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1. 发明专利

JP2014016059A Gas turbine combustor and operation method for gas turbine combustor 有权
标题翻译：燃气轮机燃气轮机及其运行方法
公开(公告)号：JP2014016059A
公开(公告)日：2014-01-30
申请号：JP2012152001
申请日：2012-07-06
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ABE KAZUCHIKA , KOGANEZAWA TOMOKI , SAITO TAKEO , MIURA KEISUKE
IPC分类号： F23R3/00 , F02C7/22 , F23R3/10 , F23R3/18 , F23R3/28 , F23R3/48
CPC分类号： F23R3/286 , F02C7/22 , F02C7/26 , F23D14/24 , F23N2027/02 , F23R3/12 , F23R3/16 , F23R3/28 , F23R3/346 , F23R3/48
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a burner configured to simultaneously ignite a plurality of combustors at a fuel air ratio suitable to ignition of a gas turbine.SOLUTION: A gas turbine combustor includes a plurality of supports that fix air hole plates to combustors and are installed at substantially the same phase as a flame propagation pipe, and accelerates flame propagation at gas turbine ignition by adjusting combustion air distribution to ignite all combustors. The gas turbine combustor adjusts the combustion air distribution by disposing a porous plate at the downstream of the support, and also the gas turbine combustor adjusts the combustion air distribution by making the diameter of an air hole to which the flame propagation pipe approaches small.
摘要翻译：要解决的问题：提供一种燃气轮机燃烧器，其包括燃烧器，所述燃烧器被配置为以适于燃气轮机点火的燃料空气比同时点燃多个燃烧器。燃气轮机燃烧器包括多个固定空气孔的支撑件板与燃烧器并且安装在与火焰传播管基本相同的相位，并且通过调节燃烧空气分布来加速燃气轮机点火时的火焰传播以点燃所有燃烧器。燃气轮机燃烧器通过在支撑体的下游设置多孔板来调节燃烧空气分布，燃气轮机燃烧器通过使火焰传播管道的气孔的直径变小而调节燃烧空气分布。

2. 发明专利

JP2013241873A Gas turbine combustor, control device for gas turbine combustor and abnormality detection method for gas turbine combustor 有权
标题翻译：气体涡轮搅拌机，气体涡轮搅拌机控制装置和气体涡轮搅拌机异常检测方法
公开(公告)号：JP2013241873A
公开(公告)日：2013-12-05
申请号：JP2012115181
申请日：2012-05-21
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KOGANEZAWA TOMOKI , ABE KAZUCHIKA , MIURA KEISUKE , SAITO TAKEO
IPC分类号： F02C9/00 , F01D25/00 , F02C7/00 , F02C7/22 , F02C9/26 , F23R3/00 , F23R3/28 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To provide a means for detecting an abnormality and protecting a combustor or a gas turbine with a simple means even when an abnormality occurs for example, a part of a plurality of fuel nozzles or a part of a plurality of fuel jetting ports which are provided in a gas turbine combustor, and a section where the plurality of fuel jetting ports or the like are branched at the downstream of a fuel flow rate control valve of one fuel system.SOLUTION: A means for detecting a difference pressure between fuel pressure at the downstream of a fuel flow rate control valve provided in a fuel system and pressure in a combustor is provided. A means for specifying a fuel flow rate flowing in the fuel system is also provided. A divider for calculating ratio of difference pressure signal of the fuel system and a fuel flow rate signal of the fuel system is provided. A comparator for determining a combustor abnormality based on a signal from the divider is included.
摘要翻译：要解决的问题：为了提供一种用于检测异常并且即使在异常发生时也以简单的方式保护燃气轮机或燃气轮机的装置，例如，多个燃料喷嘴的一部分或多个燃料喷射的一部分设置在燃气轮机燃烧器中的端口以及多个燃料喷射口等在一个燃料系统的燃料流量控制阀的下游分支的部分。解决方案：一种用于检测燃料喷射口之间的差压的装置，提供了设置在燃料系统中的燃料流量控制阀的下游的燃料压力和燃烧器中的压力。还提供了用于指定在燃料系统中流动的燃料流量的装置。提供了用于计算燃料系统的差压信号的比率和燃料系统的燃料流量信号的分压器。包括用于基于来自分频器的信号确定燃烧器异常的比较器。

3. 发明专利

JP2012098027A Combustor 有权
标题翻译：燃烧室
公开(公告)号：JP2012098027A
公开(公告)日：2012-05-24
申请号：JP2012032283
申请日：2012-02-17
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： MIURA KEISUKE , MOMO SATOSHI , ABE KAZUCHIKA , KOGANEZAWA TOMOKI
IPC分类号： F23R3/30 , F23R3/10 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To provide a structure that strikes a balance between a low NOx and a combustion stability, in a gas turbine combustor.SOLUTION: The combustor 2 includes: a combustion chamber 50 from which fuel and air are supplied; an air hole plate 33, which is located in an upstream side of the combustion chamber 50, and which has a plurality of air holes 32; and a fuel nozzle 31 for supplying fuel to the air holes 32 of the air hole plate 33. The air hole plate has an inner peripheral side plane and an outer peripheral side plane, which are the planes vertical to a central axis direction of the air hole plate in a combustion chamber side, respectively. The inner peripheral side plane is located in a downstream side more than the outer peripheral side plane, and the inner peripheral side plane is connected with the outer peripheral side plane by the plane or a smooth surface.
摘要翻译：要解决的问题：提供一种在燃气轮机燃烧器中实现低NOx和燃烧稳定性之间平衡的结构。解决方案：燃烧器2包括：供应燃料和空气的燃烧室50; 位于燃烧室50的上游侧的气孔板33，具有多个气孔32; 以及用于向空气孔板33的气孔32供给燃料的燃料喷嘴31.气孔板具有作为垂直于空气的中心轴方向的平面的内周侧面和外周侧面分别在燃烧室侧的孔板。内周侧面位于比外周侧平面更靠下游的一侧，内周侧面通过平面或平滑面与外周侧面连接。版权所有（C）2012，JPO＆INPIT

4. 发明专利

JP2011074802A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2011074802A
公开(公告)日：2011-04-14
申请号：JP2009225888
申请日：2009-09-30
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ASAI TOMOHIRO , KOIZUMI HIROMI , YOSHIDA SHOHEI , KOGANEZAWA TOMOKI
IPC分类号： F02C3/24 , F02C6/08 , F02C7/22 , F02C9/00 , F02C9/18 , F02C9/40 , F02C9/52 , F23R3/06 , F23R3/14 , F23R3/26 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To solve a problem that the reliability of a burner is deteriorated because the metal temperature of a swirler surface drastically changes due to non-evaporation fuel or soot accumulating on the swirler surface, in a low quality oil fuel burning gas turbine combustor.
SOLUTION: The combustor includes a liquid fuel nozzle 20 jetting liquid fuel into a combustion chamber, a spray air nozzle 21 positioned on an outer peripheral side of the liquid fuel nozzle 20 and spraying spray air for atomizing the liquid fuel, and a swirler 17 supplying combustion air from the outer peripheral side of the spray air nozzle 21 to the combustion chamber. A purge air hole 50 for supplying purge air 104 is provided between a spray air hole 21a and a combustion air hole 24a on a swirler surface 18.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题为了解决由于旋流器表面的金属温度由于积聚在旋流器表面上的非蒸发燃料或烟灰而急剧变化的燃烧器的可靠性恶化的问题，在低质量的油燃料燃烧燃气轮机燃烧器。解决方案：燃烧器包括将液体燃料喷射到燃烧室中的液体燃料喷嘴20，位于液体燃料喷嘴20的外周侧的喷雾空气喷嘴21，喷射用于使液体燃料雾化的喷射空气，旋流器17将燃烧空气从喷雾空气喷嘴21的外周侧供给到燃烧室。在旋流器表面18上的喷射空气孔21a和燃烧空气孔24a之间设置有用于供给吹扫空气104的吹扫空气孔50.（C）2011，JPO＆INPIT

5. 发明专利

JP2010065579A Fuel supply method of gas turbine 有权
标题翻译：燃油供应方法
公开(公告)号：JP2010065579A
公开(公告)日：2010-03-25
申请号：JP2008231618
申请日：2008-09-10
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KOIZUMI HIROMI , ASAI TOMOHIRO , KOGANEZAWA TOMOKI , MIURA KEISUKE , YOSHIDA SHOHEI , NISHIJIMA YASUMASA
IPC分类号： F02C7/232 , F01K25/14 , F02C3/28 , F02C7/22 , F02C7/26 , F02C9/40
CPC分类号： Y02E20/18
摘要： PROBLEM TO BE SOLVED: To safely start a gas turbine without using starting fuel, even when hydrogen-including fuel is used for the gas turbine.
SOLUTION: A fuel supply method of a gas turbine combustor includes a fuel system for supplying the hydrogen-including fuel, a burner connected to the fuel system and jetting the hydrogen-including fuel to a combustion chamber, and a system for supplying purge gas to the fuel system, and includes a first process of supplying the purge gas in a pipe of the fuel system, and a second process of supplying the hydrogen-including fuel and the purge gas to the burner up to completing ignition from when starting the ignition of the gas turbine combustor.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：即使使用含氢燃料用于燃气轮机，也可以不使用起动燃料来安全地启动燃气轮机。解决方案：燃气轮机燃烧器的燃料供给方法包括用于供应含氢燃料的燃料系统，连接到燃料系统并将含氢燃料喷射到燃烧室的燃烧器和用于供给燃料的系统向燃料系统吹扫气体，并且包括在燃料系统的管道中供应吹扫气体的第一过程，以及将第二过程向燃烧器供应直到完成点火的燃料和净化气体从起动燃气轮机燃烧器的点火。版权所有（C）2010，JPO＆INPIT

6. 发明专利

JP2009014297A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2009014297A
公开(公告)日：2009-01-22
申请号：JP2007178422
申请日：2007-07-06
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ABE KAZUCHIKA , KOGANEZAWA TOMOKI
IPC分类号： F23R3/28 , F02C3/30 , F02C7/08
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor equipped with a fuel nozzle and a fuel nozzle header forming a coaxial jet of fuel and air wherein thermal stress generated in the fuel nozzle header is restrained and the service life is elongated. SOLUTION: The gas turbine combustor is formed so that a fuel jet injected from the plurality of fuel nozzles in the fuel nozzle header and an air jet injected from a plurality of air holes of an air hole plate are in the form of the coaxial jet. A mounting hole 40 for arranging the fuel nozzle 31 in the fuel nozzle header 30 is provided, a space part of an air layer 42 or a hollow cylindrical heat insulating layer 44 is arranged between an outer peripheral side of the fuel nozzle and an inner peripheral side of the mounting hole in the inside of the mounting hole of the fuel nozzle header, a fitting means fitted with the mounting hole of the fuel nozzle header or an end face of the fuel nozzle header opening the mounting hole is arranged on a rear end of the fuel nozzle, and the fuel nozzle is fixed to the fuel nozzle header. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种装备有燃料喷嘴和燃料喷嘴头的燃气轮机燃烧室，其形成同时喷射的燃料和空气，其中在燃料喷嘴集管中产生的热应力被限制并且使用寿命延长。解决方案：燃气轮机燃烧器形成为使得从燃料喷嘴头中的多个燃料喷嘴喷射的燃料喷射和从空气孔板的多个气孔喷射的空气喷射的形式为同轴射流设置用于将燃料喷嘴31配置在燃料喷嘴集管30内的安装孔40，在燃料喷嘴的外周侧和内周侧配置有空气层42或中空圆筒状隔热层44的空间部安装孔位于燃料喷嘴集管的安装孔的内侧，装配有燃料喷嘴集管的安装孔的装配装置或打开安装孔的燃料喷嘴集管的端面设置在后端并且燃料喷嘴固定到燃料喷嘴头。版权所有（C）2009，JPO＆INPIT

7. 发明专利

JP2006189252A Gas turbine combustor and method for operating gas turbine combustor 有权
标题翻译：气体涡轮机燃烧器和操作气体涡轮机的方法
公开(公告)号：JP2006189252A
公开(公告)日：2006-07-20
申请号：JP2006101397
申请日：2006-04-03
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： INOUE HIROSHI , KOGANEZAWA TOMOKI , KOBAYASHI SHIGEYOSHI , TAKEHARA ISAO
IPC分类号： F23R3/28 , F02C7/232 , F23R3/10
摘要： PROBLEM TO BE SOLVED: To improve stability of fire in a combustion chamber, low NOx and combustion stability by reducing NOx and promoting mixture of fuel and air, in gas turbine equipment. SOLUTION: This gas turbine equipment is provided with the combustion chamber to which fuel and air are supplied. The gas turbine equipment is characterized by that the fuel and air are formed into a plurality of coaxial jet flows to be supplied to the combustion chamber; and, within a premixing flow passage, an air flow is formed on the outer peripheral side with a fuel flow as a center. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：在燃气轮机设备中，通过减少NOx并促进燃料和空气的混合，提高燃烧室内火灾的稳定性，降低NOx和燃烧稳定性。解决方案：该燃气轮机设备设置有供应燃料和空气的燃烧室。燃气轮机设备的特征在于，燃料和空气形成为多个同轴喷射流以供应到燃烧室; 并且在预混合流路内以燃料流为中心在外周侧形成有气流。版权所有（C）2006，JPO＆NCIPI

8. 发明专利

JP2003148734A GAS TURBINE COMBUSTOR AND METHOD FOR OPERATING GAS TURBINE COMBUSTOR 有权
公开(公告)号：JP2003148734A
公开(公告)日：2003-05-21
申请号：JP2002247951
申请日：2002-08-28
申请人： HITACHI LTD
发明人： INOUE HIROSHI , KOGANEZAWA TOMOKI , KOBAYASHI SHIGEYOSHI , TAKEHARA ISAO
IPC分类号： F23R3/28 , F02C7/057 , F02C9/26 , F23R3/12 , F23R3/26 , F23R3/46
摘要： PROBLEM TO BE SOLVED: To improve stability of a fire in a combustion chamber, low NOx and combustion stability by reducing NOx and promoting mixture of fuel and air, in gas turbine equipment. SOLUTION: This gas turbine equipment is provided with the combustion chamber to which fuel and air are supplied. The fuel and air are made a plurality of coaxial jet flows to be supplied to the combustion chamber. Within a premixing flow passage, an air flow is formed on the outer peripheral side with a fuel flow as a center. As a result, the gas turbine combustor improving low NOx and combustion stability and the method for operating the gas turbine combustor is provided.

9. 发明专利

JPH11148370A GAS TURBINE 失效
公开(公告)号：JPH11148370A
公开(公告)日：1999-06-02
申请号：JP31482197
申请日：1997-11-17
申请人： HITACHI LTD
发明人： KOGANEZAWA TOMOKI , INOUE HIROSHI , KOBAYASHI SHIGEYOSHI , ITO KAZUYUKI , NAGABUCHI NAOYUKI , YOSHIDA SHOHEI , HIRATA YOSHITAKA , ENAMI TAKAFUMI
IPC分类号： F02C7/00 , F02C9/00 , F02C9/28 , F23R3/00 , F23R3/46
摘要： PROBLEM TO BE SOLVED: To uniform temperature of combustion gas generated by each combustor, and to ristrain thermal stress fluctuation of turbine blades by measuring pressure difference between all or parts of combustors in a gas turbine equipped with plural combustors. SOLUTION: A gas turbine has plural combustors 1 which combust fuel under compressed air supply to generate high temperature gas, and these combustors 1 are arranged circularly around the axis of the gas turbine. The adjacent combustors 1 are interconnected through a connecting tube 2, and combustion gas is flown through flame propagation tubes in the connecting tubes 2 according to pressure difference between the both end combustors 1. In this case, a connector 11 for branch is mounted on the outer end of a pressure guide tube 10 connected with each combustor 1, with which a differential pressure gauge 12 for measuring pressure difference between adjacent combustors. On the basis of the measured pressure difference information, unbalance of combustion condition is detected, and combustors 1 are controlled to eliminate this unbalance.

10. 发明专利

JPH09329336A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH09329336A
公开(公告)日：1997-12-22
申请号：JP14888896
申请日：1996-06-11
申请人： HITACHI LTD
发明人： HIRATA YOSHITAKA , YOSHIDA SHOHEI , INOUE HIROSHI , KOGANEZAWA TOMOKI , OTSUKA MASAYA , MUROTA TOMOYA , MORIWAKI BUNJI
IPC分类号： F23R3/22 , F23D14/26 , F23R3/48
摘要： PROBLEM TO BE SOLVED: To prevent the burning loss of a flame propagating tube upon load operation without reducing a combustion gas temperature by a method wherein the entering of air into the flame propagating tube is prevented upon ignition while air is introduced into the flame propagating tube after finishing the ignition. SOLUTION: Combustion gas 12 is injected into a gas turbine 2 through a transition piece 10 to drive the gas turbine 2. A flame propagating tube 8 is inserted into an inner cylinder 5 and a cover 17, made of a bidirectional shape memory alloy, is installed on a plurality of cooling ports 16, formed on the flame propagating tube 8 to deform the cover 17 by the shape memory effect thereof and open or close the cooling ports 16. The cover 17 is attached so as to close the cooling ports 16 of the flame propagating tube 8 upon igniting a combustor to preclude the inflow of compressed air 11 into the flame propagating tube 8 through the cooling ports 16. Upon load operation, the cooling ports 16 are brought into opened condition and, as a result, the compressed air 11 flows into the flame propagating tube 8 through the cooling ports 16 whereby the temperature rise of the flame propagating tube 8 due to high-temperature combustion gas can be prevented.

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