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21.发明授权Selecting and applying to fuel-flow splits bias values to correct for elevated inlet air humidity 有权选择和应用燃料流分流偏置值以校正进气空气湿度的升高公开(公告)号：US08566001B2
公开(公告)日：2013-10-22
申请号：US13087048
申请日：2011-04-14
CPC分类号： F02C7/1435 , F02C7/22 , F02C7/228 , F02C9/28 , F05D2270/083 , F05D2270/16 , F05D2270/708
摘要： Methods for controlling a gas turbine engine are provided, where a compressor inlet temperature, ambient temperature, and relative humidity are measured. Utilizing these measurements, it is first determined whether an evaporation cooler is actively importing water content into inlet air entering the compressor. This determination is based on whether the inlet air is substantially cooler than the ambient temperature. If so, an EC correction factor is added to an inlet air temperature value (CTIM) and set as an air temperature parameter (INLETIM). Second, it is determined whether the relative humidity is greater than a predefined threshold. If so, a relative humidity (RH) correction factor is added to CTIM and set as the INLETIM. Next, the INLETIM and TTRF are located in a look-up table, and a bias value corresponding to these inputs is identified. The fuel-flow for a fuel circuit is adjusted according to the identified bias value.
摘要翻译： 提供了用于控制燃气涡轮发动机的方法，其中测量压缩机入口温度，环境温度和相对湿度。 利用这些测量，首先确定蒸发冷却器是否积极地将水分输入到进入压缩机的入口空气中。 该确定基于入口空气是否比环境温度基本上更冷。 如果是这样，将EC校正因子加到入口空气温度值（CTIM），并设置为空气温度参数（INLETIM）。 其次，确定相对湿度是否大于预定阈值。 如果是这样，将相对湿度（RH）校正因子添加到CTIM并设置为INLETIM。 接下来，INLETIM和TTRF位于查找表中，并且识别与这些输入相对应的偏置值。 根据所识别的偏置值来调节燃料回路的燃料流量。
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公开(公告)号：US20120085099A1
公开(公告)日：2012-04-12
申请号：US12901084
申请日：2010-10-08
CPC分类号： F01D9/023 , F01D11/005 , F23R3/02 , F23R3/26 , F23R2900/00012
摘要： A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.
摘要翻译： 公开了一种用于调节具有位于燃烧系统和涡轮机入口之间的多个密封件的燃气轮机燃烧系统的系统和方法。 该系统和方法提供允许预定量的压缩空气绕过燃烧系统并进入涡轮机以控制燃烧系统的排放和动力学的方式。 密封件包含多个孔，用于测量通过其中的气流并且被定位成使得它们可以从发动机移除并被修改以增加或减少通过其中的空气量。
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公开(公告)号：US20060260316A1
公开(公告)日：2006-11-23
申请号：US10908682
申请日：2005-05-23
申请人： Peter Stuttaford
发明人： Peter Stuttaford
IPC分类号： F23R3/30
CPC分类号： F23R3/286 , F23D14/82 , F23L7/00 , F23L2900/07002 , F23R3/24
摘要： A gas turbine combustor having improved flashback margin is disclosed. Multiple embodiments of the present invention are disclosed including combustors having a single premix chamber as well as multiple premix chambers. Flashback margin is increased for the combustor by incorporating a means for introducing an inert gas, such as nitrogen, into the premix chamber(s) at the region proximate the boundary layer to purge the boundary layer of combustible mixture, thereby ensuring that no combustion reaction occurs in the boundary layer.
摘要翻译： 公开了一种具有改善的闪回余量的燃气轮机燃烧器。 公开了本发明的多个实施例，包括具有单个预混合室的燃烧器以及多个预混室。 通过在靠近边界层的区域引入惰性气体（例如氮气）到预混合室中来提高燃烧器的闪回余量，以清除可燃混合物的边界层，从而确保没有燃烧反应 发生在边界层。
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公开(公告)号：US20060016198A1
公开(公告)日：2006-01-26
申请号：US10897785
申请日：2004-07-23
申请人： Peter Stuttaford , Jon Glende , Peter So , Lee Rosen , Khalid Oumejjoud
发明人： Peter Stuttaford , Jon Glende , Peter So , Lee Rosen , Khalid Oumejjoud
IPC分类号： F02C7/22
摘要： A fuel supply system and method thereof that utilizes an off-gas in addition to the primary fuel to lower the emissions of a gas turbine combustion system is disclosed. The fuel supply system apparatus comprises a fuel gas supply conduit and an off-gas supply conduit in fluid communication with the fuel gas supply conduit such that the flow of an off-gas to the fuel gas supply conduit can be regulated as required by the operator to the desired fuel nozzle(s). The fuel gas supply preferably operates with natural gas and the off-gas supply preferably comprises the constituents hydrogen and methane.
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公开(公告)号：US20050284442A1
公开(公告)日：2005-12-29
申请号：US10880073
申请日：2004-06-29
申请人： Peter Stuttaford , John Henriquez , Paul Economo
发明人： Peter Stuttaford , John Henriquez , Paul Economo
CPC分类号： F02C7/266 , F05D2210/10 , F05D2210/11 , F05D2210/12
摘要： An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.
摘要翻译： 公开了一种具有改进燃气轮机燃烧器可靠性的点火系统。 点火系统包括外壳，其具有至少一个燃料通道和延伸穿过的电极，形成大致环形的通道，用于冷却空气以通过混合室。 燃料和空气在混合室中混合以形成被电极点燃的可燃混合物。 外壳还包括多个空气旋转孔，以有效地冷却混合室的壁，并提供改进的火焰稳定性。
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公开(公告)号：US06915636B2
公开(公告)日：2005-07-12
申请号：US10465096
申请日：2003-06-19
CPC分类号： F23L7/002 , F23D2209/30 , F23D2214/00 , F23D2900/00008 , F23D2900/14004 , F23R3/286 , F23R3/36
摘要： A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly and simplify fuel nozzle manufacturing.
摘要翻译： 公开了一种用于燃气轮机燃烧器的双燃料预混喷嘴和操作方法。 双燃料预混喷嘴利用一种翅片组件，其包括多个径向延伸的翅片，用于喷射气体燃料和压缩空气，以便提供更均匀的注射模式和均匀的混合物。 预混合燃料喷嘴包括多个同轴通道，其向翅片组件提供气体燃料和压缩空气。 当处于液体燃料运行时，气体回路用压缩空气吹扫，液体燃料和水通过同轴通道到达双燃料预混燃料喷嘴的末端，在那里它们将液体燃料和水注入到二次燃烧室中。 替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加气体燃料喷射区域。 公开了第二替代实施例，其重新配置喷射器组件和燃料喷射位置以最小化喷射器组件处的流动阻塞问题并简化燃料喷嘴制造。
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公开(公告)号：US06536201B2
公开(公告)日：2003-03-25
申请号：US09733051
申请日：2000-12-11
申请人： Peter Stuttaford , Bernhard Fischer , David Edwin Cowburn , Saeid Oskooei , Michael Andrew Fryer , Aleksandar Kojovic , Jeffrey Scott Acton
发明人： Peter Stuttaford , Bernhard Fischer , David Edwin Cowburn , Saeid Oskooei , Michael Andrew Fryer , Aleksandar Kojovic , Jeffrey Scott Acton
IPC分类号： F02G0300
CPC分类号： F23R3/005 , F01D5/00 , F01D25/26 , F02C7/18 , F05D2260/201 , F23R2900/03044
摘要： The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling. Moreover, all the exhaust combustor backside cooling air must be used for turbine cooling and is never ingested into the combustion chamber, thereby avoiding negatively affecting the engine combustion emissions.
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公开(公告)号：US06442939B1
公开(公告)日：2002-09-03
申请号：US09742009
申请日：2000-12-22
IPC分类号： F02C300
摘要： A premixer for an industrial type gas turbine engine wherein the premixer includes a diffuser ring assembly made up of annular concentric rings and upstream of the diffuser ring assembly in the airflow path is a corresponding fuel manifold ring assembly, each ring in the manifold ring assembly corresponding to a passageway formed between the diffuser rings, and each manifold ring includes a downstream channel for feeding the fuel to the air as the air passes by the ring.
摘要翻译： 一种用于工业型燃气涡轮发动机的预混合器，其中预混合器包括由环形同心环构成的扩散器环组件，并且在气流路径中的扩散器环组件的上游是对应的燃料歧管环组件，歧管环组件中的每个环对应于 到形成在扩散器环之间的通道，并且每个歧管环包括用于当空气通过环时将燃料供给到空气的下游通道。
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公开(公告)号：US08731797B2
公开(公告)日：2014-05-20
申请号：US13086978
申请日：2011-04-14
IPC分类号： B60T7/12
摘要： A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine, and for dynamically tuning the GT engine as a function of changes to the monitored fuel properties. Initially, readings are taken from the GT engine during a reference calibration, or commissioning, and utilized to calculate an initial-pressure-drop reference value. The tuning process during commercial operation takes post-calibration readings from the GT engine to calculate a fuel property parameter, which represents a heating value of the fuel. Specifically, the fuel property parameter is calculated by deriving a corrected-pressure-drop dynamic value as a function of pressure and temperature readings of the fuel at a point upstream of a combustor and pressure drops across fuel nozzles that introduce the fuel into the combustor, and solving a ratio of the dynamic value and the reference value.
摘要翻译： 提供了一种调节过程，用于监测由燃气轮机（GT）发动机消耗的燃料的燃料性质，并且用于根据对所监测的燃料性质的变化来动态调节GT发动机。 最初，在参考校准或调试期间从GT发动机获取读数，并用于计算初始压降参考值。 商业运行过程中的调整过程需要GT发动机的后校准读数，以计算燃料特性参数，该参数代表燃料的热值。 具体地说，燃料特性参数通过导出作为燃料在燃烧器上游一点上燃料的压力和温度读数的函数的校正压降动态值来计算，并且将燃料引入燃烧器的燃料喷嘴之间的压力下降， 并求解动态值和参考值的比值。
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公开(公告)号：US08136359B2
公开(公告)日：2012-03-20
申请号：US11953162
申请日：2007-12-10
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23D2900/00008 , F23R2900/00001 , F23R2900/00005
摘要： Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
摘要翻译： 公开了用于使燃气轮机燃烧器的燃料喷嘴内的相对热增长最小化的实施例。 提供了一种燃料喷嘴结构，其中加热流体从燃料喷嘴基座中的进料孔设置在燃料喷嘴中的一个或多个通道中。 加热流体通过燃料喷嘴，从而提高燃料喷嘴部分的工作温度，以减少燃料喷嘴内热梯度的差异。 还公开了各种燃料喷嘴构造和通道几何形状。
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