公开(公告)号：US20150184856A1

公开(公告)日：2015-07-02

申请号：US14038038

申请日：2013-09-26

Applicant: PETER JOHN STUTTAFORD ,  STEPHEN JORGENSEN ,  HANY RIZKALLA

Inventor： PETER JOHN STUTTAFORD ,  STEPHEN JORGENSEN ,  HANY RIZKALLA

IPC: F23R3/00 ,  B23K31/02 ,  B23K1/00

CPC classification number: F23R3/002 ,  B23K1/0008 ,  B23K31/02 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/00018 ,  Y10T29/49826

Abstract: The present invention discloses a novel and improved device and method for securing a combustion liner within a gas turbine combustor. The improved configuration comprises a plurality of equally spaced support tab assemblies secured about the combustion liner and positioned radially outward of the combustion zone. The support tab assemblies comprise parallel liner tabs which provide increased flexibility, greater structural support, and lower operating stresses.

Abstract translation: 本发明公开了一种用于固定燃气轮机燃烧器内的燃烧衬套的新型改进的装置和方法。 改进的构造包括围绕燃烧衬套固定并且定位在燃烧区的径向外侧的多个等距间隔的支撑片组件。 支撑片组件包括平行的衬垫突片，其提供增加的柔性，更大的结构支撑和较低的操作应力。

公开(公告)号：US20140277790A1

公开(公告)日：2014-09-18

申请号：US14213366

申请日：2014-03-14

Applicant: DONALD GAUTHIER ,  HANY RIZKALLA ,  PETER JOHN STUTTAFORD

Inventor： DONALD GAUTHIER ,  HANY RIZKALLA ,  PETER JOHN STUTTAFORD

IPC: G05B15/02

CPC classification number: F02C9/22 ,  F02C9/00 ,  F02C9/48 ,  F05D2260/964 ,  G05B15/02

Abstract: Methods are provided for ensuring non-excessive variation of a gradient of an applied split bias versus firing temperature of a gas turbine engine. It is determined that an incremental split bias step is to be taken, and a current firing temperature of the gas turbine engine is identified on a graph. A first difference between a split schedule and an applied schedule gradient is calculated using lower firing temperatures than the current firing temperature, and a second difference is calculated using higher firing temperatures. If the first difference exceeds a predetermined limit, the incremental split bias step is not allowed at a lower firing temperature, and similarly, if the second difference exceeds a predetermined limit, the incremental split bias step is not allowed at a higher firing temperature.

Abstract translation: 提供了用于确保施加的分流偏压的梯度相对于燃气涡轮发动机的燃烧温度的过度变化的方法。 确定要采取增量分离偏置步骤，并且在图上识别燃气涡轮发动机的当前点火温度。 使用比当前烧制温度更低的烧制温度来计算裂缝计划和施加的计划梯度之间的第一个差异，并且使用更高的烧制温度计算第二个差异。 如果第一差异超过预定极限，则在较低的烧制温度下不允许增量分离偏压步骤，同样，如果第二差异超过预定极限，则在更高的烧制温度下不允许增量分离偏压步骤。

公开(公告)号：US20140277789A1

公开(公告)日：2014-09-18

申请号：US14213337

申请日：2014-03-14

Applicant: PETER JOHN STUTTAFORD ,  SUMIT SONI ,  DONALD GAUTHIER ,  HANY RIZKALLA

Inventor： PETER JOHN STUTTAFORD ,  SUMIT SONI ,  DONALD GAUTHIER ,  HANY RIZKALLA

IPC: G05B15/02

CPC classification number: F02C9/22 ,  F02C9/00 ,  F02C9/48 ,  F05D2260/964 ,  G05B15/02

Abstract: A method for tuning a combustor of a gas turbine engine based on one or more monitored operating conditions is provided. One or more operating conditions of the gas turbine engine are monitored. The monitored operating conditions may include, for example, a low frequency tone, a high frequency tone, and a ratio of the low frequency tone to the high frequency tone. It is determined whether the ratio of the low frequency tone to the high frequency tone is within a first predefined normal range. If the ratio of the low frequency tone to the high frequency tone is within the first predefined normal range, a determination is made not to tune the gas turbine engine. But, if the ratio of the low frequency tone to the high frequency tone is not within the first predefined normal range, a determination is made to tune the gas turbine engine.

Abstract translation: 提供了一种用于基于一个或多个监视的操作条件来调节燃气涡轮发动机的燃烧器的方法。 监测燃气涡轮发动机的一个或多个操作条件。 所监视的操作条件可以包括例如低频音调，高频音调以及低频音调与高频音调的比率。 确定低频音调与高频音调的比率是否在第一预定正常范围内。 如果低频音调与高频音调的比例在第一预定义的正常范围内，则确定不调谐燃气涡轮发动机。 但是，如果低频音与高频音的比例不在第一预定正常范围内，则确定调谐燃气轮机。

公开(公告)号：US20140090389A1

公开(公告)日：2014-04-03

申请号：US14038016

申请日：2013-09-26

Applicant: PETER JOHN STUTTAFORD ,  STEPHEN JORGENSEN ,  YAN CHEN ,  HANY RIZKALLA ,  KHALID OUMEJJOUD ,  MIRKO R. BOTHIEN

Inventor： PETER JOHN STUTTAFORD ,  STEPHEN JORGENSEN ,  YAN CHEN ,  HANY RIZKALLA ,  KHALID OUMEJJOUD ,  MIRKO R. BOTHIEN

IPC: F23R3/54

CPC classification number: F23R3/54 ,  F23C2201/20 ,  F23C2900/06043 ,  F23C2900/07001 ,  F23R3/14 ,  F23R3/16 ,  F23R3/26 ,  F23R3/286 ,  F23R3/34 ,  F23R3/343 ,  F23R3/60 ,  F23R2900/00014 ,  F23R2900/03343

Abstract: The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures.

Abstract translation: 本发明公开了一种用于操作燃气轮机燃烧器的新型装置和方法，该燃气轮机燃烧器具有靠近燃烧器的导向区域的结构构造，其试图使热声动力学的开始最小化。 燃烧器的引导区域包括大致圆柱形的延伸部，其具有带有不规则轮廓的出口端，该不规则轮廓将不对称性结合到系统中，以便破坏任何相干结构。

公开(公告)号：US08418474B2

公开(公告)日：2013-04-16

申请号：US12240380

申请日：2008-09-29

Applicant: Hany Rizkalla ,  Stephen W. Jorgensen ,  Peter Stuttaford

Inventor： Hany Rizkalla ,  Stephen W. Jorgensen ,  Peter Stuttaford

IPC: F02C7/20 ,  F02C1/00 ,  F02G3/00

CPC classification number: F01D9/023 ,  F05D2260/96

Abstract: A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.

Abstract translation: 公开了一种具有热释放后框架并且能够调节固有频率的过渡管道。 后框架能够由于过渡管道的热梯度而允许移动。 过渡管道使用位于后部安装支架附近的弹簧板，其中弹簧板基于其厚度可以增加或减小过渡管道的频率。 这种布置确保了过渡管道固有频率不与其它关键的发动机和/或燃烧器频率重合或交叉。

公开(公告)号：US20110270502A1

公开(公告)日：2011-11-03

申请号：US13086978

申请日：2011-04-14

Applicant: Nicolas Demougeot ,  Donald Gauthier ,  Peter Stuttaford ,  Hany Rizkalla

Inventor： Nicolas Demougeot ,  Donald Gauthier ,  Peter Stuttaford ,  Hany Rizkalla

IPC: F02C9/26

CPC classification number: F02C7/224 ,  F02C9/28 ,  F02C9/40

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110265487A1

公开(公告)日：2011-11-03

申请号：US13053910

申请日：2011-03-22

Applicant: Donald Gauthier ,  Nicolas Demougeot ,  Peter Stuttaford ,  Hany Rizkalla

Inventor： Donald Gauthier ,  Nicolas Demougeot ,  Peter Stuttaford ,  Hany Rizkalla

IPC: F02C9/26

CPC classification number: F02C7/228 ,  F02C9/28 ,  F05D2270/301 ,  F05D2270/303 ,  F23N1/002 ,  F23N2037/02 ,  F23N2037/18 ,  F23N2037/28 ,  F23N2041/20 ,  F23R3/34 ,  F23R2900/00013

Abstract: Tuning processes implemented by an auto-tune controller are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process includes monitoring parameters, such as combustion dynamics and emission composition. Upon determining that one or more of the monitored parameters exceed a critical value, these “out-of-tune” parameters are compared to a scanning order table. Upon comparison, the first out-of-tune parameter that is matched within the scanning order table is addressed. The first out-of-tune parameter is then plotted as overlaid slopes on respective graphs, where the graph represents a fuel-flow split. Typically, the slopes are plotted as a particular out-of-tune parameter against a particular fuel-flow split. The slopes for each graph are considered together by taking into account the combined impact on each out-of-tune parameter when a fuel-flow split is selected for adjustment.

Abstract translation: 提供由自动调谐控制器实现的调谐过程，用于通过调谐过程测量和调整燃气轮机（GT）发动机的燃烧动力学和发射组成。 最初，调谐过程包括监测参数，如燃烧动态和排放组成。 在确定一个或多个所监视的参数超过临界值时，将这些“失调”参数与扫描顺序表进行比较。 相比之下，寻址在扫描顺序表中匹配的第一个失调参数。 然后将第一个失调参数作为叠加的斜率绘制在各个图上，其中图表示燃料流分流。 通常，斜率被绘制为针对特定燃料流分流的特定失调参数。 当选择燃料流分流进行调整时，通过考虑对每个失调参数的组合影响，每个曲线图的斜率被一起考虑。

公开(公告)号：US20050262844A1

公开(公告)日：2005-12-01

申请号：US10856592

申请日：2004-05-28

Applicant: Andrew Green ,  Peter Stuttaford ,  Jeffrey Benoit ,  Vamsi Duraibabu ,  Hany Rizkalla

Inventor： Andrew Green ,  Peter Stuttaford ,  Jeffrey Benoit ,  Vamsi Duraibabu ,  Hany Rizkalla

IPC: F01D9/02 ,  F23R3/00 ,  F23R3/42 ,  F23R3/46

CPC classification number: F23R3/002 ,  F01D9/023 ,  F23R3/46 ,  Y02T50/675

Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.

Abstract translation: 公开了一种燃气轮机燃烧衬套，其在其与过渡管道之间具有交替的界面区域，其中沿着燃烧衬套的后端的冷却效果和热传递得到改善，导致部件寿命延长。 靠近其第二端的燃烧衬套的区域包括多个第一进料孔，密封过渡管道的多个弹簧密封件，具有多个第二进料孔的冷却环，其中第一进料孔通过冷却 流体进入形成在冷却环和燃烧衬套之间的环形空间中。 冷却流体越过用于增加靠近燃烧衬套第二端的热传递的装置，其中传热增强优选地包括多个凸脊，其增加外衬套壁的表面积以使冷却流体紊乱并使冷却最大化 有效性

公开(公告)号：US06886346B2

公开(公告)日：2005-05-03

申请号：US10644385

申请日：2003-08-20

Applicant: Peter A. Sobieski ,  Kelly Shawn Smith ,  Alan Lovelace ,  Hany Rizkalla

Inventor： Peter A. Sobieski ,  Kelly Shawn Smith ,  Alan Lovelace ,  Hany Rizkalla

IPC: F02C7/22

CPC classification number: F02C7/22 ,  F23R3/286 ,  F23R3/343

Abstract: A pilot fuel nozzle configuration for use in a combustor is disclosed having a natural frequency outside the range of the operating frequencies of a gas turbine engine. Multiple embodiments are disclosed for the improved pilot fuel nozzle including configurations for newly manufactured nozzles, repair to existing pilot nozzles, as well as multiple natural frequency levels for the improved pilot fuel nozzle. The pilot fuel nozzle comprises an elongated housing, first and second flanges, and a nozzle tip, with the first flange fixed to the elongated housing at a first end and the nozzle tip fixed to the second end, opposite of the first end. The second flange is fixed along the elongated housing and is used for attaching the pilot fuel nozzle to a combustor. The present invention incorporates an increased wall thickness along at least a mid-span portion of the pilot nozzle to increase the stiffness and change the natural frequency.

Abstract translation: 公开了一种用于燃烧器的先导燃料喷嘴构造，其具有在燃气涡轮发动机的工作频率范围之外的固有频率。 公开了用于改进的引燃燃料喷嘴的多个实施例，其包括用于新制造的喷嘴的构造，对现有导向喷嘴的修理以及用于改进的引燃燃料喷嘴的多个固有频率水平。 导向燃料喷嘴包括细长壳体，第一和第二凸缘以及喷嘴尖端，其中第一凸缘在第一端处固定到细长壳体，并且喷嘴尖端固定到与第一端相对的第二端。 第二凸缘沿着细长壳体固定，并用于将引燃燃料喷嘴连接到燃烧器。 本发明包括沿引导喷嘴的至少中跨部分增加的壁厚，以增加刚度并改变固有频率。

公开(公告)号：US20090188255A1

公开(公告)日：2009-07-30

申请号：US12247615

申请日：2008-10-08

Applicant: Andrew Green ,  Peter Stuttaford ,  Yan Chen ,  Hany Rizkalla

Inventor： Andrew Green ,  Peter Stuttaford ,  Yan Chen ,  Hany Rizkalla

IPC: F02C7/12 ,  F23R3/32

CPC classification number: F01D9/023 ,  F23R3/002 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.

Abstract translation: 公开了一种具有改进的冷却结构的燃烧器端盖组件。 本发明的实施例涉及一种用于冷却燃烧器端盖组件的渗出板的装置和方法。 燃烧器端盖组件还包括具有多个冷却孔的冲击板，冲击板定位在距离排出板预定距离处。 冷却流体通过冲击板并且朝向和朝向积液板上并用于冷却渗出板。