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1.发明授权Dynamically uncoupled low NOx combustor having multiple premixers with axial staging 失效具有多个具有轴向分段的预混合器的动态分离的低NOx燃烧器
公开(公告)号：US5943866A
公开(公告)日：1999-08-31
申请号：US812894
申请日：1997-03-10
CPC分类号： F23R3/286 , F23R3/32 , F05B2260/962 , F23D2210/00 , F23R2900/00014
摘要： A low NOx combustor and method improve dynamic stability of a combustion flame fed by a fuel and air mixture. The combustor includes a chamber having a dome at one end thereof to which are joined a plurality of premixers. Each premixer includes a duct with a swirler therein for swirling air, and a plurality of fuel injectors for injecting fuel into the swirled air for flow into the combustion chamber to generate a combustion flame therein. The fuel injectors are axially staged at different axial distances from the dome to uncouple the fuel from combustion to reduce dynamic pressure amplitude of the combustion flame.
摘要翻译： 低NOx燃烧器和方法提高了由燃料和空气混合物供给的燃烧火焰的动态稳定性。 该燃烧器包括一个室，其一端具有一个圆顶，并与多个预混合器连接。 每个预混合器包括其中具有用于旋转空气的旋流器的管道和用于将燃料喷射到涡流空气中以流入燃烧室中以在其中产生燃烧火焰的多个燃料喷射器。 燃料喷射器在与圆顶不同的轴向距离上轴向分段，以将燃料从燃烧中分离以减少燃烧火焰的动态压力振幅。
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公开(公告)号：US06301899B1
公开(公告)日：2001-10-16
申请号：US09299792
申请日：1999-03-17
IPC分类号： F02C100
CPC分类号： F23R3/286 , F23C7/004 , F23D2206/10
摘要： A mixer for a combustor includes a swirler having a plurality of vanes disposed at an upstream end of a mixing duct. A centerbody extends downstream from the vanes and includes a fuel chamber integrally joined to the vanes. Fuel injection openings extend from the chamber into passages between the vanes.
摘要翻译： 用于燃烧器的混合器包括旋流器，其具有设置在混合管道的上游端的多个叶片。 中心体从叶片的下游延伸并且包括与叶片整体接合的燃料室。 燃料喷射开口从腔室延伸到叶片之间的通道中。
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3.发明授权Dynamically uncoupled low nox combustor with axial fuel staging in premixers 有权在预混合器中具有轴向燃料分级的动态分离的低噪声燃烧器
公开(公告)号：US6164055A
公开(公告)日：2000-12-26
申请号：US248749
申请日：1999-02-12
CPC分类号： F23R3/286 , F05B2260/962 , F23D2210/00 , F23R3/32 , F23R2900/00014
摘要： A low NOx combustor and method improve dynamic stability of a combustion flame fed by a fuel and air mixture. The combustor includes a chamber having a dome at one end thereof to which are joined a plurality of premixers. Each premixer includes a duct with a swirler therein for swirling air, and a plurality of fuel injectors for injecting fuel into the swirled air for flow into the combustion chamber to generate a combustion flame therein. The fuel injectors are axially staged at different axial distances from the dome to uncouple the fuel from combustion to reduce dynamic pressure amplitude of the combustion flame.
摘要翻译： 低NOx燃烧器和方法提高了由燃料和空气混合物供给的燃烧火焰的动态稳定性。 该燃烧器包括一个室，其一端具有一个圆顶，并与多个预混合器连接。 每个预混合器包括其中具有用于旋转空气的旋流器的管道和用于将燃料喷射到涡流空气中以流入燃烧室中以在其中产生燃烧火焰的多个燃料喷射器。 燃料喷射器在与圆顶不同的轴向距离上轴向分段，以将燃料从燃烧中分离以减少燃烧火焰的动态压力振幅。
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公开(公告)号：US5749229A
公开(公告)日：1998-05-12
申请号：US542982
申请日：1995-10-13
申请人： Nesim Abuaf , Steven George Goebel
发明人： Nesim Abuaf , Steven George Goebel
CPC分类号： F23R3/002 , F02K1/82 , F05D2260/201 , F23R2900/03044 , Y02T50/67 , Y02T50/675 , Y10S60/909 , Y10T428/12611
摘要： A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.
摘要翻译： 燃烧器衬套包括用于面对燃烧气体的内层和用于面对冷却流体的相对的外层。 外层具有比内层更大的导热系数，用于降低内衬中的温度梯度。 在一个优选实施例中，外层显着降低了衬套中的温度梯度，这是由冲击冷却空气射流变化的冷却能力引起的，用于更均匀地冷却燃烧器衬套并降低其最大温度。
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公开(公告)号：US5899075A
公开(公告)日：1999-05-04
申请号：US818465
申请日：1997-03-17
CPC分类号： F23R3/286 , F23C7/004 , F23D2206/10
摘要： A combustor comprises a hollow body defining a combustion chamber. The hollow body is typically annular in form and includes an outer liner, an inner liner, and an upstream dome plate. The dome plate includes a swirl cup with a mixer disposed therein to provide uniform mixing of fuel and air. The mixer comprises an inner swirler and an outer swirler that are mounted in the swirl cup. The outer swirler includes solid vanes. A shroud surrounds the mixer at the upstream end, which shroud includes an annular fuel chamber. The shroud further includes a number of axial fuel injection fuel injection openings that provide flow communication between the annular fuel chamber and the mixer and radially inject fuel within the mixer.
摘要翻译： 燃烧器包括限定燃烧室的中空体。 中空体通常为环形，包括外衬套，内衬和上游圆顶板。 圆顶板包括旋转杯，其中设置有混合器，以提供燃料和空气的均匀混合。 混合器包括安装在涡流杯中的内旋流器和外旋流器。 外旋流器包括固体叶片。 护罩在上游端围绕混合器，该护罩包括环形燃料室。 护罩还包括多个轴向燃料喷射燃料喷射开口，其提供环形燃料室和混合器之间的流动连通并且在混合器内径向喷射燃料。
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公开(公告)号：US5960632A
公开(公告)日：1999-10-05
申请号：US912529
申请日：1997-08-18
申请人： Nesim Abuaf , Steven George Goebel
发明人： Nesim Abuaf , Steven George Goebel
CPC分类号： F23R3/002 , F02K1/82 , F05D2260/201 , F23R2900/03044 , Y02T50/67 , Y02T50/675 , Y10S60/909 , Y10T428/12611
摘要： A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.
摘要翻译： 燃烧器衬套包括用于面对燃烧气体的内层和用于面对冷却流体的相对的外层。 外层具有比内层更大的导热系数，用于降低内衬中的温度梯度。 在一个优选实施例中，外层显着降低了衬套中的温度梯度，这是由冲击冷却空气射流变化的冷却能力引起的，用于更均匀地冷却燃烧器衬套并降低其最大温度。
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公开(公告)号：US5996351A
公开(公告)日：1999-12-07
申请号：US888252
申请日：1997-07-07
摘要： A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.
摘要翻译： 与驱动燃气轮机的压缩机配合的燃烧器包括圆筒形的外部燃烧器壳体。 具有上游富集部分，骤冷部分和下游稀薄部分的燃烧衬套设置在外部燃烧器壳体内，限定具有至少芯部淬火区域和外部淬火区域的燃烧室。 第一组多个淬火孔设置在所述衬套内的所述淬火部分处，所述淬火部分具有第一直径，以提供冷却喷射渗透到所述燃烧室的所述淬火部分的芯区域。 第二多个骤冷孔在淬火部分内设置在衬套内，具有第二直径以提供冷却射流渗透到燃烧室的骤冷段的外部区域。 在替代实施例中，燃烧室淬火部分还包括至少一个中间区域和在淬火部分处设置在衬套内的至少三个淬火孔，其具有第三直径以提供冷却喷射穿透至少一个中间区域 燃烧室的骤冷段。
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