-11-12
申请人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
发明人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 一种具有基本上符合表中列出的X，Y和Z的笛卡尔坐标值的公称轮廓的制品。 该表从由表1S-16S，1R-17R和IGV组成的表格中选择。 其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，以每英寸的距离Z限定翼型轮廓部分。 Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。
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2.发明授权Method and apparatus for detecting and compensating for compressor surge in a gas turbine using remote monitoring and diagnostics 有权用于使用远程监控和诊断来检测和补偿燃气轮机中的压缩机喘振的方法和装置公开(公告)号：US06438484B1
公开(公告)日：2002-08-20
申请号：US09863021
申请日：2001-05-23
申请人： Philip Lynn Andrew , Chung-hei Simon Yeung , John David Stampfli , Joseph Anthony Cotroneo , Steven Mark Schirle , James Michael Hill
发明人： Philip Lynn Andrew , Chung-hei Simon Yeung , John David Stampfli , Joseph Anthony Cotroneo , Steven Mark Schirle , James Michael Hill
IPC分类号： G06F1900
CPC分类号： F04D27/02 , F05D2270/101
摘要： A method is disclosed for monitoring and controlling a compressor including (a) monitoring at least one compressor parameter; (b) storing data indicative of the monitored parameter in a database system; (c) processing the collected data using a stall precursor detection algorithm to determine a stall precursor; (d) comparing the stall precursor with at least one of a corresponding average compressor value, and a corresponding unit specific value to determine the level of compressor operability, and (e) if the stall precursor varies from at least one of the average compressor value and the unit specific value, performing corrective actions to vary the level of compressor operability to prevent a surge condition.
摘要翻译： 公开了一种用于监测和控制压缩机的方法，包括（a）监测至少一个压缩机参数; （b）将指示所监视的参数的数据存储在数据库系统中; （c）使用失速前体检测算法处理所收集的数据以确定失速前体; （d）将所述失速前体与对应的平均压缩机值和对应的单位特定值中的至少一个进行比较以确定压缩机可操作性的水平，以及（e）如果所述失速前体从平均压缩机值 和单位特定值，执行校正动作以改变压缩机可操作性的水平以防止浪涌状况。
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公开(公告)号：US07467926B2
公开(公告)日：2008-12-23
申请号：US11449770
申请日：2006-06-09
IPC分类号： F01D9/00
CPC分类号： F04D29/544 , Y10S416/02
摘要： Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.
摘要翻译： 用于压缩机的第十级定子叶片包括基本上按照表I中以英寸列出的x，Y和Z的笛卡尔坐标值的翼型，其中Z坐标值是垂直于距离压缩机中心线的半径的平面的垂直距离，以及 包含在翼型的径向空气动力学部分处的X，Y平面中从零开始的Z值的X和Y值。 X和Y是在每个距离Z处定义翼型轮廓的坐标值.X，Y和Z值可以被缩放以为每个定子叶片提供放大或缩小的翼型部分。
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公开(公告)号：US06226974B1
公开(公告)日：2001-05-08
申请号：US09339956
申请日：1999-06-25
申请人： Philip Lynn Andrew , Paul Thomas Marks , Daniel Robert Dwyer , John David Stampfli , Joseph Anthony Cotroneo , Harold Edward Miller , Ronald Richard Wesorick
发明人： Philip Lynn Andrew , Paul Thomas Marks , Daniel Robert Dwyer , John David Stampfli , Joseph Anthony Cotroneo , Harold Edward Miller , Ronald Richard Wesorick
IPC分类号： F02C1310
CPC分类号： F02C9/28 , F04D27/02 , F05D2270/05 , Y02E20/16
摘要： A gas turbine operational strategy is provided for the optimization of ISO-Day rated performance. The invention is realized by setting the nominal operating line equal to or slightly below the operating limit line, so that ISO full load performance is maximized. Thus, the first stage turbine nozzle throat area is sized such that, without inlet bleed heat addition, and at Base-Load pressure ratio and firing temperature, the compressor operates within its operational limits on a ISO day. As ambient conditions change, levels of inlet bleed heat and firing temperature are controlled and the inlet guide vane angle is set whereby the nominal operating line is equal to or slightly below the operating limit line.
摘要翻译： 提供燃气轮机操作策略，以优化ISO-Day的性能。 本发明通过将标称操作线设置为等于或稍低于操作限制线来实现，使得ISO满载性能最大化。 因此，第一级涡轮喷嘴喉部区域的尺寸使得在没有入口放热加入的情况下，并且在基本负载压力比和烧制温度下，压缩机在ISO日的运行限度内运行。 随着环境条件的变化，入口排放热量和燃烧温度的水平被控制，并且入口导向叶片角度被设定，由此标称操作线等于或略低于操作极限线。
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5.发明授权公开(公告)号：US06220086B1
公开(公告)日：2001-04-24
申请号：US09169007
申请日：1998-10-09
IPC分类号： F02C700
CPC分类号： F04D27/001 , F02C7/057 , F02C9/16 , F05D2270/101
摘要： The surge pressure ratio of a compressor is determined by transiently reducing the inlet flow to the compressor to increase the compressor pressure ratio sufficiently to produce the surge pressure ratio. The reduction in flow of fluid is maintained for a time period insufficient to exceed the exhaust gas temperature limit for the turbine. The area of the first-stage nozzle of the turbine is reduced and the inlet flow to the compressor is reduced to a steady state to achieve pressure ratios, in close proximity to the surge line. By transiently further reducing the inlet flow to the compressor and then increasing the inlet flow back to the steady-state condition, the surge pressure ratio can be obtained without exceeding machine operational limits.
摘要翻译： 压缩机的喘振压力比通过瞬时减小到压缩机的入口流量来确定，以充分提高压缩机压力比以产生浪涌压力比。 流体的流动减少维持不到超过涡轮机废气温度极限的时间。 涡轮机的第一级喷嘴的面积减小，并且到达压缩机的入口流量减小到稳定状态，以实现紧靠喘振线路的压力比。 通过暂时进一步减小进入压缩机的入口流量，然后将入口流量增加回稳定状态，可以在不超过机器操作限制的情况下获得喘振压力比。
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6.发明申请公开(公告)号：US20100269481A1
公开(公告)日：2010-10-28
申请号：US12428769
申请日：2009-04-23
IPC分类号： F02C9/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/101
摘要： Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.
摘要翻译： 提供了用于向涡轮机部件提供喘振保护的系统和方法。 可以为涡轮机部件确定浪涌保护极限。 可以接收与涡轮机部件的操作相关联的一个或多个测量，并且将其提供给执行以预测涡轮机部件的操作状态的循环模型。 可以至少部分地基于所接收的一个或多个测量来调整涡轮机部件的预测操作状态。 浪涌保护极限可以根据调整后的涡轮机部件的运行状况进行调整。
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公开(公告)号：US06574584B2
公开(公告)日：2003-06-03
申请号：US09732811
申请日：2000-12-11
IPC分类号： G06F1500
CPC分类号： F04D27/02
摘要： A method is provided for evaluating stall/surge margin of a machine of interest. The method includes identifying a vital factor where each the vital factors corresponds to operation of the machine of interest. Raw data relating to the vital factor is provided. A contribution of the vital factor to the stall/surge margin is determined from at least the provided raw data. The contribution of the vital factor to the stall/surge margin is statistically analyzed. A stall/surge margin is allocated based on the statistical analysis of the contribution of the vital factor. An operating limit line is defined based on the allocation of the stall/surge margin.
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8.发明授权公开(公告)号：US08322145B2
公开(公告)日：2012-12-04
申请号：US12428769
申请日：2009-04-23
IPC分类号： F02C7/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/101
摘要： Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.
摘要翻译： 提供了用于向涡轮机部件提供喘振保护的系统和方法。 可以为涡轮机部件确定浪涌保护极限。 可以接收与涡轮机部件的操作相关联的一个或多个测量，并且将其提供给执行以预测涡轮机部件的操作状态的循环模型。 可以至少部分地基于所接收的一个或多个测量来调整涡轮机部件的预测操作状态。 浪涌保护极限可以根据调整后的涡轮机部件的运行状况进行调整。
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公开(公告)号：US20070286718A1
公开(公告)日：2007-12-13
申请号：US11449770
申请日：2006-06-09
IPC分类号： F01D9/00
CPC分类号： F04D29/544 , Y10S416/02
摘要： Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.
摘要翻译： 用于压缩机的第十级定子叶片包括基本上按照表I中以英寸列出的x，Y和Z的笛卡尔坐标值的翼型，其中Z坐标值是垂直于距离压缩机中心线的半径的平面的垂直距离，以及 包含在翼型的径向空气动力学部分处的X，Y平面中从零开始的Z值的X和Y值。 X和Y是在每个距离Z处定义翼型轮廓的坐标值.X，Y和Z值可以被缩放以为每个定子叶片提供放大或缩小的翼型部分。
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10.发明授权Method of air-flow measurement and active operating limit line management for compressor surge avoidance 有权空气流量测量方法和压缩机浪涌回避的主动运行限制线路管理公开(公告)号：US06364602B1
公开(公告)日：2002-04-02
申请号：US09478523
申请日：2000-01-06
IPC分类号： F04D1714
CPC分类号： F01D25/007 , F01D21/10 , F02C7/30 , F02C9/28 , F04D27/02
摘要： A transfer function between the inlet air-flow consumed by a Gas Turbine engine, and the engine parameters of speed, pressure ratio, and Inlet Guide Vane (IGV) angle is described. An active compressor Operating Limit Line (OLL) management strategy that leverages this improved flow measurement transfer function is also described. The improved flow measurement capability afforded by the transfer function permits a deterioration in flow rate caused by compressor fouling to be detected. Using the deterioration in flow rate as a proxy for compressor fouling, a degraded surge boundary associated with fouling can be predicted, using a transfer function between degradation of air-flow along operating line and degradation of surge line. In combination, the inventive improvements in flow measurement and operating line management afford added compressor surge protection across the operating range, while permitting the attainment of elevated pressure ratios associated with high thermodynamic efficiency and output.
摘要翻译： 描述了燃气轮机发动机消耗的入口气流与速度，压力比和进气导叶（IGV）角度的发动机参数之间的传递函数。 还描述了利用这种改进的流量测量传递功能的主动压缩机操作限制线（OLL）管理策略。 通过传递函数提供的改进的流量测量能力允许检测到由压缩机污垢引起的流量的劣化。 使用流量的劣化作为压缩机污染的代理，可以使用在沿着操作线的气流的劣化和喘振线的劣化之间的传递函数来预测与结垢相关的劣化的浪涌边界。 结合起来，本发明的流量测量和操作管线管理的改进在整个操作范围内提供了增加的压缩机喘振保护，同时允许获得与高热力学效率和输出相关联的升高的压力比。
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