公开(公告)号：US20120279230A1

公开(公告)日：2012-11-08

申请号：US13512120

申请日：2010-11-26

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C9/26

CPC分类号： F02C9/34 ,  F02C9/00 ,  F02C9/20 ,  F05D2270/301 ,  F05D2270/303

摘要： Gas turbine and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine. The method includes calculating an exhaust temperature reference curve of the turbine as a function of a turbine pressure ratio; determining whether condition IGVmin+ΔIGV1≦IGVset point≦IGVmax+ΔIGV2, and condition ttx≧ttxh+Δttx3, are true; and changing, if both conditions are true, a split fuel quantity from a first value to a second value or otherwise maintaining the first value, the first value characterizing a lean-lean steady state mode and the second value characterizing a premixed secondary mode of a premixed mode.

摘要翻译： 燃气轮机和用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气轮机的工作点的方法。 该方法包括计算涡轮机的排气温度参考曲线作为涡轮压力比的函数; 确定条件IGVmin +＆Dgr; IGV1＆nlE; IGVset point＆nlE; IGVmax +＆Dgr; IGV2和条件ttx≥ttxh+＆Dgr; ttx3是否为真; 以及如果两个条件均为真，则从第一值到第二值或另外保持第一值的分割燃料量，表征贫瘦稳态模式的第一值和表征预混合二次模式的第二值 预混模式

公开(公告)号：US20130019607A1

公开(公告)日：2013-01-24

申请号：US13512108

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C9/00

CPC分类号： F02C9/20 ,  F02C9/00 ,  F05D2270/301 ,  F05D2270/303 ,  F23N2023/42 ,  F23N2023/44 ,  F23N2025/04 ,  F23N2025/10 ,  F23N2025/26 ,  F23N2041/20 ,  Y02T50/677

摘要： Gas turbine, software and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method includes determining a turbine exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the turbine exhaust pressure and the compressor pressure discharge; calculating an exhaust temperature at the exhaust of the turbine as a function of the turbine pressure ratio; identifying a reference exhaust temperature curve in a plane defined by the exhaust temperature and the turbine pressure ratio; and controlling the gas turbine to maintain the operating point on the reference exhaust temperature curve.

摘要翻译： 提供了用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气轮机的工作点的燃气轮机，软件和方法。 该方法包括确定涡轮机排气处的涡轮排气压力; 测量压缩机的压缩机压力放电; 基于所述涡轮排气压力和所述压缩机压力排放来确定涡轮压力比; 根据涡轮压力比计算涡轮机排气处的排气温度; 识别由排气温度和涡轮压力比限定的平面中的参考排气温度曲线; 并且控制燃气轮机将工作点保持在参考排气温度曲线上。

公开(公告)号：US20130219910A1

公开(公告)日：2013-08-29

申请号：US13512071

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C9/26

CPC分类号： F02C9/26 ,  F02C9/00 ,  F02C9/20 ,  F05D2270/301 ,  F05D2270/303 ,  F23N5/003 ,  F23N2025/04 ,  F23N2041/20 ,  F23R3/346 ,  Y02T50/677

摘要： A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.

摘要翻译： 提供了一种燃气轮机，计算机软件和用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气涡轮机的工作点的方法。 该方法包括：确定涡轮机排气处的排气压力; 测量压缩机的压缩机压力放电; 基于排气压力和压缩机压力排放确定涡轮压力比; 计算作为涡轮压力比的函数的主贫血模式转移阈值参考曲线，其中初级贫瘦模式转移阈值曲线包括燃气涡轮机的操作在初级模式到第一模式转换阈值曲线之间改变的点 贫瘦模式; 并且控制所述燃气轮机在所述主要模式和所述贫血模式之间改变。

公开(公告)号：US20130042624A1

公开(公告)日：2013-02-21

申请号：US13512185

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C1/00

CPC分类号： F02C9/00 ,  F02C9/34 ,  F05D2270/301 ,  F05D2270/303 ,  F23N5/003 ,  F23N2021/00 ,  F23N2037/08 ,  F23N2041/20 ,  F23R3/36 ,  F23R2900/00002

摘要： Gas turbine, computer readable medium, and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and a turbine is provided. The method includes determining a turbine pressure ratio, calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, determining at a first time when an exhaust temperature associated with the operating point is higher than an exhaust temperature of the primary to lean-lean mode transfer threshold reference curve for the same turbine pressure ratio, and changing, after a predetermined time after the first time, a split fuel quantity from a first value to a second value if the exhaust temperature associated with the operating point remains higher than the exhaust temperature of the primary to lean-lean mode transfer threshold reference curve.

摘要翻译： 提供了燃气轮机，计算机可读介质和用于控制包括压缩机，燃烧器和涡轮机的燃气轮机的工作点的方法。 该方法包括确定涡轮压力比，计算作为涡轮压力比的函数的主贫贫模式转移阈值参考曲线，在与工作点相关联的排气温度高于排气温度的第一时间确定 在相同的涡轮机压力比下，对于初级至贫乏模式转移阈值参考曲线，并且如果与第一值相关联的排气温度在第一时间之后的预定时间之后将分流燃料量从第一值改变为第二值， 工作点保持高于主稀薄模式转移阈值参考曲线的排气温度。

公开(公告)号：US08904803B2

公开(公告)日：2014-12-09

申请号：US13512071

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C1/00 ,  F02C9/20 ,  F02C9/00 ,  F02C9/26

CPC分类号： F02C9/26 ,  F02C9/00 ,  F02C9/20 ,  F05D2270/301 ,  F05D2270/303 ,  F23N5/003 ,  F23N2025/04 ,  F23N2041/20 ,  F23R3/346 ,  Y02T50/677

摘要： A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.

摘要翻译： 提供了一种燃气轮机，计算机软件和用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气涡轮机的工作点的方法。 该方法包括：确定涡轮机排气处的排气压力; 测量压缩机的压缩机压力放电; 基于排气压力和压缩机压力排放确定涡轮压力比; 计算作为涡轮压力比的函数的主贫血模式转移阈值参考曲线，其中初级贫瘦模式转移阈值曲线包括燃气涡轮机的操作在初级模式到第一模式转换阈值曲线之间改变的点 贫瘦模式; 并且控制所述燃气轮机在所述主要模式和所述贫血模式之间改变。

公开(公告)号：US08713946B2

公开(公告)日：2014-05-06

申请号：US13512120

申请日：2010-11-26

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C1/00

CPC分类号： F02C9/34 ,  F02C9/00 ,  F02C9/20 ,  F05D2270/301 ,  F05D2270/303

摘要： Gas turbine and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine. The method includes calculating an exhaust temperature reference curve of the turbine as a function of a turbine pressure ratio; determining whether condition IGVmin+ΔIGV1≦IGVset point≦IGVmax+ΔIGV2, and condition ttx≧ttxh+Δttx3, are true; and changing, if both conditions are true, a split fuel quantity from a first value to a second value or otherwise maintaining the first value, the first value characterizing a lean-lean steady state mode and the second value characterizing a premixed secondary mode of a premixed mode.

摘要翻译： 燃气轮机和用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气轮机的工作点的方法。 该方法包括计算涡轮机的排气温度参考曲线作为涡轮压力比的函数; 确定条件IGVmin +＆Dgr; IGV1＆nlE; IGVset point＆nlE; IGVmax +＆Dgr; IGV2和条件ttx≥ttxh+＆Dgr; ttx3是否为真; 以及如果两个条件均为真，则从第一值到第二值或另外保持第一值的分割燃料量，表征贫瘦稳态模式的第一值和表征预混合二次模式的第二值 预混模式

公开(公告)号：US08448445B2

公开(公告)日：2013-05-28

申请号：US12364580

申请日：2009-02-03

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C7/22 ,  F02C7/26

CPC分类号： F01D19/00 ,  F02C7/26 ,  F02C9/26

摘要： A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct (28) of the turbine (20), establishing a predetermined minimum value (FSR1) for the flow of gaseous fuel entering the combustor (14) for a period of time which is adequate for effecting a first attempt at ignition and effecting a first attempt at ignition, effecting an intermediate purging cycle of the discharge duct (28), interrupting the flow of gaseous fuel to the combustor (14), and progressively increasing the value (FSRn) of the flow of gaseous fuel entering the combustor (14), effecting further attempts at ignition until the mixture of air/gaseous fuel has been ignited and the consequent start-up of the turbine (20), or until a predetermined maximum value (FSRmax) of the flow of gaseous fuel has been reached.

摘要翻译： 描述了一种用于启动燃气涡轮机的方法，该方法包括实现涡轮机（20）的排放管道（28）的初步吹扫循环的相位，为气体燃料流量建立预定的最小值（FSR1） 进入燃烧器（14）一段时间，足以在点燃时进行第一次尝试并且进行点火时的第一次尝试，进行排放管道（28）的中间清洗循环，中断气态燃料流向 燃烧器（14），并逐渐增加进入燃烧器（14）的气体燃料流的值（FSRn），进一步尝试着火，直到空气/气体燃料的混合物被点燃，并且随后的启动 涡轮机（20），或直到达到气态燃料流的预定最大值（FSRmax）。

公开(公告)号：US09140195B2

公开(公告)日：2015-09-22

申请号：US13512108

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C9/20 ,  F02C9/00

CPC分类号： F02C9/20 ,  F02C9/00 ,  F05D2270/301 ,  F05D2270/303 ,  F23N2023/42 ,  F23N2023/44 ,  F23N2025/04 ,  F23N2025/10 ,  F23N2025/26 ,  F23N2041/20 ,  Y02T50/677

摘要： Gas turbine, software and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method includes determining a turbine exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the turbine exhaust pressure and the compressor pressure discharge; calculating an exhaust temperature at the exhaust of the turbine as a function of the turbine pressure ratio; identifying a reference exhaust temperature curve in a plane defined by the exhaust temperature and the turbine pressure ratio; and controlling the gas turbine to maintain the operating point on the reference exhaust temperature curve.

摘要翻译： 提供了用于控制包括压缩机，燃烧器和至少一个涡轮机的燃气轮机的工作点的燃气轮机，软件和方法。 该方法包括确定涡轮机排气处的涡轮排气压力; 测量压缩机的压缩机压力放电; 基于所述涡轮排气压力和所述压缩机压力排放来确定涡轮压力比; 根据涡轮压力比计算涡轮机排气处的排气温度; 识别由排气温度和涡轮压力比限定的平面中的参考排气温度曲线; 并且控制燃气轮机将工作点保持在参考排气温度曲线上。

公开(公告)号：US08820089B2

公开(公告)日：2014-09-02

申请号：US13512185

申请日：2010-11-19

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C9/00

CPC分类号： F02C9/00 ,  F02C9/34 ,  F05D2270/301 ,  F05D2270/303 ,  F23N5/003 ,  F23N2021/00 ,  F23N2037/08 ,  F23N2041/20 ,  F23R3/36 ,  F23R2900/00002

摘要： Gas turbine, computer readable medium, and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and a turbine is provided. The method includes determining a turbine pressure ratio, calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, determining at a first time when an exhaust temperature associated with the operating point is higher than an exhaust temperature of the primary to lean-lean mode transfer threshold reference curve for the same turbine pressure ratio, and changing, after a predetermined time after the first time, a split fuel quantity from a first value to a second value if the exhaust temperature associated with the operating point remains higher than the exhaust temperature of the primary to lean-lean mode transfer threshold reference curve.

摘要翻译： 提供了燃气轮机，计算机可读介质和用于控制包括压缩机，燃烧器和涡轮机的燃气轮机的工作点的方法。 该方法包括确定涡轮压力比，计算作为涡轮压力比的函数的主贫贫模式转移阈值参考曲线，在与工作点相关联的排气温度高于排气温度的第一时间确定 在相同的涡轮机压力比下，对于初级至贫乏模式转移阈值参考曲线，并且如果与第一值相关联的排气温度在第一时间之后的预定时间之后将分流燃料量从第一值改变为第二值， 工作点保持高于主稀薄模式转移阈值参考曲线的排气温度。

公开(公告)号：US20100126179A1

公开(公告)日：2010-05-27

申请号：US12364580

申请日：2009-02-03

申请人： Claudio Botarelli

发明人： Claudio Botarelli

IPC分类号： F02C7/26

CPC分类号： F01D19/00 ,  F02C7/26 ,  F02C9/26

摘要： A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct (28) of the turbine (20), establishing a predetermined minimum value (FSR1) for the flow of gaseous fuel entering the combustor (14) for a period of time which is adequate for effecting a first attempt at ignition and effecting a first attempt at ignition, effecting an intermediate purging cycle of the discharge duct (28), interrupting the flow of gaseous fuel to the combustor (14), and progressively increasing the value (FSRn) of the flow of gaseous fuel entering the combustor (14), effecting further attempts at ignition until the mixture of air/gaseous fuel has been ignited and the consequent start-up of the turbine (20), or until a predetermined maximum value (FSRmax) of the flow of gaseous fuel has been reached.

摘要翻译： 描述了一种用于启动燃气涡轮机的方法，该方法包括实现涡轮机（20）的排放管道（28）的初步吹扫循环的相位，为气体燃料流量建立预定的最小值（FSR1） 进入燃烧器（14）一段时间，足以在点燃时进行第一次尝试并且进行点火时的第一次尝试，进行排放管道（28）的中间清洗循环，中断气态燃料流向 燃烧器（14），并逐渐增加进入燃烧器（14）的气体燃料流的值（FSRn），进一步尝试着火，直到空气/气体燃料的混合物被点燃，并且随后的启动 涡轮机（20），或直到达到气态燃料流的预定最大值（FSRmax）。