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1.发明授权公开(公告)号：US07188465B2
公开(公告)日：2007-03-13
申请号：US10704302
申请日：2003-11-10
CPC分类号： F23R3/34 , F02C7/222 , F02C7/228 , F02C9/28 , F05D2270/0831 , F05D2270/303 , F23N1/002 , F23N5/102 , F23N2035/12 , F23N2037/02 , F23R3/46
摘要： The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each manifold supplies at least one fuel nozzle in multiple combustion chambers with fuel. The fuel control valves are mounted on the manifolds such that the weight of the fuel control valves and nozzles are carried by the manifolds, not the multiple combustion chambers. A plurality of thermocouples for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In carrying out the methods of the present invention for tuning a gas turbine, it is essential to note that the most efficient gas turbine is one which has the least nitrous oxides, the least amount of unburned hydrocarbons, and the least amount of carbon monoxide for a specified energy output. In order to tune the gas turbine to accomplish these objectives, it is desirable that each combustion chamber in the gas turbine be well balanced relative to the remaining combustion chambers. It is an aim of the present invention to tune each of the multiple combustion chambers such that no specific combustion chamber is rich or lean, and all are operating within about 1% of the remaining combustion chambers.
摘要翻译： 本发明的燃气轮机具有多个燃烧室，并且在每个室内都有多个燃料喷嘴。 每个喷嘴都有自己的燃料控制阀，以控制流向喷嘴的燃料。 为了最小化通过燃料控制阀的压降，采用多个歧管。 每个歧管在具有燃料的多个燃烧室中提供至少一个燃料喷嘴。 燃料控制阀安装在歧管上，使得燃料控制阀和喷嘴的重量由歧管而不是多个燃烧室承载。 用于测量来自所述多个燃烧室的废气的多个热电偶用于感测排气温度。 在执行用于调谐燃气轮机的本发明的方法时，必须注意的是，最有效的燃气轮机是具有最少一氧化二氮，最少量的未燃碳氢化合物和最少量的一氧化碳的燃气轮机 指定能量输出。 为了调整燃气涡轮机以实现这些目的，期望燃气涡轮机中的每个燃烧室相对于剩余的燃烧室良好平衡。 本发明的目的是调节多个燃烧室中的每个，使得没有特定的燃烧室是富的或者是贫的，并且都在剩余的燃烧室的大约1％的范围内运行。
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公开(公告)号：US07260937B2
公开(公告)日：2007-08-28
申请号：US11670542
申请日：2007-02-02
CPC分类号： F23R3/34 , F02C7/222 , F02C7/228 , F02C9/28 , F05D2270/0831 , F05D2270/303 , F23N1/002 , F23N5/102 , F23N2035/12 , F23N2037/02 , F23R3/46
摘要： The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each manifold supplies at least one fuel nozzle in multiple combustion chambers with fuel. The fuel control valves are mounted on the manifolds such that the weight of the fuel control valves and nozzles are carried by the manifolds, not the multiple combustion chambers. A plurality of thermocouples for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In carrying out the methods of the present invention for tuning a gas turbine, it is essential to note that the most efficient gas turbine is one which has the least nitrous oxides, the least amount of unburned hydrocarbons, and the least amount of carbon monoxide for a specified energy output. In order to tune the gas turbine to accomplish these objectives, it is desirable that each combustion chamber in the gas turbine be well balanced relative to the remaining combustion chambers. It is an aim of the present invention to tune each of the multiple combustion chambers such that no specific combustion chamber is rich or lean, and all are operating within about 1% of the remaining combustion chambers.
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