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21. 发明申请

US20050039460A1 GAS TURBINE FUEL PILOT NOZZLE 有权
标题翻译：燃气涡轮喷油嘴喷嘴
公开(公告)号：US20050039460A1
公开(公告)日：2005-02-24
申请号：US10644385
申请日：2003-08-20
申请人： Peter Sobieski , Kelly Smith , Alan Lovelace , Hany Rizkalla
发明人： Peter Sobieski , Kelly Smith , Alan Lovelace , Hany Rizkalla
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F23R3/286 , F23R3/343
摘要： 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.
摘要翻译：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。

22. 发明授权

US06886346B2 Gas turbine fuel pilot nozzle 有权
标题翻译：燃气轮机燃油先导喷嘴
公开(公告)号：US06886346B2
公开(公告)日：2005-05-03
申请号：US10644385
申请日：2003-08-20
申请人： Peter A. Sobieski , Kelly Shawn Smith , Alan Lovelace , Hany Rizkalla
发明人： Peter A. Sobieski , Kelly Shawn Smith , Alan Lovelace , Hany Rizkalla
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F23R3/286 , F23R3/343
摘要： 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.
摘要翻译：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。

23. 发明授权

US09347669B2 Variable length combustor dome extension for improved operability 有权
标题翻译：可变长度的燃烧器穹顶延伸，以提高可操作性
公开(公告)号：US09347669B2
公开(公告)日：2016-05-24
申请号：US14038016
申请日：2013-09-26
申请人： Peter John Stuttaford , Stephen Jorgensen , Yan Chen , Hany Rizkalla , Khalid Oumejjoud , Mirko R. Bothien
发明人： Peter John Stuttaford , Stephen Jorgensen , Yan Chen , Hany Rizkalla , Khalid Oumejjoud , Mirko R. Bothien
IPC分类号： F23R3/16 , F23R3/54 , F23R3/28 , F23R3/26 , F23R3/60 , F23R3/34 , F23R3/14
CPC分类号： 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
摘要： 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.
摘要翻译：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。

24. 发明授权

US06935116B2 Flamesheet combustor 有权
标题翻译：火焰燃烧器
公开(公告)号：US06935116B2
公开(公告)日：2005-08-30
申请号：US10424350
申请日：2003-04-28
申请人： Peter J. Stuttaford , Stephen Jennings , Andrew Green , Ryan McMahon , Yan Chen , Hany Rizkalla , John Carella , Vamsi Duraibabu , Martin Spalding
发明人： Peter J. Stuttaford , Stephen Jennings , Andrew Green , Ryan McMahon , Yan Chen , Hany Rizkalla , John Carella , Vamsi Duraibabu , Martin Spalding
IPC分类号： F23R3/14 , F23R3/28 , F23R3/34 , F02C3/00 , F02C7/22 , F23R3/54
CPC分类号： F23R3/34 , F23R3/14 , F23R3/286
摘要： A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, and precise three dimensional staging between fuel injectors. Axial, radial, and circumferential fuel staging is utilized including fuel injection proximate air swirlers. Furthermore, strong recirculation zones are established proximate the introduction of fuel and air premixture from different stages to the combustion zone. The combination of the strong recirculation zones, efficient premixing, and staged fuel flow thereby provide the opportunity to produce low emissions combustion at various load conditions.
摘要翻译：公开了一种在多个负载条件下具有减少的排放和改进的火焰稳定性的燃气轮机燃烧系统。改进的燃烧系统通过完全预混合，多个燃料喷射器位置，燃烧器几何形状和燃料喷射器之间的精确三维分级来实现。使用轴向，径向和周向燃料分级，包括靠近空气旋流器的燃料喷射。此外，在从不同阶段到燃烧区的燃料和空气预混物的引入附近建立强的再循环区域。强再循环区域的组合，有效的预混合和分级燃料流量因此提供在各种负载条件下产生低排放燃烧的机会。

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