CN1107933A - 燃气轮机燃烧室 - Google Patents
燃气轮机燃烧室 Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
- F23C7/006—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes adjustable
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
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Abstract
一种具有形成两个通道(90,92)的空气进口的
燃气轮机燃烧室(4),每个通道有一沿周边分布的单
独可转动的弯曲叶片(84,86)的系列。弯曲叶片装
在轴向的二次燃料芯的供给管72上,该管穿过空气
进口通道。中间套筒和外套筒构成外环道,在其中放
置径向安装的二次燃料芯176。中间套筒和内套筒
构成供给冷却空气的内环道。一个沿周打孔的伸展
的阻尼件位于内环道中并引导冷却空气流过内套
筒。
Description
本发明涉及在压缩空气中燃烧料的燃烧室,更特别的是,本发明涉及一种低氧化氮(NOk)的燃气轮机的燃烧室。
在燃气轮机中,燃料在一个或多个燃烧室内的由压气机产生的压缩空气中燃烧。传统上,这类燃烧室有一个一次燃烧区,在该区内形成近似理论配比的燃料和空气的混合物,它以扩散燃烧过程进行燃烧。在一次燃烧区的下游燃烧室引入补充空气。虽然总的燃料/空气比明显地小于理论值,但由于在一次燃烧区的燃料空气混合物的局部富燃料性质,燃料/空气混合物很容易被触发点火并在宽阔的点火温度范围内获得良好的火焰稳定性。
遗憾的是,使用这种接近理论燃料/空气配比的混合物导致在一次燃烧区内很高的温度。这样的高温促使氧化氮(NOx)的形成,它被认为是一种对空气的污染物。众所周知,在贫的燃料/空气比下燃烧可减少NOx的生成。然而,要获得这样低的燃料/空气比的混合物要求燃料广泛地分布并要充分地混合于助燃的空气中。这可将燃料引入一次和二次的环形空气进口中来实现,在使用气体燃料的场合,使用围绕环管分布的燃料喷射管。
已发现,燃料和空气混合由使用了分别的通道将一次空气进口处的空气分成两股气流而得到增强。分布在这些通道周围的,由若干弯曲叶片组成的径向的离心式旋流器给空气的一旋转角有助于燃料和空气的混合。在每个一次进口通道中的旋流器是反向放置的,故使于混区出来的空气几乎没有净旋角。这种燃烧室公开于美国机械工程师学会1993年5月的文章“工业用RB211的干式低排放燃烧”中,作者为J.Willis等人。
遗憾的是,这类燃烧室有种种缺点。首先,弯曲叶片是总体地铸在一次空气进口的组件中,一旦燃烧室建成后它就不可能改变旋角。这就使它难以优化旋涡的状态,因为燃烧室的设计者不可能事先予测为了获得在最小压降下的最佳结果应给予空气的特定的旋角。其次,在这类燃烧室中不能烧液体燃料,因为燃料喷管仅仅取决于引入的燃料。第三,将燃料引入二次空气进口通道的燃料喷管是轴向的并位于通道进口的上游。这导致一部分燃料无法进入二次空气进口通道,会引起暴露于燃料中的燃烧室另件被脏物堵塞和污染。第四,包围一次燃烧区的内套筒遭受过热和损坏,特别是在其出口边缘处。
因而,本发明的总的目的是提供一种燃气轮机燃烧室,它具有可调的弯曲叶片,双燃料功能,精确注入燃料于二次予混区并对包围燃烧区的套筒以足够的冷却。
鉴于该目的,本发明归属於这样一种燃气轮机,它具有产生压缩空气的压气机部分,加热压缩空气的燃烧部分,该燃烧部分包括一个具有第一和第二环形通道的空气进口,它的空气流与压气机部分相通;其特征是有多个配置于第一通道内的第一弯曲叶片和多个配置于第二通道内的第二弯曲叶片以给予至少是压缩空气的(第一部分)以第一旋角和给予压缩空气的第二部分以第二旋角;为转动每个第一弯曲叶片和第二弯曲叶片进入至少是第一和第二位置的机构,用它可调节第一旋角和第二旋角;将第一弯曲叶片和第二弯曲叶锁定在一予先确定的角度方向的机构;以及多个具有多个燃料排出口的经向伸展入第一通道和第二通道的燃料排出口的将燃料注入空气进口的燃料注入器。
通过示于附图的,仅以举例子方式表达对一优先实施例的下列描述,本发明将变得更为明白。附图中,
图1是使用本发明的燃烧室的燃气轮机的示意图;
图2是图1所示的燃气轮机的燃烧部分的纵剖面;
图3是图2所示的燃烧室的纵剖面;
图4是图3所示的燃烧室的空气进口部分的立体图,为清楚起见,在局部剖视图中示出流动走向;
图5是沿图3中的Ⅴ-Ⅴ线剖切的横断面;
图6是沿图5中的Ⅵ-Ⅵ线部切的断面,它表示出在弯曲叶片附近的燃烧室空气进口的一部分,除此以外,图6中所示的弯曲叶片已从图5中所示的它们的位置转动了一个位置以便基本上在轴向走向于0°以在一个剖面上看到两个叶片中的定位器中的销钉;
图7是图3中由框线Ⅶ圈出的部分的详图;
图8是沿图6中的Ⅷ-Ⅷ线切割的断面图;
以及
图9是示提图6中的弯曲叶片支座的可替代的实施例。
参照这些图,在图1中示出燃气轮机1的示意图。燃气轮机1包含压气机2,它通过轴2b由透平6驱动。环境空气12被引入压气机2并被压缩。由压气机2产生的压缩空气8被导入燃烧系统,该系统包括一个或更多的燃烧室4和可引入气体燃料16和燃油14至燃烧室的燃料室的燃料喷咀18。在燃烧室4中,燃料在压缩空气8中燃烧,从而产生热的压缩的燃气20。
由燃烧室4产生的压缩的热燃气20被引入透平6,在那里它因膨胀而产生轴动力以驱动压气机2以及一负载,诸如一个发电机22。由透平6产生的膨胀了的燃气24被直接排出至大气中或排至联合循环的电流中的热再生式蒸汽发生器,然后再排至大气。
图2示出燃气轮机1的燃烧部分。沿圆周排列的燃烧室4的阵列,在图2中仅示出其中的一个,由交叉的火焰管82联接,示於图3,并由一外壳22所罩盖。每个燃烧室有一个一次区30和一个二次区32。自二次区32出来的热燃气20由导管5引至透平部分6,燃烧室4的一次区30由一支撑板28支撑。支撑板28贴靠在自外壳22伸出并包围一次区30的圆筒13上。二次区32由自支撑板13伸出的八根杆(图中未示)支撑。一次区30和二次区32分别支撑可减少由于不均匀的热膨胀引起的热应力。
参照图3,位于燃烧室4的一次区30内的是一次燃烧区36,其中燃烧着贫的燃料和空气的混合物。特别是,一次燃烧区36由一次区30的一个柱状内套筒44部分所包围。该由套筒44由柱状中间套筒42所围绕,而中间套筒42依次由柱状外套筒40所围绕。套筒40,42和44皆同心安放使在内套筒44和中套筒42间形成内环道70,在中套筒42和外套筒40间形成外环道68。交叉火焰管82,在图3中示出其中的一个,伸展通过套筒40,42和44与相邻的燃烧室4的一次燃烧区36相连接以便点火。
如图3所示,按照本发明,双燃料喷管18置于一次区30的中央部位。燃料喷管18由一柱状外套管48与中间套管49形成的外环通路56和柱状内套管51与中间套管49所形成的内环通路58组成。供油管60设置在内套管51内并向燃油喷咀54供燃油14。燃油14自喷咀54经由在外套管48中形成的燃油排出口52进入一次燃烧区36,气体燃料16’流经外环道56并经由多个在外套管48中形成的气体燃料出口50排入一次燃烧区36。此外,冷却空气38流经内环道58。
来自压气机2的压缩空气内在一次区30前端形成的一次空气进口通入一次燃烧区36。如图3所示,一次空气进口是由将进气分成两股气流8’和8”的第一和第二通道90和92所构成。第一进气道90有一在上游的径向部分和在下游的轴向部分。第一进气道90的上游部分在一经向伸展的圆形法兰88和导流件46的经向伸展部分之间形成。其下游部分在导流件46和燃料喷咀18的外套管48间形成并为第二进气道92所围绕。
第二进气道92亦有一在上游的经向部分和一在下游的轴向部分。第二进气道92的上游部分在导流件46的径向伸展部分和内套筒44之间形成。第二进气道的下游部分在导流件46轴向部分与内套筒44的轴向伸展部分之间形成并由通道90所围绕。如图3所示,第二进气道92的上游部分轴向地置于第一进气道90自上游部分而下的下游,而第二进气道92的下游部分围绕着第一进气道的下游部分。
如图3-5所示,若干经向放置的管状一次燃料喷射芯62沿一次室气进口作圆周分布1以便伸入第一进气道90和第二进气道92两者的上游部位。而排气体燃料排出口64沿每个一次燃料喷射芯62的长度方向分布以便引导气体燃料16”进入经由进气道90和92的气流8’和8”中去。如图4中清楚地表示出的气体燃料排出口64是这样的定向以便沿圆周顺时针和逆时针方向排出气体燃料16”。
亦如图3-5所示,若干弯曲叶片84和86沿周分布于进气道90和92的上游。在优先的实施例中,弯曲叶片置於每个一次燃料芯62之间。如图5所示,在进气道90中的弯曲叶片84给予气流8’以逆时针旋转(从轴向来看),故空气在径向形成一旋角面。在进气道92中的弯曲叶片86给予气流8”以顺时针旋转,故空气在经向形成一旋角A。由叶片84和86给予气流8’和8”的旋涡有助于保证在气体燃料16”和空气间的良好的混合,从而消除了局部的富燃料混合物以及随之而产生的高温,该高温能增加NOx的产生。
外环道68构成燃烧室二次空气的进口,空气流8”经过它流入二次区32,若干个二次气体燃料喷射芯76环绕二次空气进气道68沿周分布。根据本发明的一个重要方面,二次燃料芯76配置在二次空气进气道68内并经向走位的保证所有的气体燃料16”完全地进入二次空气进气道。自沿周伸展的集流管74,在图6中看得最清楚,向二次燃料芯76供给燃料16’’’。
两排气体燃料排出口78沿着每个二次燃料芯76的长度分布以便将气体燃料16’’’引入流经二次进气道68的二次气流8’’’中。如图5中清楚地表示,气体燃料出口78是规定方向的,以便沿圆周以顺时针和逆时针方向排放气体燃料。由於二次空气8'''当它进入进气道68时扭了90°的转弯,故是经向速度分布将是非线性的。因此,燃料排出口78之间的间距可以调整到附合速度分布,以此提供燃料和空气最佳混合。
运行时,经过中央喷咀18引入的燃料,燃油14或燃料气体16',在一次燃烧区36开始建立火焰。随着透平6负荷的增加要求较高的点火温度,由经过一次燃料芯62引入气体燃料16''来追加额外的燃料。因为一次燃料芯62导致在空气中更佳的燃料分布,它们产生比中尖喷咀更为贫的燃料/空气混合物,从而降低了NOx。于是,一旦在一次燃烧区36中点着了火,至中央喷咀18的燃料可以切断。除了由一次燃料芯62供给以外,对燃料的多需求可以通过二次燃料芯76供给了追加了燃料16''来满足。
如图3所示,最好是,弯曲叶片84和86互相方向相反地放置,使旋涡角A和B有相互抵消的趋势从导致在一次燃烧区36中的净旋涡角为零。弯曲叶片84和86的最佳角度,该角度将导致在最小的压降下有良好的混合,将取决于特定的燃烧室设计而且是难以予先予测的。所以,根据本发明的一个重要的方面,弯曲叶片84和86可以转成各种角度。
如图6和8所示,弯曲叶片84和86的旋转是由弯曲叶片84和86成对地沿一公共的轴可转动地安装而获得的。在优选的实施例中,它是在由供燃料16''至二次燃料芯76的管子72所构成的轴上装配可替代的弯曲叶片对来实现的,特别是1燃料芯的供给管72伸展穿过弯曲叶片84和86中的紧挨着的安装孔116和118。其它的弯曲叶片对均可转动地装在紧挨的对中螺栓上,如图9中的螺栓112,它代替二次燃料芯的供给管72。除了允许弯曲叶片可以转动以外,对中螺栓112还起将组合件紧固在一起的作用并提供导流件46和内套筒44的同心对中。
如图6所示,销钉96装在每个弯曲叶片中并伸展入孔98中,该孔对于弯曲叶片84而言是在清至88内,或对弯曲叶片86而言是伸入导流件46的径向部分。销钉96将弯曲叶片销定在予先确定的角度方向。
如图8所示,对每个弯曲叶片84,在法兰88中有若干锁定销钉的孔98。这些孔排列成弧状,故当燃烧室组装时,每个弯曲叶片84的角度可以通过变化销钉96所在孔的位置个别地调整。在导流件46中形成类似的孔98的排列以对弯曲叶片86的角度作个别的调整。于是,根据本发明,弯曲叶片84和86的角度可以个别地调整以获得对进入的空气的最佳旋角A和B。
图9示出本发明的可替代的实施例,利用它,所有的弯曲叶片对84和86均可转动地安装在紧挨着的对中螺栓112上,代之以将另一弯曲叶片对装在二次燃料芯的供给管72上。每个螺栓头112固定在法兰88上,而螺母114套在螺栓上以固定组合件。在该实施例中,燃料管72直接穿过通道90和92的进口伸至联通管74中。
由于内套筒44是直接暴露在一次燃烧区36的热燃气中,冷却该套筒,特别是在它的下游端部邻近出口71处,是十分重要的。根据本发明,这由在内套筒44的经向伸展部分开若干孔94来实现,见图3,这些孔94可谓来自压气机二的压缩空气8的一部分66进入在内套筒44和中间套筒42之间所构成的环形通道70。
如图7所示,根据本发明的一个重要方面,一个近似于圆柱的护隔物80位于通道70的出口处并在内套筒44和中间套筒42间伸展。在优先实施例中,护隔物80其下游末端108通过点焊104搭接在中间套筒42的下游处,可替代地,护隔物80的下游末端108可通过角焊搭接在中间套筒42上。护隔物80的前端106以弹簧承载着压在内套筒44外表面。如图3和7所示,护隔物80的前端106向上游伸展仅为内套筒44的长度的约 1/3 。然而,在某些场合下,它最好将护隔物80前端部106向上游伸展得更长些使护隔物围绕内套筒44的整个大直径部分。
如图7所示,若干个孔100分布在护隔物80的四周并将冷却空气66分为若干个射到内套筒44的外表面的射流102。于是护隔物80就冷却内套筒44而言可更有效地使用冷却空气66。
为防止内套筒44在其下游端振动,在本发明了一个实施例中,一些向内凸出的阻尼块122分布在护隔物80的四周为内套筒44提供摩擦阻尼,见图7。阻尼块122最好敷以耐磨涂尽。阻尼块122最好的尺寸分类,使它们与内套筒44间在装配时留有空隙。然而,在运行期间,在内套筒44和护隔物80之间的不均匀膨胀将导致内套筒比护隔物伸长得更多并与阻尼块122相接触,因而形成所希望的阻尼。于是1护隔物80不仅冷却了由套筒44,而且减少了它的振动。
Claims (7)
1、一种燃气轮机,它具有产生压缩空气(8)的压气机部分(2);和一个燃烧部分,所述的压缩空气(8)在其中被加热,所述的燃烧部分包括一个具有一个有第一和第二环形通道(90、92)的空气进口的燃烧室(4),以空气流将它与上述压气机部分(2)相联系;其特征是,有布置在第一通道(90)中的多个第一弯曲叶片(84)和布置在第二通道(92)中的第二弯曲叶片(86)以给予所述的压缩空气的至少是第一部分以第一旋角和给予所述的压缩空气的第二部分以第二旋角,所述的第一旋角与所述的第二旋角方向相反;有转动每个所述的第一弯曲叶片(84)和第二弯曲叶片(86),转到至少是第一和第二位置的机构,用它可调整所述第一旋角和第二旋角;和有将燃料引入所述空气进口的机构。
2、根据权利要求1的燃气轮机,其特征是在那里每个所述的第一叶片(84)与所述的第二叶片(86)一起绕一公共轴转动。
3、根据权利要求1的燃气轮机,其特征是,在那里所述的第一旋角与第二旋角方向相反。
4、根据权利要求1的燃气轮机,其特征是,在那里所述的分别用於转动第一和第二弯曲叶片的第一和第二机构,包含多个轴向的通管(72),每个所述的通管伸展穿过所述的第一弯曲叶片(84)的其中的一个和穿过所述的第二弯曲叶片(86)的其中的一个。
5、根据权利要求1的燃气轮机,其特征是,在那里所述的燃料引入机构的特征是有多个喷射芯(62)径向伸展入所述环形通道,每个所述的喷射芯具有多个在那里形成的燃料出口(64)。
6、根据权利要求4的燃气轮机,其特征是,有将每个所述的第一和第二弯曲叶片锁定在予先确定的角度方向的机构。
7、根据权利要求6的燃气轮机,其特征是,在那里所述的弯曲叶片的锁定机构是每个弯曲叶片有一销钉(98),每个所述的销钉伸展入它相对应的弯曲叶片内。
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- 1994-10-07 US US08/319,686 patent/US5479782A/en not_active Expired - Fee Related
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- 1994-10-25 ES ES94307823T patent/ES2123102T3/es not_active Expired - Lifetime
- 1994-10-25 DE DE69413352T patent/DE69413352T2/de not_active Expired - Fee Related
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- 1994-10-26 CA CA002134419A patent/CA2134419A1/en not_active Abandoned
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CN110454411A (zh) * | 2019-08-26 | 2019-11-15 | 西北工业大学 | 带有叶角可调风扇的压气机 |
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Also Published As
Publication number | Publication date |
---|---|
ES2123102T3 (es) | 1999-01-01 |
EP0654639B1 (en) | 1998-09-16 |
DE69413352T2 (de) | 1999-05-12 |
CA2134419A1 (en) | 1995-04-28 |
TW248585B (zh) | 1995-06-01 |
KR950011818A (ko) | 1995-05-16 |
DE69413352D1 (de) | 1998-10-22 |
AU7575694A (en) | 1995-05-18 |
US5479782A (en) | 1996-01-02 |
US5394688A (en) | 1995-03-07 |
EP0654639A1 (en) | 1995-05-24 |
JPH07180835A (ja) | 1995-07-18 |
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