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1. 发明专利

JP2012251742A Fuel injector 有权
标题翻译：喷油器
公开(公告)号：JP2012251742A
公开(公告)日：2012-12-20
申请号：JP2011125481
申请日：2011-06-03
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社 , Japan Aerospace Exploration Agency , 独立行政法人宇宙航空研究開発機構
发明人： MATSUYAMA TATSUSUKE , KOBAYASHI MASAYOSHI , ODA TAKEO , HORIKAWA ATSUSHI , HAYASHI SHIGERU , SHIMODAIRA KAZUO , MATSUURA KAZUAKI , YAMADA SHUJI , KUROSAWA YOJI , FUJIWARA HITOSHI
IPC分类号： F23R3/28 , F23D14/24 , F23R3/14 , F23R3/16 , F23R3/30
CPC分类号： F23R3/343 , F23R3/286
摘要： PROBLEM TO BE SOLVED: To provide a fuel injector which can improve the combustion efficiency, the ignitability and the flame holding performance of a pilot injection valve at low output without a pilot combustion zone and a main combustion zone largely separating.SOLUTION: The fuel injector includes a pilot injection valve 6, which so sprays fuel as to form a diffused combustion zone A1 in a combustion chamber 4, and a main injection valve 8, which is provided coaxially with the pilot injection valve 6 to surround the pilot injection valve 6 and supplies premixed gas between fuel and air to form a premixed combustion zone A2 within the combustion chamber 4. The pilot injection valve 6 has a center nozzle 20, which ejects air jet that goes straight axially on the central axis, an inside swirler 30, which is positioned outside in its radial direction to give swirl around the axis of the pilot injection valve 6 to the air that flows in, and a pilot fuel injecting portion 22a, which injects fuel to an air flow within the center nozzle 20 from between the center nozzle 20 and the inside swirler 30.
摘要翻译：要解决的问题：提供一种燃料喷射器，其可以在没有先导燃烧区和主燃烧区大分离的情况下，在低输出下提高先导喷射阀的燃烧效率，点火性和火焰保持性能。解决方案：燃料喷射器包括先导喷射阀6，其在燃烧室4中喷射燃料以形成扩散燃烧区域A1，以及与喷油阀6同轴设置的主喷射阀8 以围绕引燃喷射阀6并在燃料和空气之间提供预混合气体，以在燃烧室4内形成预混合燃烧区域A2。引燃喷射阀6具有中心喷嘴20，该中心喷嘴20喷射在中心轴线，内旋流器30，其位于径向外侧，以使引导喷射阀6的轴线围绕流入的空气旋转;以及引燃燃料喷射部分22a，其将燃料喷射到内部的空气流中中心喷嘴20在中心喷嘴20和内部旋流器30之间。版权所有（C）2013，JPO＆INPIT

2. 发明专利

JP2012137380A Sampling device for combustion gas from combustor for gas turbine engines 有权
标题翻译：用于燃气涡轮机发动机燃烧气体的采样装置
公开(公告)号：JP2012137380A
公开(公告)日：2012-07-19
申请号：JP2010289725
申请日：2010-12-27
申请人： Japan Aerospace Exploration Agency , Kawasaki Heavy Ind Ltd , 川崎重工業株式会社 , 独立行政法人宇宙航空研究開発機構
发明人： KOBAYASHI MASAYOSHI , YAMADA HIDESHI , SHIMODAIRA KAZUO , YAMAMOTO TAKESHI , YAMAGUCHI KENTA
IPC分类号： G01N1/22 , G01M15/10 , G01N1/28
摘要： PROBLEM TO BE SOLVED: To provide a sampling device that can endure environment of high temperature and high pressure.SOLUTION: In a device 2 for sampling combustion gas G discharged from a combustor 12 for gas turbine engines, an inlet unit 11 has a gas inlet passage GP for letting in the combustion gas G discharged from the combustor 12 and a cooling passage CP for letting cooling water C for cooling the gas inlet passage GP flow; a drive mechanism K causes the inlet unit 11 to rotate around its axial part 30; a supporting unit 34 has a gas communicating path 77 and cooling water communicating paths 81 and 83 respectively communicating with the gas inlet passage GP and the cooling passage CP of the inlet unit 11, and the axial part 30 is rotatably linked to it; to the supporting unit 34, a gas outlet pipe 98 for letting the combustion gas G out, a cooling water inlet pipe 78 for letting in the cooling water C from outside and a cooling water outlet pipe 96 for letting the cooling water C out are connected.
摘要翻译：要解决的问题：提供可承受高温高压环境的取样装置。解决方案：在用于对从燃气涡轮发动机的燃烧器12排出的燃烧气体G进行采样的装置2中，入口单元11具有用于使从燃烧器12排出的燃烧气体G中的冷却通道用于使用于冷却气体入口通道GP的冷却水C的流量; 驱动机构K使入口单元11围绕其轴向部分30旋转; 支撑单元34具有分别与进气通道GP和入口单元11的冷却通道CP连通的气体连通路径77和冷却水连通路径81和83，并且轴向部分30可旋转地连接到其上; 连接到支撑单元34，连接用于使燃烧气体G输出的气体出口管98，用于从外部排出冷却水C的冷却水入口管78和用于使冷却水C出出的冷却水出口管96 。版权所有（C）2012，JPO＆INPIT

3. 发明专利

JP2012251741A Fuel injector 有权
标题翻译：喷油器
公开(公告)号：JP2012251741A
公开(公告)日：2012-12-20
申请号：JP2011125480
申请日：2011-06-03
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社 , Japan Aerospace Exploration Agency , 独立行政法人宇宙航空研究開発機構
发明人： MATSUYAMA TATSUSUKE , KOBAYASHI MASAYOSHI , ODA TAKEO , HORIKAWA ATSUSHI , HAYASHI SHIGERU , SHIMODAIRA KAZUO , MATSUURA KAZUAKI , YAMADA SHUJI , KUROSAWA YOJI , FUJIWARA HITOSHI
IPC分类号： F23R3/16 , F23D14/24 , F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23R3/286 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a fuel injector, which can achieve NOx reduction by mixing air and fuel enough at middle output and at high output when a main injection valve is operated without complicating the fuel injector or a control mechanism.SOLUTION: The fuel injector includes a pilot injection valve 6, which so sprays fuel to form a pilot combustion zone A1 in a combustion chamber 4, and a main injection valve 8, which is provided coaxially with the pilot injection valve 6 to surround the pilot injection valve 6 and supplies premixed gas between fuel and air to form a premixed combustion zone A2 within the combustion chamber 4. The main injection valve 8 has the first air passage 38, which takes in air at flow velocity that has an axial main component, the second air passage 42, which takes in air at flow velocity that has a radial main component to join it with air from the first air passage 38, and a main fuel injecting portion 40, which injects fuel to only the second air passage 42.
摘要翻译：要解决的问题：提供一种燃料喷射器，其可以在主喷射阀在不使燃料喷射器或控制机构复杂化的情况下在中间输出和高输出时混合空气和燃料来实现NOx还原。解决方案：燃料喷射器包括一个先导喷射阀6，其喷射燃料以在燃烧室4中形成先导燃烧区A1，以及与喷油阀6同轴设置的主喷射阀8，围绕引燃喷射阀6，并在燃料和空气之间提供预混合气体，以在燃烧室4内形成预混合燃烧区域A2。主喷射阀8具有第一空气通道38，其以具有轴向主要部件，第二空气通道42，其以具有径向主要部件的流速的空气以与来自第一空气通道38的空气接合的空气;以及主燃料喷射部分40，其仅向第二空气喷射燃料通过42.版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2006258041A Gas turbine combustor and its igniting method 有权
标题翻译：燃气轮机及其点火方法
公开(公告)号：JP2006258041A
公开(公告)日：2006-09-28
申请号：JP2005078730
申请日：2005-03-18
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： KOBAYASHI MASAYOSHI , NINOMIYA HIROYUKI , ODA TAKEO
IPC分类号： F02C7/264 , F23R3/32 , F23R3/34
CPC分类号： F23R3/28 , F23D2206/10 , F23D2207/00 , F23R3/14 , F23R3/343 , F23R3/50 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor having simple construction for improving igniting performance while maintaining lower NOx combustion and high combustion efficiency.
SOLUTION: The gas turbine combustor 1 comprises fuel nozzles 2A, 2B having pilot fuel injection valves 4 and main fuel injection valves 7A, 7B, respectively. The fuel nozzle 2A is arranged right near an igniter 8. It has a local fuel injection hole 19a for injecting fuel F from the main fuel injection valve 7A at its predetermined position in an air flow path 24 at least during ignition with the igniter 8 to form a flammable mixture zone S3 near the igniter 8.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：解决问题：提供一种具有简单结构的燃气轮机燃烧器，用于提高点火性能，同时保持较低的NOx燃烧和高燃烧效率。解决方案：燃气轮机燃烧器1包括分别具有先导燃料喷射阀4和主燃料喷射阀7A，7B的燃料喷嘴2A，2B。燃料喷嘴2A配置在靠近点火器8的位置。它具有一个局部燃料喷射孔19a，用于将燃料F从主燃料喷射阀7A喷射到空气流路24中的预定位置，至少在点火器8点火到在点火器8附近形成易燃混合区域S3。版权所有（C）2006年，JPO＆NCIPI

5. 发明专利

JP2005265232A Gas turbine combustor 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2005265232A
公开(公告)日：2005-09-29
申请号：JP2004075609
申请日：2004-03-17
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： NINOMIYA HIROYUKI , ODA TAKEO , KOBAYASHI MASAYOSHI
IPC分类号： F23R3/50 , F02C7/266 , F23R3/00 , F23R3/06 , F23R3/28 , F23R3/30
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of making low NOx combustion and excellent ignition performance and stable combustion compatible.
SOLUTION: This gas turbine combustor 1 is provided with an annular combustion cylinder 2 for forming a combustion chamber 2a inside it, a fuel supply device 3 for supplying fuel F into the combustion chamber 2a, and an igniter 4. The fuel supply device 3 is provided with a premixing fuel nozzle 7 for mixing fuel F with air A and then supplying the mixture into the combustion chamber 2a to perform premixing combustion and a diffusion fuel nozzle 6 for injecting fuel F into the combustion chamber 2a and mixing it with air A to perform diffusion combustion. The diffusion fuel nozzle 6 is arranged in the vicinity of the igniter 4.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：解决的问题：提供一种能够进行低NOx燃烧和优异的点火性能和稳定的燃烧兼容的燃气轮机燃烧器。解决方案：该燃气轮机燃烧器1设置有用于在其内部形成燃烧室2a的环形燃烧气缸2，用于将燃料F供应到燃烧室2a中的燃料供给装置3和点火器4.燃料供给设备3设置有用于将燃料F与空气A混合的预混合燃料喷嘴7，然后将混合物供应到燃烧室2a中以进行预混合燃烧;以及扩散燃料喷嘴6，用于将燃料F喷射到燃烧室2a中并将其与空气A进行扩散燃烧。扩散燃料喷嘴6布置在点火器4附近。版权所有（C）2005，JPO＆NCIPI

6. 发明专利

JP2005180730A Atomization improving device of fuel injection valve 有权
标题翻译：燃料喷射阀装置的改进
公开(公告)号：JP2005180730A
公开(公告)日：2005-07-07
申请号：JP2003418729
申请日：2003-12-16
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： ODA TAKEO , NINOMIYA HIROYUKI , KOBAYASHI MASAYOSHI
IPC分类号： F23R3/30 , F02C7/232 , F23R3/10 , F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F23R3/14
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine and an airplane engine for preventing degradation of atomization performance of fuel at a low load time of a premixing/prevaporization lean combustion system combustor.
SOLUTION: A combustibility improving device of a premixed-fuel injection valve includes an air flow path 11 added on an inner circumferential side of air flow paths 4a, 4b for fuel combustion of a combustor liner head part. Main fuel is injected from a main fuel injection hole 7 provided on the way of a partitioning wall 13 between the added air flow path 11 and an air flow path 4b for fuel combustion in an outer circumferential direction. A swirler 12 for giving turning to a flow of air is provided on the added air flow path 11, and an atomization lip 9 is provided on a tip end part of the partitioning wall 13.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于燃气轮机的燃烧器和用于防止在预混/先蒸发稀燃燃烧系统燃烧器的低负载时间燃料的雾化性能的降低的飞机发动机。解决方案：预混合燃料喷射阀的可燃性提高装置包括在燃烧器衬套头部的燃料燃烧用空气流路4a，4b的内周侧添加有空气流路11。主燃料从设置在分配壁13的路径上的主燃料喷射孔7喷射到附加的气流路径11和用于燃料燃烧的外部气流路径4b之间。在添加的空气流动路径11上设置有用于转向空气流的旋流器12，并且在分隔壁13的前端部设置有雾化唇9。（C）2005，JPO＆NCIPI

7. 发明专利

JP2009192195A Combustor for gas turbine engine 审中-公开
标题翻译：燃气轮机发动机
公开(公告)号：JP2009192195A
公开(公告)日：2009-08-27
申请号：JP2008036104
申请日：2008-02-18
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： KOBAYASHI MASAYOSHI , OGATA HIDEKI
IPC分类号： F23R3/28 , F02C7/228
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine achieved in weight reduction and the improvement of combustion efficiency.
SOLUTION: The combustor for the gas turbine is equipped with an annular burning tube forming a combustion chamber, an annular housing covering the burning tube, and a plurality of fuel injectors arranged in a row in a circumferential direction of the burning tube to inject fuel into the combustion chamber. The combustor is provided with an annular inner fuel manifold supplying fuel to the plurality of fuel injectors, and fuel supply systems of a number smaller than the plurality of fuel injectors supplying the fuel to the inner fuel manifold from an exterior of the burning tube. The inner fuel manifold is arranged in the housing.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种在重量减轻中实现的燃气轮机的燃烧器和提高燃烧效率。解决方案：燃气轮机的燃烧器配备有形成燃烧室的环形燃烧管，覆盖燃烧管的环形壳体和沿着燃烧管的圆周方向排成一列的多个燃料喷射器，将燃料喷入燃烧室。燃烧器设置有向多个燃料喷射器供应燃料的环形内部燃料歧管，以及比从燃烧管的外部向内部燃料歧管供应燃料的多个燃料喷射器数量少的燃料供应系统。内部燃料歧管布置在壳体中。版权所有（C）2009，JPO＆INPIT

8. 发明专利

JP2008298351A Combustion device for gas turbine engine 有权
标题翻译：燃气轮机发动机燃烧装置
公开(公告)号：JP2008298351A
公开(公告)日：2008-12-11
申请号：JP2007144184
申请日：2007-05-30
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： OGATA HIDEKI , KOBAYASHI MASAYOSHI , NAGATOME YOICHI
IPC分类号： F23R3/14 , F23R3/30 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To provide a combustion device for a turbine engine capable of uniforming a distribution of a flame temperature in a combustion chamber by providing the air flowing into an annular swirler with the uniform distribution of flow velocity in the entire circumferential direction in a combined combustion method.
SOLUTION: This combustion device for a gas turbine engine comprises an annular heat chamber 9 forming the combustion chamber 12, a plurality of fuel injection units 2 having premixed air-fuel supply portions 4 for supplying the premixed air-fuel of fuel F and air CA to form premixed air-fuel combustion region 51 in the combustion chamber 12, a fuel supply unit 20 for supplying the fuel F to the premixed air-fuel supply portions 4, and an annular air inlet 14a for introducing the compressed air CA from a compressor to an upstream side of the fuel injection units 2. The fuel injection units 2 have the swirler for swirling the air, fixed to an air intake, and a circumferential width VWH of a front edge portion in a high dynamic pressure area HA opposed to the air inlet 14a, of a plurality of blades 48 arranged in the circumferential direction of the swirler 43, is determined to be larger than that outside of the area.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于涡轮发动机的燃烧装置，其能够通过使流入环形旋流器的空气通过在整个周向上具有均匀分布的流速而均匀化燃烧室中的火焰温度的分布组合燃烧方式的方向。解决方案：这种燃气轮机的燃烧装置包括形成燃烧室12的环形加热室9，多个燃料喷射单元2，其具有用于供给燃料F的预混合空气燃料的预混合空气燃料供应部分4 和空气CA，以在燃烧室12中形成预混合空气燃料燃烧区域51，用于将燃料F供应到预混合空气燃料供应部分4的燃料供应单元20和用于将压缩空气CA引入的环形空气入口14a 从燃料喷射单元2的压缩机到上游侧。燃料喷射单元2具有用于旋转空气的旋转器，固定到进气口，以及在高动态压力区域HA中的前边缘部分的周向宽度V W 与旋流器43的圆周方向上配置的多个叶片48的空气入口14a相对地被确定为大于该区域的外侧。版权所有（C）2009，JPO＆INPIT

9. 发明专利

JP2005188822A Method and mechanism for fuel supply to fuel injection device 有权
标题翻译：燃油供应燃料注入装置的方法和机理
公开(公告)号：JP2005188822A
公开(公告)日：2005-07-14
申请号：JP2003430408
申请日：2003-12-25
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： KOBAYASHI MASAYOSHI , ODA TAKEO , MIYAMOTO HIROAKI , NINOMIYA HIROYUKI
IPC分类号： F23R3/28 , F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide a method and a mechanism for fuel supply to a fuel injection device capable of smoothly assembling a gas turbine and properly supplying air for combustion.
SOLUTION: The fuel supply to the fuel injection device A comprising a fuel injection part 10 having a plurality of fuel injecting members 40, 50 is performed through fuel supply passages 23, 24, 31 and 32, by forming a supply holding part 20 for holding the fuel injection part 10, and a fuel supply communication part 30 for communicating the plurality of fuel injection members 40, 50 and the supply holding part 20, and forming the fuel supply passages 23, 24, 31 and 32 communicated from the supply holding part 20 to each of the fuel injection members 40, 50 through the fuel supply communication part 30.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种燃料喷射装置的燃料供给方法和机构，其能够平稳地组装燃气轮机并适当地供应用于燃烧的空气。解决方案：包括具有多个燃料喷射部件40,50的燃料喷射部10的燃料喷射装置A的燃料供给通过燃料供给通路23,24,31和32进行，通过形成供给保持部 20，用于保持燃料喷射部10的燃料供给连通部30，以及用于连通多个燃料喷射部件40,40和供给保持部20的燃料供给连通部30，以及形成从燃料喷射部20传递的燃料供给通路23,24,31,32。供给保持部20通过燃料供给连通部30向各燃料喷射部件40,50供给。（C）2005年，JPO＆NCIPI

10. 发明专利

JP2005180729A Combustibility improving device of premixed-fuel injection valve 有权
标题翻译：改善燃油喷射阀装置的可燃性
公开(公告)号：JP2005180729A
公开(公告)日：2005-07-07
申请号：JP2003418728
申请日：2003-12-16
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： ODA TAKEO , NINOMIYA HIROYUKI , KOBAYASHI MASAYOSHI
IPC分类号： F23R3/14 , F23R3/28 , F23R3/30
CPC分类号： F23R3/30 , F23D2900/11101 , F23R3/286 , Y10S261/55
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine and airplane engine for preventing degradation of combustibility at a low load time of a premixing/prevaporization lean combustion system combustor.
SOLUTION: The combustibility improving device of the premixed-fuel injection valve includes one air flow path 11 added on an outer side of an air flow path for main combustion of a combustor liner head part, an atomization lip 9 added on a tip end part on a combustor side of a partitioning wall for structuring the flow path 11, and swirlers 8a, 8b for giving turning to an air flow installed on the added flow path 11.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于燃气轮机和飞机发动机的燃烧器，用于防止在预混/先蒸发稀燃燃烧系统燃烧器的低负载时间下的可燃性降低。解决方案：预混合燃料喷射阀的可燃性提高装置包括一个空气流路11，其添加在燃烧器衬套头部的主燃烧用空气流路的外侧，添加在尖端的雾化唇9 用于构造流路11的分隔壁的燃烧器侧的端部和用于使安装在添加流路11上的气流转向的旋流器8a，8b。（C）2005，JPO＆NCIPI

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