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1. 发明专利

JP2005226849A Gas turbine combustor and its combustion air supply method 审中-公开
标题翻译：气体涡轮搅拌机及其燃烧空气供应方法
公开(公告)号：JP2005226849A
公开(公告)日：2005-08-25
申请号：JP2004032944
申请日：2004-02-10
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ITO KAZUYUKI , TAKEHARA ISAO , SASAO TOSHIBUMI , YOSHIDA SHOHEI , HIRATA YOSHITAKA
IPC分类号： F23R3/06 , F23R3/14 , F23R3/30
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor and its combustion air supply method capable of reducing the environmental load without impairing ignition characteristic and combustion stability.
SOLUTION: This gas turbine combustor comprises a combustion chamber liner 1, an air revolving unit 2 mounted near a shaft central part at an upstream part of the combustion chamber liner, a fuel nozzle 3 for jetting the fuel from the neighborhood of the air revolving unit 2, a double wall conical member 5 mounted at an outer peripheral side of the air revolving unit 2 and the fuel nozzle 3 at the upstream part of the combustion chamber liner 1 and having a plurality of slits 24 for introducing the combustion air, and a combustion air jetting port 6 formed between the air revolving unit 2 and the double wall conical member 5, and jetting out the combustion air 800 into the combustion chamber liner 1 in a state of hardly interfering a low flow rate circulation flow area 300 formed at a downstream area of the double wall conical member 5.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种能够降低环境负荷而不损害点火特性和燃烧稳定性的燃气轮机燃烧器及其燃烧空气供给方法。解决方案：该燃气轮机燃烧器包括燃烧室衬套1，安装在燃烧室衬套的上游部分处的轴中心部附近的空气回转单元2，用于从燃烧室衬里附近喷射燃料的燃料喷嘴3 空气旋转单元2，安装在空气旋转单元2的外周侧的双壁锥形构件5和位于燃烧室衬套1的上游部分处的燃料喷嘴3，并且具有多个用于引入燃烧空气的狭缝24 以及形成在空气回转单元2和双壁锥形构件5之间的燃烧空气喷射口6，并且在几乎不干扰低流量循环流量区域300的状态下将燃烧空气800喷射到燃烧室衬套1中形成在双壁锥形构件5的下游区域。版权所有（C）2005，JPO＆NCIPI

2. 发明专利

JP2004138376A Gas turbine combustor, combustion method of gas turbine combustor, and remodeling method of gas turbine combustor 有权
公开(公告)号：JP2004138376A
公开(公告)日：2004-05-13
申请号：JP2003086757
申请日：2003-03-27
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： HAYASHI AKINORI , INAGE SHINICHI , KOIZUMI HIROMI , TAKEHARA ISAO , ITO KAZUYUKI , SASAO TOSHIBUMI , MURATA EITARO
IPC分类号： F23R3/10 , F02C3/30 , F23R3/00 , F23R3/16 , F23R3/18 , F23R3/32 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To perform proper combustion with reduced NOx in a combustor usable of gas fuel and liquid fuel.
SOLUTION: This gas turbine combustor comprises a premixing combustion burner arranged on the circumference of a pilot burner and a substantially cylindrical combustor inner cylinder wall arranged on the downstream side of the premixing combustion burner and having a combustion chamber formed in the inner part. This combustor further comprises flame holding devices radially arranged at the outlet of the premixing combustion burner, a fuel injection means for injecting at least one of gas fuel and liquid fuel, and a plurality of air nozzle holes for blowing air to the combustion chamber, which are provided on the outside of the pilot burner and on the inside of the premixing combustion burner. According to such a structure, proper combustion with reduced NOx can be performed in the combustor usable of gas fuel and liquid fuel.
COPYRIGHT: (C)2004,JPO

3. 发明专利

JP2005106351A Gas turbine combustor 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2005106351A
公开(公告)日：2005-04-21
申请号：JP2003339045
申请日：2003-09-30
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： SASAO TOSHIBUMI , TAKEHARA ISAO , WATANABE YASUYUKI , YAMANOBE TAKUMI , AKATSU FUMIHIKO , ITO KAZUYUKI
IPC分类号： F23R3/08 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To reduce an air flow rate slipping through from a fitting and connecting part of a combustion chamber liner and a transition piece, to approximately uniformize distribution in a circumferential direction of a cooling air flow rate on the combustion chamber liner, thus to increase a fuel air flow rate, leading to reduction in NOx discharge amount, and to suppress increase in metal temperature at a terminal of the combustion chamber liner.
SOLUTION: The combustion chamber liner 2 is connected with the transition piece 3 in a fitting structure, and an air flow passage is formed outside the combustion chamber liner 2 and the transition piece 3. At the fitting and connecting position, flow passage width in a radial direction of the air flow passage is set small in the transition piece 3 side, and is set large in the combustion chamber liner 2 side, creating a step 300. A partition wall (ring) 100 serving as resistance to an air flow is provided on an outer wall of the combustion chamber liner 2 in the vicinity of a terminal of the transition piece 3 at the fitting and connecting position.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题为了减少从燃烧室衬套和过渡件的装配和连接部分滑过的空气流量，大致均匀化在燃烧室上的冷却空气流量的圆周方向上的分布从而增加燃料空气流量，导致NOx排出量的降低，并且抑制燃烧室衬套的端子处的金属温度升高。解决方案：燃烧室衬套2与过渡件3以配合结构连接，并且在燃烧室衬套2和过渡件3之外形成空气流动通道。在配合和连接位置，流动通道空气流路的径向的宽度在过渡件3侧被设定得较小，并且在燃烧室衬垫2侧被设定得较大，形成了台阶300.用作空气阻力的隔壁（环）100 在装配和连接位置处在过渡件3的端子附近在燃烧室衬套2的外壁上设置有流动。版权所有（C）2005，JPO＆NCIPI

4. 发明专利

JP2004211558A Gas turbine combustor, fuel injection nozzle and fuel injection method of gas turbine combustor 有权
公开(公告)号：JP2004211558A
公开(公告)日：2004-07-29
申请号：JP2002378873
申请日：2002-12-27
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ITO KAZUYUKI , YOSHIDA SHOHEI , HIRATA YOSHITAKA , MUROTA TOMOYA , TAKEHARA ISAO , SASAO TOSHIBUMI
IPC分类号： F02C3/30 , F02C7/232 , F23R3/28 , F23R3/30 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To attain combustion stability up to the middle of speed-up from ignition; and to reduce delivery pressure of a fuel supply pump without arranging large-scale equipment such as a large capacity compressor and a heat exchanger applied to an air assist type liquid fuel injection nozzle in a dual orifice type liquid fuel injection nozzle for a gas turbine combustor.
SOLUTION: Air is introduced up to the middle of speed-up from ignition by connecting a pipe for introducing the air to the downstream side of a pressurizing valve arranged on the upstream side of a main nozzle. Combustion air is turned by arranging a turning unit outside the fuel injection nozzle, and the combustion air is turned by contacting with the combustion chamber side tip of the fuel injection nozzle.
COPYRIGHT: (C)2004,JPO&NCIPI

5. 发明专利

JP2007033025A Gas turbine combustor, combustion method for gas turbine combustor, and method of modifying gas turbine combustor 审中-公开
标题翻译：气体涡轮机燃烧器，燃气轮机燃烧器的燃烧方法和燃气涡轮机燃烧器的改造方法
公开(公告)号：JP2007033025A
公开(公告)日：2007-02-08
申请号：JP2006299797
申请日：2006-11-06
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： HAYASHI AKINORI , INAGE SHINICHI , KOIZUMI HIROMI , TAKEHARA ISAO , ITO KAZUYUKI , SASAO TOSHIBUMI , MURATA EITARO
IPC分类号： F23R3/34 , F23R3/00 , F23R3/14 , F23R3/18 , F23R3/28 , F23R3/32 , F23R3/48
摘要： PROBLEM TO BE SOLVED: To carry out proper combustion in a combustor capable of using gas fuel and liquid fuel, and to reduce NOx.
SOLUTION: This gas turbine combustor provided with a premixed combustion burner arranged in an outer circumference of a pilot burner, and a substantially cylindrical combustor inner cylinder wall arranged in a downstream of the premixed combustion burner, and for forming a combustion chamber in its inside, is provided with flame stabilizers radially arranged in an outlet of the premixed combustion burner, and a fuel injection means for injecting at least one of the gas fuel and the liquid fuel, in the pilot burner, and a plurality of air injection nozzles for injecting air to an inside of the premixed combustion burner, in an outside of the pilot burner.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：在能够使用气体燃料和液体燃料的燃烧器中进行适当的燃烧并且减少NOx。解决方案：该燃气轮机燃烧器设置有布置在引燃燃烧器的外周的预混合燃烧器，以及布置在预混合燃烧器下游的大致圆柱形的燃烧器内筒壁，并且用于形成燃烧室其内部设置有径向布置在预混合燃烧器的出口中的火焰稳定器，以及用于在引燃燃烧器中喷射气体燃料和液体燃料中的至少一种的燃料喷射装置，以及多个空气喷射喷嘴用于在引燃燃烧器的外部将空气喷射到预混燃烧器的内部。版权所有（C）2007，JPO＆INPIT

6. 发明专利

JP2004156860A Gas turbine combustor 有权
公开(公告)号：JP2004156860A
公开(公告)日：2004-06-03
申请号：JP2002323784
申请日：2002-11-07
申请人： Chubu Electric Power Co Inc , Hitachi Ltd , 中部電力株式会社 , 株式会社日立製作所
发明人： TAKEHARA ISAO , ICHIKAWA KUNIHIRO , ITO KAZUYUKI , HIRANO RYUICHI , KIDA RYOSUKE
IPC分类号： F23R3/08 , F23R3/48
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor reducing cooling air flow rate while maintaining metal temperature of a combustion chamber liner within an appropriate range.
SOLUTION: This gas turbine combustor is constituted by connecting a plurality of can type combustors with cross fire pipes. The can type combustor has the combustion chamber liner 20 on which a connection part of the cross fire pipe is arranged. A plurality of combustion holes 30a, 30b and cooling holes 40a, 40b, 40c for cooling the combustion chamber liner are arranged on the combustion chamber liner 20, and the combustion holes 30a, 30b are circumferentially dispersedly arranged thereon at axial positions approximately at the same position as the cross fire pipe connection parts 101. In addition to the cooling holes 40a, 40b, 40c, cooling hole columns 50a, 50b are also provided, and the cooling holes are more densely arranged on the axial area in the vicinity of the cross fire pipe connection part 101 of the combustion chamber liner 20 than other portions.
COPYRIGHT: (C)2004,JPO

7. 发明专利

JP2007218487A Gas turbine combustor 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2007218487A
公开(公告)日：2007-08-30
申请号：JP2006038705
申请日：2006-02-16
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ICHIKAWA KUNIHIRO , ITO KAZUYUKI , WATANABE YASUYUKI , ENDO HIROYUKI
IPC分类号： F23R3/28 , F02C7/24
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of relieving heat stress generated by temperature difference between compressed air and fuel around a fuel flow channel intersecting with the flow of the compressed air, and preventing generation of cracking.
SOLUTION: This combustor 1 for burning the compressed air A discharged from a compressor 100 with the fuel F, comprises a liner 7 forming a combustion chamber 6 for burning the fuel F with the compressed air A, a flange 26 disposed at an upstream side in the fuel gas jetting direction, of the liner 7, and having a circular flow channel 35 on its inner peripheral portion, and a fuel introduction flow channel 36 inside of plate thickness for introducing the fuel gas F from a fuel system to the circular flow channel 35 from a radial outer side, a plurality of fuel nozzles 22 disposed on the flange 26 to allow fuel injection holes 37 to direct to the combustion chamber 6, and jetting the fuel gas F flowing in the circular flow channel 36 toward the combustion chamber 6, and a heat shield pipe 40 inserted into the fuel introduction flow channel 36 of the flange 26.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：解决的问题：提供一种燃气轮机燃烧器，其能够缓和由与压缩空气的流动相交的燃料流路的压缩空气和燃料之间的温度差产生的热应力，并且防止产生裂纹。解决方案：用于燃烧由燃料F从压缩机100排出的压缩空气A的燃烧器1包括形成用于用压缩空气A燃烧燃料F的燃烧室6的内衬7，衬套7的燃料气体喷射方向的上游侧，其内周部具有圆形的流动通道35，以及用于将燃料气体F从燃料系统引入到燃料系统的板厚内部的燃料引入流动通道36 从径向外侧的圆形流动通道35，设置在凸缘26上的多个燃料喷嘴22，以允许燃料喷射孔37引导到燃烧室6，并且将在圆形流动通道36中流动的燃料气体F喷射到燃烧室6和插入凸缘26的燃料引入流动通道36中的隔热管40。版权所有（C）2007，JPO＆INPIT

8. 发明专利

JP2007205215A Control method for gas turbine, and control device for gas turbine 有权
标题翻译：用于气体涡轮机的控制方法和用于气体涡轮机的控制装置
公开(公告)号：JP2007205215A
公开(公告)日：2007-08-16
申请号：JP2006024048
申请日：2006-02-01
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： HIRATA YOSHITAKA , YOSHIDA SHOHEI , TAKAHASHI YASUO , SASAO TOSHIBUMI , INOUE HIROSHI , MURATA EITARO , ITO KAZUYUKI
IPC分类号： F02C7/042 , F01D17/00 , F02C7/18 , F04D27/00 , F04D29/56
CPC分类号： F02C9/54 , F02C7/22 , F02C7/2365 , F02C9/20 , F05D2270/08 , F05D2270/083 , F05D2270/303 , F05D2270/304 , F23N2035/06 , F23N2041/20 , F23R3/26
摘要： PROBLEM TO BE SOLVED: To suppress an amount of generation of soot and dust in a partial load area, while enjoying an advantage of a pressure spraying type liquid fuel nozzle.
SOLUTION: A combustor is provided with a pressure spraying type liquid fuel nozzle. A working fluid flow rate of a compressor is reduced with respect to a working fluid flow rate of a compressor set so that the performance of the compressor becomes the highest in the partial load area of the gas turbine. The amount of generation of soot and dust in the partial load area is thereby suppressed, while enjoying the advantage of the pressure spraying type liquid fuel nozzle.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：解决问题：在享受压力喷射型液体燃料喷嘴的优点的同时，抑制部分负荷区域中的烟灰和灰尘的产生量。解决方案：燃烧器设置有压力喷射型液体燃料喷嘴。相对于压缩机组的工作流体流量，压缩机的工作流体流量减小，使得压缩机的性能在燃气轮机的部分负载区域中变得最高。由此，能够在享受压力喷射式液体燃料喷嘴的优点的同时，抑制部分负荷区域中的烟尘的产生量。版权所有（C）2007，JPO＆INPIT

9. 发明专利

JP2007064625A Gas turbine combustor and its fuel supply method 有权
标题翻译：燃气轮机及其燃油供应方法
公开(公告)号：JP2007064625A
公开(公告)日：2007-03-15
申请号：JP2006332911
申请日：2006-12-11
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： YOSHIDA SHOHEI , HIRATA YOSHITAKA , ITO KAZUYUKI , MUROTA TOMOYA , INOUE HIROSHI , ASAI TOMOHIRO
IPC分类号： F23R3/10 , F02C7/22 , F23R3/28 , F23R3/34 , F23R3/36
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor and its fuel supply method capable of preventing backfire, while reducing an NOx generation quantity. SOLUTION: This combustor 2 for mixing a fuel with combustion air introduced from a compressor 1 and burning it, and supplying generated combustion gas to a gas turbine 3 is equipped with a liquid fuel nozzle 13 for blowing out the fuel; a mixing chamber wall 5 equipped with the liquid fuel nozzle 13 in the center, having a hollow circular-cone shape enlarged toward the blowout direction, and forming a mixing chamber 4 inside; a plurality of air introduction holes 14, 15, 16 bored on the mixing chamber wall 5 so that the combustion air is introduced into the mixing chamber 4, and that simultaneously its introduction angle is deflected at least toward the circumferential direction of the mixing chamber wall 5; and each gas fuel nozzle 17 provided respectively oppositely to the plurality of air introduction holes 14, 15, 16 on the peripheral side of the mixing chamber wall 5, for blowing out the fuel approximately in the same axial direction as axial lines L1, L2, L3 of the air introduction holes 14, 15, 16. COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够在减少NOx生成量的同时防止回火的燃气轮机燃烧器及其燃料供给方法。解决方案：用于将燃料与从压缩机1引入的燃烧空气混合并将其燃烧并将生成的燃烧气体供应到燃气轮机3的燃烧器2配备有用于吹出燃料的液体燃料喷嘴13; 在中央配备有液体燃料喷嘴13的混合室壁5，具有朝向吹出方向扩大的中空圆锥形状，在内部形成混合室4; 在混合室壁5上钻出的多个空气导入孔14,15,16，使得燃烧空气被引入到混合室4中，同时其引入角度至少朝向混合室壁的圆周方向偏转 5; 以及与混合室壁5的周边侧的多个空气导入孔14,15,16分别相对地设置的各气体燃料喷嘴17，用于沿与轴线L1，L2相同的轴线吹出燃料，空气导入孔14,15,16的L3。版权所有（C）2007，JPO＆INPIT

10. 发明专利

JP2005147459A Gas turbine combustor and method of supplying fuel to it 审中-公开
标题翻译：燃气轮机及其燃料供应方法
公开(公告)号：JP2005147459A
公开(公告)日：2005-06-09
申请号：JP2003383259
申请日：2003-11-13
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： HIRATA YOSHITAKA , YOSHIDA SHOHEI , ITO KAZUYUKI , INOUE HIROSHI , MUROTA TOMOYA
IPC分类号： F23R3/28 , F02C7/22 , F23R3/26 , F23R3/36
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor and method of supplying fuel to it, increasing a mixing characteristic of liquid fuel to air.
SOLUTION: This gas turbine combustor that mixes liquid fuel and gas fuel with air for combustion comprises a mixing chamber 4 being formed in approximately conical shape expanding toward the downstream side and having a plurality of air introduction holes on the side wall part, a liquid fuel nozzle 10 being placed on the upstream side of the mixing chamber 4 and injecting the liquid fuel to the inner wall surface of the air introduction hole 17 for collision, and gas fuel nozzles 9 being arranged opposite to the air introduction holes 17-19, injecting the gas fuel approximately coaxially with the axes of the air introduction holes 17-19, and supplying the gas fuel inside the mixing chamber 4 via the air introduction holes 17-19.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种燃气轮机燃烧器和向其供给燃料的方法，提高液体燃料与空气的混合特性。解决方案：将液体燃料和气体燃料与用于燃烧的空气混合的燃气轮机燃烧器包括形成为朝向下游侧扩张的大致圆锥形的混合室4，并且在侧壁部分上具有多个空气引入孔，液体燃料喷嘴10被放置在混合室4的上游侧，并且将液体燃料喷射到用于碰撞的空气引入孔17的内壁表面，气体燃料喷嘴9与空气引入孔17- 如图19所示，将气体燃料与空气导入孔17-19的轴线大致同轴地喷射，并且经由空气导入孔17-19向混合室4供给气体燃料。版权所有（C）2005，JPO＆NCIPI

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