CN1158383A - 燃气透平环形燃烧室 - Google Patents
燃气透平环形燃烧室 Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
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- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
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- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
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Abstract
燃气透平环形燃烧室(4),在压缩机(1)的下游安置,在它的前壁板上至少装有呈环形布置的一系列预混合燃烧器(5),各个作为扩散器设计的燃烧用空气通道(15)从最后一列压缩机的导向叶片(9)通往每个燃烧器(5),在燃烧用空气通道下游端至少有一个纵向涡流发生器(16),而在其中或其下游配备燃料喷射器(17)。后者下游安置一个混合通道(19),它终止于燃烧室(4)中,其不变的高度为(H),其长度为(L),大致相当于液压通道直径(D)值的两倍。这样减小了透平尺寸和压力损失。
Description
本发明涉及燃烧技术领域。本发明涉及的是一种燃气透平环形燃烧室,该燃烧室利用预混合燃烧器来运行,同时还涉及运行这一装置的一种方法。
燃气透平基本上包含如下部分:压缩机,燃烧室和涡轮机。由于环境保护原因,已越来越多地采用一种有害物少的预混合燃烧以代替扩散燃烧。
大家已熟悉的技术现状是(参考H.Neuhoff和K.Throen:《新型燃气透平GT24和GT26-由于顺序燃烧而达到高效率》,ABBTechnik2(1994),第4-7页;及D.Viereck:《燃气透平GT13E2-一个对未来有指导意义的方案》,ABB Technik 6(1993),第11-16页),在一个燃气透平的压缩机和装备着多个预混合燃烧器的环形燃烧室之间安置一个集气室,在其中保持着很低的空气速度。通过这一集气室,便可实现对各燃烧器的均匀空气分配。附带地还可提供这样一个可能性:为燃烧室和透平拾取高压力水平的冷却空气。
从压缩机中出来的空气具有很高的速度(约200米/秒),而且为了回收其中所含的动能须尽可能无损耗地在一导向扩压器中加以减速。
为了实现有害物少的燃烧,使燃料和燃烧用空气在燃烧器中预先混合。但为了预混合过程的安全进行,在附有一理想配比混合物区的混合点处,空气速度必须很高,才能可靠地避免火焰的反冲。在集气室中速度还是极低(约10米/秒)的空气因此须在预混合区再加速到高速度(约80-100米/秒)。
为了把火焰在预混合燃烧器下游稳定到一个固定的地方,必须至少局部地在燃烧器下游再次大大降低燃烧室中的空气速度。在大多数情况下会产生一种局部的、有负速度的回流区。在燃烧室中,速度大约为50米/秒,以便于获得足够的停留时间,并保持热气和燃烧室壁之间的最小的热传导。在离开燃烧室时,又有一次加速,这样,在进入透平机时的燃气速度将可达到接近声速。
在压缩机出口和透平机入口之间的流动介质(空气、燃气/空气-混合物、热气)的多次加速和减速有一缺点,即它们必然造成损耗。此外,还要求对全部的空气流进行多次转向,这是因为根据转子动力学理由,压缩机出口和透平机入口之间的距离必须保持很小,从而按照已知的技术现状使得燃烧室的结构尺寸相当的大而复杂。
本发明试图避免上述所有缺点。本发明的基本任务是开发出一种装备着特殊预混合燃烧器的燃气透平环形燃烧室,该燃烧室的特点是结构尺寸小,而且与已知的技术相比它的结构也简化了,从而在减小总的压力损耗情况下改善了燃料和空气的预混合。
按照本发明,燃气透平环形燃烧室在一个压缩机下游安置,在其前壁上至少装着按环形布置的一系列预混合燃烧器。按照本发明,前述任务是通过下述措施加以解决的:在压缩机下游与其紧挨地设有作为扩散器加以设计制做的燃烧器空气通道,分别从最后一列压缩机的导向叶片至每个燃烧器各在该通道的下游端至少有一个纵向涡流发生器。在这里,在纵向涡流发生器中或者在纵向涡流发生器下游,至少配备一个燃料喷入口,在该燃料喷入口下游设置一个通入燃烧室的混合通道,该通道具有恒定的通道高度,其长度大致相当于液压通道高度的值的两倍。
燃烧用空气从压缩机出来后便直接分成单股空气流分配给燃烧器,及用于燃烧室和透平机的冷却。分配后用于燃烧器的空气的速度将大约减缓到压缩机出口处速度的一半,随后每个燃烧用空气通道至少在空气中发生一个纵向涡流,这时,在纵向涡流发出处或者在其下游掺入燃料,于是混合物便沿着混合通道流动,并随同一个总涡流流入燃烧室中,最后在那里燃烧。
此外,本发明的优点在于:与迄今的技术水平相比,燃烧室的尺寸较小,因而燃烧室中需要冷却的表面减少了。压缩机出口和透平机入口之间的压力损耗较小。另一方面,对各燃烧器可以实现甚佳的稳定的空气均匀分配,并改善燃料和燃烧用空气的预混合。
尤其可取的是,最后一列压缩机叶片的数目与预混燃烧器的数目是成整数比例的,特别是1或2的比率,因为这样,一条燃烧用空气通道可以直接地连接到最后一列压缩机的一个或两个叶片通道上。
有利的做法是,混合通道的横截面近似于一个圆,因为这样可以实现空气和燃料的充分混合。但是,混合通道具有矩形横截面也是可以设想的。同样地,在只有一列燃烧器时,混合通道是作为一个分段的环形间隙加以设计的。
此外,还有一个有优点的方法是,燃烧用空气通道呈螺旋状地安置在燃气透平的轴周围。由此可以节省轴向长度。
最后一个优点是,混合通道的轴线(即进入燃烧室中的混合物的流动方向)是这样设置的,使得该轴线与燃气透平的轴最好成一个45°角。从而可以进一步改善混合和火焰稳定性。
此外一个可取之点是,在有一个以上的环形预混合燃烧器系列的情况下,燃烧器一列与另一列在圆周方向上彼此反向地布置。这样,燃烧室中的总涡流趋于零。
还有一个有优点的做法是,附加地将空气喷入混合通道的边界层,因为这样可进一步防止火焰回冲到混合区中。
另一个优点是,在采用具有中等热值(MBtu)的燃料时,将该燃料混合在高空气速度(>100米/秒)的范围中。这样,即使这些燃料具有很高的火焰速度,也能可靠地避免至燃料喷射器的回火现象。
附图中示明了本发明的几个实施例。
附图中:
图1表示一个燃气透平装置的部分纵剖面图,该装置具有一个装有预混合燃烧器的符合技术现状的环形燃烧室;
图2表示一个燃气透平装置的部分纵剖面图,该装置具有本发明提出的四列式燃烧室;
图3表示一个二列式燃烧室的部分横截面图,与图2中所示四列式燃烧室的平面III-III的一个截面相对应;
图4表示压缩机出口和燃烧室前壁板之间的预混合区段(沿着图3中的IV-IV线)的展开图。
图中只示出为理解本发明所需的一些主要构成部分。未出示的设备部分例如有燃气透平的废气室及其废气管,烟道,以及压缩机部分的入口段和低压压缩机级段。工作介质的流动方向以箭头表示。
本发明按实施例及附图1至4加以详细说明如下。
图1按照技术现状首先示明一种具有环形燃烧室的燃气透平装置的部分纵剖面。在压缩机1和透平2(图上只示明第一导向叶片系列中的一个导向叶片3)之间,安置一个环形燃烧室4,该燃烧室装备着双锥结构的预混合燃烧器5。输送每个预混合燃烧器5的燃料6是经过燃料喷枪7实现的。环形燃烧室4是通过对流方式或者说利用冲击冷却方式加以冷却的。压缩机1基本上由叶片支座8和转子10组成,在该叶片支座中悬置着导向叶片9,而该转子则承接着运动叶片11。图1中也只示明最后的压缩机级段。在压缩机1的出口处安置了一个导向扩散器12。该扩散器通入一个安置在压缩机1和环形燃烧室4之间的集气室13。
从压缩机1出来的空气14具有很高的速度。在导向扩散器12中空气被减速,以便回收空气中所含的动能,这样,在与导向扩散器12相连的集气室13中只保持着很低的空气速度。由于上述结果,可以对燃烧器5实现空气14的均匀分配,同时可以毫无困难地为燃烧室4和透平2提供冷却空气。但另一方面为了安全实现空气14和燃料6的预混合过程,在燃料6混入点空气速度须是高的以避免火焰反冲,因此空气14在预混合区先必须再次大大加速,然后再在燃烧室4中的燃烧器5的下游降低其速度,这样做是为了达到火焰稳定的目的。在燃烧室4的下游端,于是再将燃气加速,使得在其进入透平2时达到接近声速的速度。在压缩机出口和透平入口之间的多次加速和减速必然带来一些损耗,而空气流所需的多次转向导致该装置要有相当大的结构高度。因此例如在按照技术现状(见图1)的一个170MWel级的燃气透平上,在燃烧室范围中的外径约为4.5米。
图2中就一个四列式燃气透平环形燃烧器示明本发明的一个实施例。与上述技术现状不同的是,空气14不再受集气室的限制而减速,而空气14的减速仍然只限于预混合段的速度水平。因此,可以免去总空气流的多次转向,并大大缩小燃烧室范围内的结构尺寸。
在图2中所示本发明的一个实施方案中,在压缩机出口下游与其紧挨地并在最后一列压缩机叶片的导向叶片9旁安置一个燃烧用空气分配系统,在该系统上,有作为扩散器设计的燃烧用空气通道15分别通往环形燃烧室4的每个燃烧器5。在燃烧用空气通道15的下游端至少有一个纵向涡流发生器16。在纵向涡流发生器16中或者在该发生器下游端至少配备一个燃料喷射器17,而且在该燃料喷射器17的下游设置一个通入燃烧室4的混合通道19,其高度H是不变的,其长度L大致相当于液压通道直径D的值的两倍。液压通道直径定义为通道横截面的四倍与通道周长之比。因此,在一个圆形通道上,H=D。
按照本发明因此省去了转向扩散器12和集气室13。
从压缩机1出来的空气从压缩机1的出口出来后直接被分配到若干个单独的通道中,也就是被分配到燃烧用空气通道15中和环形的靠毂部一侧安置的或靠壳体一侧安置的通道20中,后者供燃烧室4和透平2所需的冷却空气21用,在这里空气被置于高压状态。此外,还可从通道20中分取出空气22用于冲刷在混合通道19中形成的边界层。空气22仅对最里面的混合通道19示例性地表示出。
燃烧用空气通道15是作为扩散器加以设计的,并将空气速度大约减小到压缩机出口速度的一半值,在此最多可将动能的75%转化为压力增益。
在将燃烧用空气14减速到一个合适的速度值之后,即为了每个燃烧用空气通道15在纵向涡流发生器16上发生一个或几个纵向涡流。在纵向涡流发生器16中通过与之构成一体的一个燃料喷射器17,将诸如通过燃料喷枪7输送的燃料6掺混到空气14中。不言而喻,在另一个实施例中,也可以在纵向涡流发生器16的下游安置燃料喷射器17。所产生的纵向涡流保证了燃料6和燃烧用空气14在紧接着的混合通道19中实现良好的混合。混合通道19具有不变的高度H,其长度大约为液压通道直径D的两倍。在上述情况下,混合通道19具有圆形横截面,也是一条混合管。混合管轴线24在这里是与燃气透平的轴线25相平行地安置的。在其它的在这里未图示出来的实施例中,混合通道19也可以具有矩形的或多角形的横截面,或者它们也可以是分段的环形间隙。
下述做法是有利的:由纵向涡流发生器16产生的纵向涡流在混合通道19中形成一个总涡流,该涡流在燃料/空气-混合物23出来而进入燃烧室4中之后,被引向一个高紊流的火焰稳定区,这时涡流分离,而且在轴线上产生一个具有很小的或负的轴向速度的区域。火焰向混合区的反冲可以通过一个均衡的轴向速度分布形式来可靠地加以阻止,制定,其中在轴线上有一个速度峰值;还通过将空气22补充喷入混合通过19的边界层来解决。
有利的做法是,最后一列压缩机导向叶片9的数目和预混合燃烧器5的数目相互成整数比。这样,燃烧用空气通道15便可以直接连接到最后一列压缩机的比如一个或两个叶片通道上。
比较一下图1和2,便可清楚地看出:按照本发明,燃烧室壁需要加以冷却的表面减小了。现以一个170MWel级的燃气透平比如GT13E2为例。按照技术现状(图1),在燃烧器范围内的外径约为4.5米,但采用本发明得出的这个值仅为3.5米,从而使得结构尺寸减小大约20%。由于新型燃烧室中大大减小了需要冷却的面积,又由于在相当高的火焰温度条件下利用良好的预混燃烧器技术可以达到极低的氧化氮排放物(在15%O2和1850卡火焰温度时理论上约有5ppm(100万分之5)氧化氮),所以燃烧室的冷却可经过薄膜式冷却或溢出式冷却予以实现。
图3和图4示明另一个实施例。图3中示明的是一个两列式环形燃烧室的部分横截面,与图2中所示的四列式燃烧室的平面III-III中的一个断面相当。按照图3的环形燃烧室4因此配备着两列预混合燃烧器5。图3中的箭头均表示相邻系列中的燃烧器5彼此反向的布置角。通过这一彼此反向布置达到了在燃烧室4中不发生总涡流的目的。在上述实施例中,混合通道19的横截面不是圆的,而是椭圆的。
图4中示明的是压缩机出口和燃烧室前壁板18之间沿IV-IV的展开图。混合管轴线24相对于轴沿切线方向布置,即混合管轴线24与机器轴线25成一个约45°的角α。从而改善了燃烧室4中的混合和火焰稳定性。
在另一个未图示出来的实施例中,燃烧用空气通道15呈螺旋状地设置在燃气透平的轴线25周围,其目的是为了保持透平机的轴向长度尽可能小。
本发明特别适合于使用MBtu燃料,即具有中等热值的燃料,这种燃料例如在重油、煤和焦油气化时产生。在这种情况下,燃料的混合可很简单地转移到一个较高速度范围(>100米/秒),以便即使在使用具有高火焰速度特性的这些燃料时也能可靠地避免向燃料喷射器的回火。由最后一列压缩机产生的高频(>1000赫兹)压力脉动(叶片的空转)在这里特别有助于燃料-空气-混合过程,这是因为在压缩机1的端部和燃料喷射器17之间只需要一个短的减速段,即一个设计得比扩散器短的燃烧用空气通道15。
参考代号一览表1 压缩机2 透平3 项2的导向叶片4 环形燃烧室5 预混合燃烧器5a 外燃烧器列5b 内燃烧器列6 燃料7 燃料喷枪8 叶片支座9 项1的导向叶片10 转子11 项1的工作叶片12 转向扩散器13 集气室14 空气15 作为扩散器设计的燃烧用空气通道16 纵向涡流发生器17 燃料喷射器18 前壁板19 混合通道20 用于项21的通道21 冷却空气22 用于冲刷项19中的边界层的空气23 燃料/空气-混合物24 项19的轴线25 透平机轴线H 项19的高度L 项19的长度D 液压通道直径α 项24和项25之间所成的角度
Claims (15)
1.燃气透平环形燃烧室(4),它布置在一个压缩机(1)的下游,而且在它的前壁板(18)上至少装备着呈环形布置的一系列预混合燃烧器(5),其特征在于:在压缩机下游紧挨着它有作为扩散器设计的燃料通道(15),各自从最后一列压缩机的导向叶片(9)通往每一个燃烧器(5),在燃料通道的下游端至少有一个纵向涡流发生器(16),而在纵向涡流发生器(16)中或者在其下游至少配备一个燃料喷射器(17),同时在燃料喷射器(17)的下游安置一个混合通道(19),该混合通道终止于燃烧室(4)中,其不变的高度为(H),其长度为(L),大致相当于液压通道直径(D)值的两倍。
2.按照权利要求1中所述的燃气透平环形燃烧器,其特征在于:最后一列压缩机叶片(9)的数目与预混合燃烧器(5)的数目之比为整数。
3.按照权利要求2中所述的燃气透平环形燃烧室,其特征在于:最后一列压缩机的叶片(9)的数目与预混合燃烧器(5)的数目的比率为1。
4.按照权利要求2中所述的燃气透平环形燃烧室,其特征在于:最后一列压缩机的叶片(9)的数目与预混合燃烧器(5)的数目的比率为2。
5.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:燃料通道(15)呈螺旋状安置在燃气透平的轴线(25)周围。
6.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:混合通道(19)具有圆的横截面。
7.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:混合通道(19)具有一个矩形横截面。
8.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:混合通道(19)是一个分段的环形间隙。
9.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:混合通道(19)的轴线(24)和燃气透平的轴线(25)是平行的。
10.按照权利要求1中所述的燃气透平环形燃烧室,其特征在于:混合通道(19)的轴线(24)与燃气透平的轴线(25)形成一个角(α)。
11.按照权利要求10中所述的燃气透平环形燃烧室,其特征在于:角(α)约为45°。
12.按照权利要求1至11的一项中所述的燃气透平环形燃烧室,其特征在于:在有一列以上的环形布置的预混合燃烧器的情况下,列(5a)的燃烧器(5)与列(5b)的燃烧器以在依切线方向上彼此反向的方式布置。
13.按照权利要求1至12中所述的燃气透平环形燃烧室的运行方法,其特征在于:燃烧用空气(14)从压缩器(1)的出口出来后直接分配成单个空气流,分别用于各燃烧器及用于燃烧室和透平机的冷却,然后用于燃烧器(5)的空气(14)的速度在燃烧用空气通道(15)中被大约减速到压缩机出口处速度的一半值,继而在每个燃烧用空气通道(15)中,空气(14)中至少发生一个纵向涡流,这时,在纵向涡流发生处或者在其下游将燃料(6)混合进去,燃料和空气的混合物顺着混合通道(19)中流动,并以一个总涡流流入燃烧室(4)中并在那里燃烧。
14.按照权利要求13中所述的方法,其特征在于:将补充空气(22)喷射到混合通道(19)的边界层中。
15.按照权利要求13中所述的方法,其特征在于:在使用具有平均或中等热值(MBtu)的燃料(6)时,燃料在一高空气速度范围即大于100米/秒的范围内混合进去。
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Cited By (4)
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Families Citing this family (131)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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JP2003065537A (ja) * | 2001-08-24 | 2003-03-05 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器 |
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US20060156734A1 (en) * | 2005-01-15 | 2006-07-20 | Siemens Westinghouse Power Corporation | Gas turbine combustor |
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WO2007102807A1 (en) * | 2006-03-06 | 2007-09-13 | United Technologies Corporation | Angled flow annular combustor for turbine engine |
CN101981272B (zh) | 2008-03-28 | 2014-06-11 | 埃克森美孚上游研究公司 | 低排放发电和烃采收系统及方法 |
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US20090241547A1 (en) * | 2008-03-31 | 2009-10-01 | Andrew Luts | Gas turbine fuel injector for lower heating capacity fuels |
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US8221073B2 (en) * | 2008-12-22 | 2012-07-17 | Pratt & Whitney Canada Corp. | Exhaust gas discharge system and plenum |
US8133017B2 (en) * | 2009-03-19 | 2012-03-13 | General Electric Company | Compressor diffuser |
US8474266B2 (en) * | 2009-07-24 | 2013-07-02 | General Electric Company | System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle |
DE102009046066A1 (de) | 2009-10-28 | 2011-05-12 | Man Diesel & Turbo Se | Brenner für eine Turbine und damit ausgerüstete Gasturbine |
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US8381532B2 (en) * | 2010-01-27 | 2013-02-26 | General Electric Company | Bled diffuser fed secondary combustion system for gas turbines |
DE102010023816A1 (de) | 2010-06-15 | 2011-12-15 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenbrennkammeranordnung |
JP5913305B2 (ja) | 2010-07-02 | 2016-04-27 | エクソンモービル アップストリーム リサーチ カンパニー | 低エミッション発電システム及び方法 |
PL2588727T3 (pl) | 2010-07-02 | 2019-05-31 | Exxonmobil Upstream Res Co | Spalanie stechiometryczne z recyrkulacją gazów spalinowych i chłodnicą bezpośredniego kontaktu |
JP5906555B2 (ja) | 2010-07-02 | 2016-04-20 | エクソンモービル アップストリーム リサーチ カンパニー | 排ガス再循環方式によるリッチエアの化学量論的燃焼 |
BR112012031153A2 (pt) | 2010-07-02 | 2016-11-08 | Exxonmobil Upstream Res Co | sistemas e métodos de geração de energia de triplo-ciclo de baixa emissão |
TWI593872B (zh) | 2011-03-22 | 2017-08-01 | 艾克頌美孚上游研究公司 | 整合系統及產生動力之方法 |
TWI563166B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Integrated generation systems and methods for generating power |
TWI564474B (zh) | 2011-03-22 | 2017-01-01 | 艾克頌美孚上游研究公司 | 於渦輪系統中控制化學計量燃燒的整合系統和使用彼之產生動力的方法 |
TWI563165B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Power generation system and method for generating power |
US8978388B2 (en) | 2011-06-03 | 2015-03-17 | General Electric Company | Load member for transition duct in turbine system |
US8448450B2 (en) | 2011-07-05 | 2013-05-28 | General Electric Company | Support assembly for transition duct in turbine system |
US8650852B2 (en) | 2011-07-05 | 2014-02-18 | General Electric Company | Support assembly for transition duct in turbine system |
DE102011108887A1 (de) | 2011-07-28 | 2013-01-31 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenzentripetalringbrennkammer sowie Verfahren zur Strömungsführung |
US9328623B2 (en) * | 2011-10-05 | 2016-05-03 | General Electric Company | Turbine system |
EP2587021A1 (en) | 2011-10-24 | 2013-05-01 | Siemens Aktiengesellschaft | Gas turbine and method for guiding compressed fluid in a gas turbine |
US8701415B2 (en) | 2011-11-09 | 2014-04-22 | General Electric Company | Flexible metallic seal for transition duct in turbine system |
US8974179B2 (en) | 2011-11-09 | 2015-03-10 | General Electric Company | Convolution seal for transition duct in turbine system |
US8459041B2 (en) | 2011-11-09 | 2013-06-11 | General Electric Company | Leaf seal for transition duct in turbine system |
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US9353682B2 (en) | 2012-04-12 | 2016-05-31 | General Electric Company | Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation |
US9784185B2 (en) | 2012-04-26 | 2017-10-10 | General Electric Company | System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine |
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CA2830031C (en) * | 2012-10-23 | 2016-03-15 | Alstom Technology Ltd. | Burner for a can combustor |
US9574496B2 (en) | 2012-12-28 | 2017-02-21 | General Electric Company | System and method for a turbine combustor |
US9611756B2 (en) | 2012-11-02 | 2017-04-04 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
US10215412B2 (en) | 2012-11-02 | 2019-02-26 | General Electric Company | System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system |
US9708977B2 (en) | 2012-12-28 | 2017-07-18 | General Electric Company | System and method for reheat in gas turbine with exhaust gas recirculation |
US9869279B2 (en) | 2012-11-02 | 2018-01-16 | General Electric Company | System and method for a multi-wall turbine combustor |
US9803865B2 (en) | 2012-12-28 | 2017-10-31 | General Electric Company | System and method for a turbine combustor |
US10161312B2 (en) | 2012-11-02 | 2018-12-25 | General Electric Company | System and method for diffusion combustion with fuel-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system |
US9631815B2 (en) | 2012-12-28 | 2017-04-25 | General Electric Company | System and method for a turbine combustor |
US10107495B2 (en) | 2012-11-02 | 2018-10-23 | General Electric Company | Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent |
US9599070B2 (en) | 2012-11-02 | 2017-03-21 | General Electric Company | System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system |
US10208677B2 (en) | 2012-12-31 | 2019-02-19 | General Electric Company | Gas turbine load control system |
US8707673B1 (en) | 2013-01-04 | 2014-04-29 | General Electric Company | Articulated transition duct in turbomachine |
US9581081B2 (en) | 2013-01-13 | 2017-02-28 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
US9512759B2 (en) | 2013-02-06 | 2016-12-06 | General Electric Company | System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation |
US9938861B2 (en) | 2013-02-21 | 2018-04-10 | Exxonmobil Upstream Research Company | Fuel combusting method |
TW201502356A (zh) | 2013-02-21 | 2015-01-16 | Exxonmobil Upstream Res Co | 氣渦輪機排氣中氧之減少 |
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TW201500635A (zh) | 2013-03-08 | 2015-01-01 | Exxonmobil Upstream Res Co | 處理廢氣以供用於提高油回收 |
US9618261B2 (en) | 2013-03-08 | 2017-04-11 | Exxonmobil Upstream Research Company | Power generation and LNG production |
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US20140250945A1 (en) | 2013-03-08 | 2014-09-11 | Richard A. Huntington | Carbon Dioxide Recovery |
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US9458732B2 (en) | 2013-10-25 | 2016-10-04 | General Electric Company | Transition duct assembly with modified trailing edge in turbine system |
US9752458B2 (en) | 2013-12-04 | 2017-09-05 | General Electric Company | System and method for a gas turbine engine |
US10030588B2 (en) | 2013-12-04 | 2018-07-24 | General Electric Company | Gas turbine combustor diagnostic system and method |
US10227920B2 (en) | 2014-01-15 | 2019-03-12 | General Electric Company | Gas turbine oxidant separation system |
US9915200B2 (en) | 2014-01-21 | 2018-03-13 | General Electric Company | System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation |
US9863267B2 (en) | 2014-01-21 | 2018-01-09 | General Electric Company | System and method of control for a gas turbine engine |
US9631814B1 (en) * | 2014-01-23 | 2017-04-25 | Honeywell International Inc. | Engine assemblies and methods with diffuser vane count and fuel injection assembly count relationships |
US10079564B2 (en) | 2014-01-27 | 2018-09-18 | General Electric Company | System and method for a stoichiometric exhaust gas recirculation gas turbine system |
US10047633B2 (en) | 2014-05-16 | 2018-08-14 | General Electric Company | Bearing housing |
US10655542B2 (en) | 2014-06-30 | 2020-05-19 | General Electric Company | Method and system for startup of gas turbine system drive trains with exhaust gas recirculation |
US9885290B2 (en) | 2014-06-30 | 2018-02-06 | General Electric Company | Erosion suppression system and method in an exhaust gas recirculation gas turbine system |
US10060359B2 (en) | 2014-06-30 | 2018-08-28 | General Electric Company | Method and system for combustion control for gas turbine system with exhaust gas recirculation |
US9851107B2 (en) * | 2014-07-18 | 2017-12-26 | Ansaldo Energia Ip Uk Limited | Axially staged gas turbine combustor with interstage premixer |
US9819292B2 (en) | 2014-12-31 | 2017-11-14 | General Electric Company | Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine |
US9869247B2 (en) | 2014-12-31 | 2018-01-16 | General Electric Company | Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation |
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US10316746B2 (en) | 2015-02-04 | 2019-06-11 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
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US10094566B2 (en) | 2015-02-04 | 2018-10-09 | General Electric Company | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation |
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Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2627721A (en) * | 1947-01-30 | 1953-02-10 | Packard Motor Car Co | Combustion means for jet propulsion units |
GB1048968A (en) * | 1964-05-08 | 1966-11-23 | Rolls Royce | Combustion chamber for a gas turbine engine |
US3879939A (en) * | 1973-04-18 | 1975-04-29 | United Aircraft Corp | Combustion inlet diffuser employing boundary layer flow straightening vanes |
GB1581050A (en) * | 1976-12-23 | 1980-12-10 | Rolls Royce | Combustion equipment for gas turbine engines |
EP0059490B1 (de) * | 1981-03-04 | 1984-12-12 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Ringbrennkammer mit Ringbrenner für Gasturbinen |
DE3836446A1 (de) * | 1988-10-26 | 1990-05-03 | Proizv Ob Nevskij Z Im V I | Verfahren fuer die luftzufuhr zur brennzone einer brennkammer und brennkammer zur durchfuehrung dieses verfahrens |
US4991398A (en) * | 1989-01-12 | 1991-02-12 | United Technologies Corporation | Combustor fuel nozzle arrangement |
US5207064A (en) * | 1990-11-21 | 1993-05-04 | General Electric Company | Staged, mixed combustor assembly having low emissions |
CH684963A5 (de) * | 1991-11-13 | 1995-02-15 | Asea Brown Boveri | Ringbrennkammer. |
FR2711771B1 (fr) * | 1993-10-27 | 1995-12-01 | Snecma | Diffuseur de chambre à alimentation circonférentielle variable. |
DE4411623A1 (de) * | 1994-04-02 | 1995-10-05 | Abb Management Ag | Vormischbrenner |
DE4419338A1 (de) * | 1994-06-03 | 1995-12-07 | Abb Research Ltd | Gasturbine und Verfahren zu ihrem Betrieb |
DE4435266A1 (de) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | Brenner |
US5619855A (en) * | 1995-06-07 | 1997-04-15 | General Electric Company | High inlet mach combustor for gas turbine engine |
-
1995
- 1995-12-29 DE DE19549143A patent/DE19549143A1/de not_active Withdrawn
-
1996
- 1996-11-12 DE DE59610298T patent/DE59610298D1/de not_active Expired - Fee Related
- 1996-11-12 EP EP96810777A patent/EP0781967B1/de not_active Expired - Lifetime
- 1996-11-18 US US08/751,721 patent/US5839283A/en not_active Expired - Fee Related
- 1996-12-25 JP JP8345880A patent/JPH09196379A/ja not_active Abandoned
- 1996-12-27 CN CN96123618A patent/CN1088151C/zh not_active Expired - Fee Related
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CN102947650A (zh) * | 2010-06-18 | 2013-02-27 | 西门子公司 | 透平燃烧器 |
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CN102947650B (zh) * | 2010-06-18 | 2014-12-17 | 西门子公司 | 透平燃烧器 |
CN103874887A (zh) * | 2011-10-26 | 2014-06-18 | 斯奈克玛 | 在涡轮发动机中的环形燃烧室 |
CN103874887B (zh) * | 2011-10-26 | 2015-11-25 | 斯奈克玛 | 在涡轮发动机中的环形燃烧室 |
CN114576655A (zh) * | 2022-03-09 | 2022-06-03 | 西北工业大学 | 一种扰流柱带风扇的燃烧室火焰筒壁层板冷却结构 |
Also Published As
Publication number | Publication date |
---|---|
EP0781967A3 (de) | 1999-04-07 |
EP0781967B1 (de) | 2003-04-02 |
US5839283A (en) | 1998-11-24 |
CN1088151C (zh) | 2002-07-24 |
DE19549143A1 (de) | 1997-07-03 |
DE59610298D1 (de) | 2003-05-08 |
JPH09196379A (ja) | 1997-07-29 |
EP0781967A2 (de) | 1997-07-02 |
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