CN101782232A - 文丘里管冷却*** - Google Patents
文丘里管冷却*** Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract
提供一种用于燃气轮机的燃烧器,其具有:喷嘴组件,其位于一个端部;以及燃烧室,其限定燃烧器的第二端部。文丘里管在燃烧器中位于喷嘴与燃烧室之间。文丘里管中限定有通路,所述通路具有面向喷嘴的第一侧以及面向燃烧室的第二侧。压缩空气导入入口中,所述入口与文丘里管的通路的第一侧和第二侧流体连通。文丘里管的通路在所述通路的第一侧和第二侧中沿相反方向引导来自入口的压缩空气用于冷却文丘里管。
Description
技术领域
本发明涉及可用于燃气轮机中的燃烧器。更具体地,本发明涉及一种用于对一级燃烧室与二级燃烧室之间的文丘里管喉部区域进行冷却的***。
背景技术
燃气轮机在许多应用场合起着至关重要的作用,如用于飞行器推进、船舶推进、发电以及诸如泵和压缩机的驱动处理中。一般地,燃气轮机包括压缩机、燃烧器和涡轮机。操作中,空气供给到***中,在此它通过压缩机压缩并在燃烧器中与燃料混合。接着,压缩空气和燃料混合物在燃烧器中燃烧,从而引起气流膨胀以便驱动涡轮机。
燃烧室衬筒限定燃烧器的内部容积并且用于保护燃烧器外壳以及其余轮机部件不受燃烧器中的极高温度的影响。为了减少NOX排放并且延长轮机部件的寿命,需要使用一部分来自压缩机的压缩空气用于冷却包括燃烧室衬筒在内的各种燃烧器部件。
燃烧室衬筒通常包括文丘里管喉部区域,所述文丘里管喉部区域用于在燃烧器内影响火焰定位并且使燃烧火焰稳定。在这种布置中,通过燃烧稀薄、均匀的燃料与空气的混合物来降低峰值火焰温度,从而实现NOX排放的减少。均匀性通常通过在文丘里管的上游使燃料和空气在燃烧器中进行预混合并且接着在文丘里管的边缘或顶点下游将混合物点燃进入二级燃烧室来实现。通过对喉部之前的气流的加速特性,文丘里管的构造旨在防止火焰闪回文丘里管喉部的上游的预混合区域或者一级燃烧室。文丘里管上游的火焰保持区域也需要在特定的操作条件下进行冷却。由于火焰能够存在于文丘里管的各侧上,因此两侧都需要进行冷却。但是,如果从文丘里管下游释放的冷却空气流过大或者释放地过于接近文丘里管,可能对燃烧性能产生不利影响。
美国专利US 5,117,636示出了文丘里管内的冷却通路,所述冷却通路自文丘里管的顶点或喉部向下游延伸,使得冷却空气不会再次进入二级燃烧室中的火焰保持区域。期望将火焰保持的功能与文丘里管的冷却功能分离。美国专利US 6,430,932示出了文丘里管内的冷却室,所述冷却室引导冷却气流与燃烧气流反向并且在文丘里管的上游排放冷却空气。
已经确定,文丘里管的上游侧和下游侧上的热载荷不同,并且在文丘里管附近在任一侧排出冷却空气都会对燃烧器的操作产生影响。在现有的设计中,文丘里管两侧的冷却是关联的,既没有平衡文丘里管壁中的吸热量,也没有对冷却通道中的压降进行适应性调节。
发明内容
提供一种用于以下类型的燃气轮机的燃烧器:其具有位于燃烧器的第一端部的喷嘴组件以及在喷嘴下游限定于燃烧器的第二端部的燃烧室。文丘里管位于喷嘴与燃烧室之间。文丘里管限定燃烧器的第一端部与燃烧器的第二端部之间的过渡。文丘里管中包括用于接收冷却气流的通路。所述通路具有面向喷嘴的第一侧以及面向燃烧室的第二侧。压缩空气源导入所述通路中,并且气流入口与文丘里管的通路的第一侧和第二侧都连通。文丘里管的通路在文丘里管中沿相反方向引导来自压缩空气源的压缩空气。因此,该通路的第一侧和第二侧中的气流沿相反方向流动。
本发明的另一个方面可以包括二级通路,所述二级通路在文丘里管的通路的第二侧的上游延伸。而且,冷却气流入口可以置位为更加接近喷嘴或者更加接近文丘里管的顶点的上游侧。
附图说明
在附图中,示出了目前优选的多个实施方式。
图1示出了结合了本发明的实施方式的燃气轮机燃烧***的简化剖面图。
图2是图1所示的燃烧***的文丘里管喉部区域的局部剖视图。
图3是燃烧***中使用的文丘里管***的另一个实施方式的局部剖视图。
图4是燃烧***中使用的文丘里管***的再一个实施方式的局部剖视图。
具体实施方式
在附图中,示出了一般的燃烧器和多个本发明的实施方式的图示。燃烧器总体上由标号10指示并且预计将被结合至燃气轮机(未示出)中。在图1中,燃烧器10包括燃烧室衬筒12,所述燃烧室衬筒12至少部分由隔热罩或导流套管14包绕。压缩空气由上游压缩机(未示出)提供并且导入形成在隔热罩14与燃烧室衬筒12之间的周围通道16中。
在燃烧室衬筒12所限定的空间内设置有二级燃料喷嘴20和多个一级燃料喷嘴18。燃烧器导流套管22设置为包绕二级燃料喷嘴20,从而使二级喷嘴20与一级喷嘴18隔开。燃料24引入控制器26中并且供给至喷嘴18和20。燃烧室衬筒12与燃烧器导流套管22之间的区域限定了上游或一级燃烧室28。二级喷嘴20的下游是文丘里管30,所述文丘里管30在由燃烧室衬筒12限定的区域中限定环形缩窄部。文丘里管30包括顶点32,所述顶点32限定文丘里管喉部。顶点32位于喷嘴18和20的下游。下游或二级燃烧室34在燃烧器中位于文丘里管顶点32的下游。
在操作中,火焰能够存在于文丘里管30的任一侧上,即,既可以存在于上游燃烧室28中也可以存在于下游燃烧室34中。在一级工况中,燃料24供给到一级喷嘴18,燃烧在上游燃烧室中发生并经过文丘里管喉部32导入下游。在稀-稀工况中,燃料24供给到一级喷嘴18也供给到二级喷嘴20。上游燃烧室28以及下游燃烧室34中都发生燃烧。此外,燃烧器10可以在仅将燃料24导入二级喷嘴20的情况下进行操作,从而在下游燃烧室34中产生燃烧。可以将附加的燃料24供给到一级喷嘴18而不在上游燃烧室28中产生火焰。穿过上游燃烧室28的燃料与空气的预混合物通过文丘里管30导入下游燃烧室34,从而在下游燃烧室34中产生预混工况以及相当大的火焰。
由于火焰能够存在于文丘里管30的各侧上,为了适当的工况以及设备的寿命,通常需要对文丘里管的两侧的壁进行冷却。如图1所示,周围通道16中的冷却空气导入文丘里管30的后部,并且接着沿文丘里管30的内侧壁流动。预期文丘里管30的上游侧和下游侧上的热载荷是不同的。此外,冷却空气在文丘里管30的任一侧上回到燃烧室的运动还对燃烧器10的工况有影响。
在图2中,示出图1所示的文丘里管30的一侧的放大示意剖视图。压缩空气36导入文丘里管30后部上的气室38中。在这一实施方式中,进气室38直接位于文丘里管30的顶点32的后部。通过进气室导入文丘里管30的冷却空气与两个通道40和42流体连通,所述通道40大致平行于文丘里管30的第一侧或上游侧41并且所述通道42大致平行于文丘里管30的第二侧或下游侧43。导入通道40的冷却空气36沿着与导入通道42的冷却空气相反的方向转向。将穿过处于文丘里管30上游侧41的上游通道40的气流通过上游出口44导入一级燃烧室28。穿过下游通道42并且沿下游侧43流动的冷却气流通过置位为邻近燃烧室衬筒12的出口46导入下游燃烧室34。多种用于文丘里管空气的排气出口的具体形式在现有技术中是已知的并且能够结合于当前所述的文丘里管30。
在图3中,示出本发明的结构的变型。冷却空气36自通道16导入具有出口的进气室138,所述出口置位为邻近文丘里管的下游侧43。进气室138与下游通道142直接流体连通。通过通道142朝向下游出口46沿下游方向引导冷却空气。在下游通道部142a中沿着与下游出口46相反方向引导冷却空气的另外气流。下游通道部142a与上游通道140连通并位于文丘里管30的上游侧41的后部。通过上游出口44将上游通道140中的冷却空气导入上游燃烧室28。将冷却通道置位在文丘里管的下游表面能够减少文丘里管的下游部所需的冷却。可替换地,进气室138可以置位为邻近文丘里管30的上游侧41。
因此,文丘里管限定了燃烧器的第一端部与第二端部之间的过渡。文丘里管中的内部通路包括位于文丘里管的顶点的相反两侧上的第一侧和第二侧。用于压缩的空气流的冷却入口与文丘里管通路的第一侧和第二侧流体连通,并且引导来自冷却入口的压缩空气在第一侧和第二侧中沿相反方向通过文丘里管通路。冷却入口可以在与文丘里管的顶点成直线或者偏移的位置与文丘里管通路连通。冷却入口可以形成位于文丘里管的后部的径向气室或者采取许多其它形式。
在图4中,提供文丘里管冷却***的另一个实施方式。冷却空气36自通道16导入进气室238。进气室238将冷却空气导入文丘里管30的后侧上的通道242和通道240。如图所示,进气室238置位为邻近文丘里管30的顶点32的后部,并且上游通道240引导冷却空气沿上游侧41流动而下游通道242引导冷却空气沿下游侧43流动。通道242的下游端与二级通路248流体连通。通道242内的冷却空气在其进入二级通路248时反转方向。二级通路248朝向燃烧器的上游侧延伸并且与邻近排气通道250的上游通道240连接。来自上游通道240和二级通路248的汇合气流穿过排气通道250并且通过上游出口244排入位于文丘里管30的上游侧上的燃烧室28中。
在图4所示的实施方式中(以及上述的实施方式中),预期进气室238可以包括除了连续槽或者环形通道之外的一些部件。进气室238和二级通路248可以通过一系列彼此交叉的管道形成。因此,进气室238在跨越形成通路248的一系列管道之后供给到文丘里管30的后侧。还可以利用进气室238相对于文丘里管30的顶点32的轴向位置的重新置位来调整文丘里管30的冷却效果。此外,根据此处所述的所有实施方式,可以改变通道和通路的相对尺寸和形成,从而随着冷却空气在文丘里管壁的内侧流动并且接着导入燃烧室中,来调整冷却空气的气流和压降。
通过阅读这里的公开内容,对于本领域的普通技术人员来说,所述实施方式的多种变型将是显而易见的。因此,本发明可以在不背离其精神或基本特性的前提下通过其它的具体形式实施,从而,在考虑本发明的范围时,应参考所附权利要求而不是前述说明书。
Claims (17)
1.一种用于燃气轮机的燃烧器,包括:
喷嘴组件,其位于所述燃烧器的第一端部;
燃烧室,其限定于所述燃烧器中,所述喷嘴下游;
文丘里管,其位于所述燃烧器中并且限定所述第一端部与所述燃烧室之间的过渡,所述文丘里管中具有内部通路,所述内部通路具有面向所述喷嘴的第一侧以及面向所述燃烧室的第二侧;以及
压缩空气源,其导入冷却入口,所述冷却入口与所述文丘里管的内部通路的所述第一侧和所述第二侧流体连通;
所述内部通路在所述第一侧和所述第二侧中沿相反方向从所述压缩空气源引导压缩空气用于冷却所述文丘里管。
2.如权利要求1所述的燃烧器,其进一步包括二级通路,所述二级通路与所述文丘里管的内部通路的所述第二侧的下游端连通,其中,经过所述内部通路的所述第二侧流入所述二级通路的气流被反转方向并且被引向所述文丘里管的所述第一侧。
3.如权利要求2所述的燃烧器,其进一步包括冷却空气出口,所述冷却空气出口位于所述文丘里管的内部通路的所述第一侧的端部用于将冷却空气导入所述燃烧器的所述第一端部。
4.如权利要求3所述的燃烧器,其中,所述二级通路以及所述内部通路的所述第一侧分别与所述冷却空气出口流体连通。
5.如权利要求4所述的燃烧器,其中,所述冷却空气出口将来自所述二级通路和所述文丘里管的内部通路的所述第一侧的气流导入所述燃烧器的所述第一端部,所述文丘里管的上游。
6.如权利要求1所述的燃烧器,其中,所述冷却入口在所述燃烧器中所述文丘里管的上游侧的后部的位置与所述文丘里管的内部通路的所述第一侧连通。
7.如权利要求1所述的燃烧器,其进一步包括位于所述文丘里管后部的径向气室。
8.一种用于燃气轮机的燃烧器,包括:
喷嘴组件,其位于所述燃烧器的第一端部;
燃烧室,其限定于所述燃烧器中,所述喷嘴下游;
文丘里管,其位于所述燃烧器中并且限定所述第一端部与所述燃烧室之间的过渡,所述文丘里管中具有内部通路,所述文丘里管的内部通路在所述文丘里管的顶点的相反两侧上具有第一侧和第二侧;以及
用于压缩的气流的冷却入口,所述冷却入口与所述文丘里管的内部通路的所述第一侧和所述第二侧流体连通,并且,来自所述冷却入口的压缩空气在所述第一侧和所述第二侧中沿相反方向被引导穿过所述文丘里管的内部通路用于冷却所述文丘里管。
9.如权利要求8所述的燃烧器,其中,在所述燃烧器中,所述冷却入口在偏移所述文丘里管的顶点的位置与所述文丘里管的内部通路的所述第一侧或所述第二侧连通。
10.如权利要求8所述的燃烧器,其中,所述冷却入口包括位于所述文丘里管的后部的径向气室。
11.如权利要求8所述的燃烧器,其进一步包括二级通路,所述二级通路与所述文丘里管的内部通路的所述第二侧的下游端连通,其中,经过所述内部通路的所述第二侧流入所述二级通路的气流被反转方向并且被引向所述文丘里管的所述第一侧。
12.如权利要求11所述的燃烧器,其进一步包括冷却空气出口,所述冷却空气出口位于所述文丘里管的内部通路的所述第一侧的端部用于将冷却空气导入所述燃烧器的所述第一端部。
13.如权利要求12所述的燃烧器,其中,所述二级通路以及所述内部通路的所述第一侧分别与所述冷却空气出口流体连通。
14.如权利要求13所述的燃烧器,其中,所述冷却空气出口将来自所述二级通路和所述文丘里管的内部通路的所述第一侧的气流导入所述燃烧器的所述第一端部,所述文丘里管的上游。
15.一种燃气轮机燃烧器中的文丘里管,包括:
带角度的上游侧;
带角度的下游侧;
位于所述上游侧与所述下游侧之间的顶点;
处于所述上游侧与所述下游侧之间的冷却空气入口,所述冷却空气入口用于在所述顶点附近供给冷却空气;
第一通路,其用于引导冷却空气自所述冷却空气入口沿所述带角度的下游侧的内表面流动并且接着沿衬筒向其上游流动;
第二通路,其用于引导冷却空气自所述冷却空气入口沿所述带角度的上游侧流动;以及
冷却排放部,其用于引导冷却空气从所述第二通道流入所述燃烧器,所述文丘里管的顶点的上游。
16.如权利要求15所述的文丘里管,其进一步包括中心气室,在所述文丘里管中,所述中心气室围绕所述燃烧器径向延伸。
17.如权利要求15所述的文丘里管,其中,所述冷却排放部位于所述文丘里管的所述带角度的上游侧的上游。
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US12/357,029 US7712314B1 (en) | 2009-01-21 | 2009-01-21 | Venturi cooling system |
US12/357,029 | 2009-01-21 |
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US (2) | US7712314B1 (zh) |
EP (1) | EP2211104B1 (zh) |
JP (1) | JP4933578B2 (zh) |
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CN (1) | CN101782232B (zh) |
AR (2) | AR072358A1 (zh) |
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CA (1) | CA2661248C (zh) |
CL (1) | CL2009001101A1 (zh) |
HK (1) | HK1146108A1 (zh) |
IL (1) | IL198653A (zh) |
MX (1) | MX2009004301A (zh) |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104566463A (zh) * | 2014-11-29 | 2015-04-29 | 哈尔滨广瀚燃气轮机有限公司 | 燃气轮机低排放燃烧室空气调节装置 |
CN104807042A (zh) * | 2015-05-15 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种燃烧室 |
CN105465455A (zh) * | 2015-12-25 | 2016-04-06 | 深圳荣钜源科技有限公司 | 出水单元、喷头以及花洒 |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8707704B2 (en) * | 2007-05-31 | 2014-04-29 | General Electric Company | Method and apparatus for assembling turbine engines |
US8096133B2 (en) * | 2008-05-13 | 2012-01-17 | General Electric Company | Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface |
US8646277B2 (en) * | 2010-02-19 | 2014-02-11 | General Electric Company | Combustor liner for a turbine engine with venturi and air deflector |
RU2519014C2 (ru) * | 2010-03-02 | 2014-06-10 | Дженерал Электрик Компани | Диффузор для камеры сгорания турбины (варианты) и камера сгорания турбины |
US8959886B2 (en) * | 2010-07-08 | 2015-02-24 | Siemens Energy, Inc. | Mesh cooled conduit for conveying combustion gases |
US8894363B2 (en) | 2011-02-09 | 2014-11-25 | Siemens Energy, Inc. | Cooling module design and method for cooling components of a gas turbine system |
US20120047895A1 (en) * | 2010-08-26 | 2012-03-01 | General Electric Company | Systems and apparatus relating to combustor cooling and operation in gas turbine engines |
US9518739B2 (en) | 2013-03-08 | 2016-12-13 | Pratt & Whitney Canada Corp. | Combustor heat shield with carbon avoidance feature |
US9453424B2 (en) * | 2013-10-21 | 2016-09-27 | Siemens Energy, Inc. | Reverse bulk flow effusion cooling |
US10100730B2 (en) | 2015-03-11 | 2018-10-16 | Pratt & Whitney Canada Corp. | Secondary air system with venturi |
CN105157063B (zh) * | 2015-09-18 | 2018-04-13 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种流量分配可调的火焰筒 |
CN107013941B (zh) * | 2016-01-27 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | 燃烧室燃油喷嘴装置 |
US10316803B2 (en) * | 2017-09-25 | 2019-06-11 | Woodward, Inc. | Passive pumping for recirculating exhaust gas |
CN109084329A (zh) * | 2018-07-05 | 2018-12-25 | 西北工业大学 | 一种多点直接喷射燃烧室头部结构 |
US10995705B2 (en) | 2019-02-07 | 2021-05-04 | Woodward, Inc. | Modular exhaust gas recirculation system |
CN213175878U (zh) | 2020-01-08 | 2021-05-11 | 伍德沃德有限公司 | 排气气体再循环混合器和发动机*** |
US11215132B1 (en) | 2020-12-15 | 2022-01-04 | Woodward, Inc. | Controlling an internal combustion engine system |
US11174809B1 (en) | 2020-12-15 | 2021-11-16 | Woodward, Inc. | Controlling an internal combustion engine system |
CN116265810A (zh) | 2021-12-16 | 2023-06-20 | 通用电气公司 | 利用成形冷却栅栏的旋流器反稀释 |
US11835236B1 (en) | 2022-07-05 | 2023-12-05 | General Electric Company | Combustor with reverse dilution air introduction |
US11747019B1 (en) * | 2022-09-02 | 2023-09-05 | General Electric Company | Aerodynamic combustor liner design for emissions reductions |
Family Cites Families (109)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2935841A (en) * | 1956-06-18 | 1960-05-10 | Bell Aircraft Corp | Thrust chamber with integrated cooling and structural members |
US3656303A (en) | 1970-04-13 | 1972-04-18 | Robert C La Force | Combustion engine pollution control |
US4010607A (en) | 1973-01-02 | 1977-03-08 | Hopping Alvin S | Internal combustion engine with afterburner, venturi cooler and exhaust turbine |
US3904307A (en) | 1974-04-10 | 1975-09-09 | United Technologies Corp | Gas generator turbine cooling scheme |
US3938324A (en) * | 1974-12-12 | 1976-02-17 | General Motors Corporation | Premix combustor with flow constricting baffle between combustion and dilution zones |
UST962010I4 (en) | 1976-03-25 | 1977-09-06 | Variable venturi carburetor idle speed fuel control | |
US4250856A (en) | 1980-01-25 | 1981-02-17 | Abbey Harold | Fuel-air ratio automatic control system using variable venturi structure |
US4200124A (en) | 1978-02-21 | 1980-04-29 | Eaton Corporation | Valve assembly |
DE7810865U1 (de) | 1978-04-12 | 1978-09-21 | Dolmar Maschinen-Fabrik Gmbh & Co, 2000 Hamburg | Abgasschalldaempfer fuer auspuffvorrichtungen von brennkraftmaschinen, insbesondere von brennkraftmaschinenangetriebenen handarbeitsgeraeten |
US4303374A (en) | 1978-12-15 | 1981-12-01 | General Electric Company | Film cooled airfoil body |
US4420929A (en) | 1979-01-12 | 1983-12-20 | General Electric Company | Dual stage-dual mode low emission gas turbine combustion system |
US4292801A (en) | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
US4361010A (en) * | 1980-04-02 | 1982-11-30 | United Technologies Corporation | Combustor liner construction |
US4413477A (en) * | 1980-12-29 | 1983-11-08 | General Electric Company | Liner assembly for gas turbine combustor |
US4690245A (en) | 1983-03-17 | 1987-09-01 | Stemco, Inc. | Flattened venturi, method and apparatus for making |
US4719748A (en) | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
US4984429A (en) * | 1986-11-25 | 1991-01-15 | General Electric Company | Impingement cooled liner for dry low NOx venturi combustor |
US4982570A (en) | 1986-11-25 | 1991-01-08 | General Electric Company | Premixed pilot nozzle for dry low Nox combustor |
US5329773A (en) | 1989-08-31 | 1994-07-19 | Alliedsignal Inc. | Turbine combustor cooling system |
US5101624A (en) | 1989-09-07 | 1992-04-07 | General Electric Company | Exhaust nozzle hinge |
US5285631A (en) | 1990-02-05 | 1994-02-15 | General Electric Company | Low NOx emission in gas turbine system |
US5117636A (en) * | 1990-02-05 | 1992-06-02 | General Electric Company | Low nox emission in gas turbine system |
US5123248A (en) | 1990-03-28 | 1992-06-23 | General Electric Company | Low emissions combustor |
US5127221A (en) * | 1990-05-03 | 1992-07-07 | General Electric Company | Transpiration cooled throat section for low nox combustor and related process |
US5125227A (en) | 1990-07-10 | 1992-06-30 | General Electric Company | Movable combustion system for a gas turbine |
US5257499A (en) | 1991-09-23 | 1993-11-02 | General Electric Company | Air staged premixed dry low NOx combustor with venturi modulated flow split |
US5253478A (en) | 1991-12-30 | 1993-10-19 | General Electric Company | Flame holding diverging centerbody cup construction for a dry low NOx combustor |
US5487275A (en) | 1992-12-11 | 1996-01-30 | General Electric Co. | Tertiary fuel injection system for use in a dry low NOx combustion system |
US5377483A (en) | 1993-07-07 | 1995-01-03 | Mowill; R. Jan | Process for single stage premixed constant fuel/air ratio combustion |
US5454221A (en) | 1994-03-14 | 1995-10-03 | General Electric Company | Dilution flow sleeve for reducing emissions in a gas turbine combustor |
SE504431C2 (sv) | 1994-06-29 | 1997-02-10 | Iggesund Tools Ab | Knivanordning |
US5584651A (en) | 1994-10-31 | 1996-12-17 | General Electric Company | Cooled shroud |
US5612006A (en) | 1995-07-05 | 1997-03-18 | Fisk; James C. | Catalytic converter and phase-spreading spiral muffler assembly |
JP3619599B2 (ja) | 1995-11-30 | 2005-02-09 | 株式会社東芝 | ガスタービンプラント |
GB2311596B (en) | 1996-03-29 | 2000-07-12 | Europ Gas Turbines Ltd | Combustor for gas - or liquid - fuelled turbine |
US5787703A (en) | 1996-05-10 | 1998-08-04 | Fougerousse; Russell | Combined ramjet and rocket engine having rectilinear duct |
US5950417A (en) | 1996-07-19 | 1999-09-14 | Foster Wheeler Energy International Inc. | Topping combustor for low oxygen vitiated air streams |
US6250066B1 (en) | 1996-11-26 | 2001-06-26 | Honeywell International Inc. | Combustor with dilution bypass system and venturi jet deflector |
US5829245A (en) | 1996-12-31 | 1998-11-03 | Westinghouse Electric Corporation | Cooling system for gas turbine vane |
US5738493A (en) | 1997-01-03 | 1998-04-14 | General Electric Company | Turbulator configuration for cooling passages of an airfoil in a gas turbine engine |
US5896742A (en) | 1997-03-20 | 1999-04-27 | General Electric Co. | Tapered cross-fire tube for gas turbine combustors |
US6139257A (en) | 1998-03-23 | 2000-10-31 | General Electric Company | Shroud cooling assembly for gas turbine engine |
CA2288557C (en) | 1998-11-12 | 2007-02-06 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor cooling structure |
GB2345942B (en) | 1998-12-24 | 2002-08-07 | Rolls Royce Plc | Gas turbine engine internal air system |
RU2158841C2 (ru) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Камера жидкостного ракетного двигателя и ее корпус |
US6925809B2 (en) | 1999-02-26 | 2005-08-09 | R. Jan Mowill | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
DE19912365A1 (de) | 1999-03-19 | 2000-09-21 | Roche Diagnostics Gmbh | Mehrschichtiges analytisches Hilfsmittel |
US6037684A (en) | 1999-04-28 | 2000-03-14 | Campbell Haufeld/Scott Fetzer Company | HVLP motor assembly |
GB9926257D0 (en) | 1999-11-06 | 2000-01-12 | Rolls Royce Plc | Wall elements for gas turbine engine combustors |
US6267106B1 (en) | 1999-11-09 | 2001-07-31 | Caterpillar Inc. | Induction venturi for an exhaust gas recirculation system in an internal combustion engine |
DE10019437A1 (de) | 2000-04-19 | 2001-12-20 | Rolls Royce Deutschland | Verfahren und Vorrichtung zum Kühlen der Gehäuse von Turbinen von Strahltriebwerken |
WO2003093664A1 (en) | 2000-06-28 | 2003-11-13 | Power Systems Mfg. Llc | Combustion chamber/venturi cooling for a low nox emission combustor |
US6446438B1 (en) | 2000-06-28 | 2002-09-10 | Power Systems Mfg., Llc | Combustion chamber/venturi cooling for a low NOx emission combustor |
US6374594B1 (en) | 2000-07-12 | 2002-04-23 | Power Systems Mfg., Llc | Silo/can-annular low emissions combustor |
US6427446B1 (en) | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
US6672570B2 (en) | 2000-11-17 | 2004-01-06 | Walbro Japan, Inc. | Variable venturi carburetor |
US6536201B2 (en) | 2000-12-11 | 2003-03-25 | Pratt & Whitney Canada Corp. | Combustor turbine successive dual cooling |
US6698924B2 (en) | 2000-12-21 | 2004-03-02 | Tank, Inc. | Cooling system comprising a circular venturi |
US6623160B2 (en) | 2000-12-21 | 2003-09-23 | Mccarthy, Jr. Joseph H. | Method and system for cooling heat-generating component in a closed-loop system |
US6430932B1 (en) * | 2001-07-19 | 2002-08-13 | Power Systems Mfg., Llc | Low NOx combustion liner with cooling air plenum recesses |
FR2836986B1 (fr) | 2002-03-07 | 2004-11-19 | Snecma Moteurs | Systeme d'injection multi-modes d'un melange air/carburant dans une chambre de combustion |
US6705088B2 (en) | 2002-04-05 | 2004-03-16 | Power Systems Mfg, Llc | Advanced crossfire tube cooling scheme for gas turbine combustors |
US6772595B2 (en) | 2002-06-25 | 2004-08-10 | Power Systems Mfg., Llc | Advanced cooling configuration for a low emissions combustor venturi |
US6832482B2 (en) | 2002-06-25 | 2004-12-21 | Power Systems Mfg, Llc | Pressure ram device on a gas turbine combustor |
US6691516B2 (en) | 2002-07-15 | 2004-02-17 | Power Systems Mfg, Llc | Fully premixed secondary fuel nozzle with improved stability |
US6675581B1 (en) | 2002-07-15 | 2004-01-13 | Power Systems Mfg, Llc | Fully premixed secondary fuel nozzle |
US6898937B2 (en) | 2002-07-15 | 2005-05-31 | Power Systems Mfg., Llc | Gas only fin mixer secondary fuel nozzle |
US7290394B2 (en) | 2002-11-21 | 2007-11-06 | Parker-Hannifin Corporation | Fuel injector flexible feed with moveable nozzle tip |
US6969230B2 (en) | 2002-12-17 | 2005-11-29 | General Electric Company | Venturi outlet turbine airfoil |
US6865892B2 (en) * | 2002-12-17 | 2005-03-15 | Power Systems Mfg, Llc | Combustion chamber/venturi configuration and assembly method |
JP2006518823A (ja) | 2003-02-24 | 2006-08-17 | プラット アンド ホイットニー カナダ コーポレイション | 複合サイクルエンジン |
US6912838B2 (en) | 2003-03-06 | 2005-07-05 | Power Systems Mfg, Llc | Coated crossfire tube assembly |
US6981846B2 (en) | 2003-03-12 | 2006-01-03 | Florida Turbine Technologies, Inc. | Vortex cooling of turbine blades |
US6935116B2 (en) | 2003-04-28 | 2005-08-30 | Power Systems Mfg., Llc | Flamesheet combustor |
US6986254B2 (en) | 2003-05-14 | 2006-01-17 | Power Systems Mfg, Llc | Method of operating a flamesheet combustor |
US7051524B1 (en) | 2003-06-30 | 2006-05-30 | Bernard A Kraft | Venturi device |
JP4040556B2 (ja) | 2003-09-04 | 2008-01-30 | 株式会社日立製作所 | ガスタービン設備及び冷却空気供給方法 |
US7021892B2 (en) | 2003-11-19 | 2006-04-04 | Massachusetts Institute Of Technology | Method for assembling gas turbine engine components |
US7096668B2 (en) | 2003-12-22 | 2006-08-29 | Martling Vincent C | Cooling and sealing design for a gas turbine combustion system |
US7082770B2 (en) | 2003-12-24 | 2006-08-01 | Martling Vincent C | Flow sleeve for a low NOx combustor |
US6951109B2 (en) | 2004-01-06 | 2005-10-04 | General Electric Company | Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
JP4495603B2 (ja) | 2004-01-15 | 2010-07-07 | 株式会社日立製作所 | ガスタービン発電装置およびそれに用いる消音装置 |
US7127899B2 (en) | 2004-02-26 | 2006-10-31 | United Technologies Corporation | Non-swirl dry low NOx (DLN) combustor |
US7013649B2 (en) | 2004-05-25 | 2006-03-21 | General Electric Company | Gas turbine engine combustor mixer |
US7007482B2 (en) | 2004-05-28 | 2006-03-07 | Power Systems Mfg., Llc | Combustion liner seal with heat transfer augmentation |
US7152410B2 (en) | 2004-06-10 | 2006-12-26 | Honeywell International, Inc. | System and method for dumping surge flow into eductor primary nozzle for free turbine |
US6983600B1 (en) | 2004-06-30 | 2006-01-10 | General Electric Company | Multi-venturi tube fuel injector for gas turbine combustors |
US7003958B2 (en) | 2004-06-30 | 2006-02-28 | General Electric Company | Multi-sided diffuser for a venturi in a fuel injector for a gas turbine |
AU2005263680B2 (en) | 2004-07-19 | 2009-04-02 | Ansaldo Energia Ip Uk Limited | Method for operating a gas turbine group |
US7153488B2 (en) | 2004-08-03 | 2006-12-26 | Millennium Inorganic Chemicals, Inc. | Suppression of the formation of noxious substances during chloride processes |
US20060042257A1 (en) | 2004-08-27 | 2006-03-02 | Pratt & Whitney Canada Corp. | Combustor heat shield and method of cooling |
US7237384B2 (en) | 2005-01-26 | 2007-07-03 | Peter Stuttaford | Counter swirl shear mixer |
US7389643B2 (en) * | 2005-01-31 | 2008-06-24 | General Electric Company | Inboard radial dump venturi for combustion chamber of a gas turbine |
US7677025B2 (en) | 2005-02-01 | 2010-03-16 | Power Systems Mfg., Llc | Self-purging pilot fuel injection system |
US7386980B2 (en) | 2005-02-02 | 2008-06-17 | Power Systems Mfg., Llc | Combustion liner with enhanced heat transfer |
US7513115B2 (en) | 2005-05-23 | 2009-04-07 | Power Systems Mfg., Llc | Flashback suppression system for a gas turbine combustor |
US7451600B2 (en) | 2005-07-06 | 2008-11-18 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
CN1932316B (zh) | 2005-09-16 | 2010-09-29 | 深圳富泰宏精密工业有限公司 | 多段式转轴结构 |
US7559203B2 (en) | 2005-09-16 | 2009-07-14 | Pratt & Whitney Canada Corp. | Cooled support boss for a combustor in a gas turbine engine |
US7546737B2 (en) | 2006-01-24 | 2009-06-16 | Honeywell International Inc. | Segmented effusion cooled gas turbine engine combustor |
FR2897107B1 (fr) | 2006-02-09 | 2013-01-18 | Snecma | Paroi transversale de chambre de combustion munie de trous de multiperforation |
US7770395B2 (en) | 2006-02-27 | 2010-08-10 | Mitsubishi Heavy Industries, Ltd. | Combustor |
US7624577B2 (en) | 2006-03-31 | 2009-12-01 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
US8109098B2 (en) | 2006-05-04 | 2012-02-07 | Siemens Energy, Inc. | Combustor liner for gas turbine engine |
US7669411B2 (en) | 2006-05-10 | 2010-03-02 | Caterpillar Inc. | Cooling device |
FR2904048B1 (fr) | 2006-07-19 | 2012-12-14 | Snecma | Systeme de ventilation de paroi de chambre de combustion dans une turbomachine |
US7631503B2 (en) | 2006-09-12 | 2009-12-15 | Pratt & Whitney Canada Corp. | Combustor with enhanced cooling access |
US8182199B2 (en) | 2007-02-01 | 2012-05-22 | Pratt & Whitney Canada Corp. | Turbine shroud cooling system |
US20090019854A1 (en) | 2007-07-16 | 2009-01-22 | General Electric Company | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR |
-
2009
- 2009-01-21 US US12/357,029 patent/US7712314B1/en active Active
- 2009-04-01 EP EP09004835.6A patent/EP2211104B1/en active Active
- 2009-04-02 SG SG2011091501A patent/SG177888A1/en unknown
- 2009-04-02 SG SG200902292-2A patent/SG163466A1/en unknown
- 2009-04-02 CA CA2661248A patent/CA2661248C/en active Active
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104566463A (zh) * | 2014-11-29 | 2015-04-29 | 哈尔滨广瀚燃气轮机有限公司 | 燃气轮机低排放燃烧室空气调节装置 |
CN104807042A (zh) * | 2015-05-15 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种燃烧室 |
CN105465455A (zh) * | 2015-12-25 | 2016-04-06 | 深圳荣钜源科技有限公司 | 出水单元、喷头以及花洒 |
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MX2009004301A (es) | 2010-07-20 |
CA2661248C (en) | 2011-02-08 |
MY149412A (en) | 2013-08-30 |
KR101131646B1 (ko) | 2012-03-28 |
CL2009001101A1 (es) | 2011-08-19 |
EP2211104A2 (en) | 2010-07-28 |
US7707836B1 (en) | 2010-05-04 |
HK1146108A1 (en) | 2011-05-13 |
AU2009201420B2 (en) | 2011-01-27 |
CA2661248A1 (en) | 2010-07-21 |
KR20100085810A (ko) | 2010-07-29 |
TWI376484B (en) | 2012-11-11 |
CN101782232B (zh) | 2012-11-28 |
AR072358A1 (es) | 2010-08-25 |
AR092910A2 (es) | 2015-05-06 |
TW201028622A (en) | 2010-08-01 |
IL198653A0 (en) | 2010-02-17 |
JP4933578B2 (ja) | 2012-05-16 |
TW201241369A (en) | 2012-10-16 |
AU2009201420B8 (en) | 2011-02-17 |
TWI452242B (zh) | 2014-09-11 |
IL198653A (en) | 2013-01-31 |
BRPI0901605A2 (pt) | 2010-12-21 |
US7712314B1 (en) | 2010-05-11 |
EP2211104B1 (en) | 2017-06-14 |
JP2010169076A (ja) | 2010-08-05 |
SG177888A1 (en) | 2012-02-28 |
AU2009201420A1 (en) | 2010-08-05 |
SG163466A1 (en) | 2010-08-30 |
EP2211104A3 (en) | 2014-08-06 |
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