CN102444911A - 具有贫预喷喷嘴燃料喷射系统的燃烧器 - Google Patents
具有贫预喷喷嘴燃料喷射系统的燃烧器 Download PDFInfo
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- 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
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
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- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
Abstract
本发明涉及具有贫预喷喷嘴燃料喷射系统的燃烧器。具体而言,本申请提供了一种用于燃烧燃料流(30)和空气流(20)的燃烧器(100)。燃烧器(100)可包括多个燃料喷嘴(120)、定位在燃料喷嘴(120)上游的贫预喷喷嘴燃料喷射系统(270),以及定位在燃料喷嘴(120)与贫预喷喷嘴燃料喷射系统(270)之间用于预混燃料流(30)和空气流(20)的预混环形空间(250)。
Description
技术领域
本申请主要涉及燃气涡轮发动机,并且更具体地涉及一种具有用于在燃料喷嘴上游混合燃料和空气的贫预喷喷嘴燃料喷射系统的燃烧器。
背景技术
在燃气涡轮发动机中,操作效率通常随燃烧流温度的升高而提高。然而,较高的燃烧流温度可产生较高水平的氮氧化物(″NOx″)及其它类型的排放物,而这受到美国联邦法规和州法规管制以及在国外还受到类似法规的管制。因此,在有效温度范围内操作燃气涡轮发动机与同时还确保NOx及其它类型的受管制排放物的输出保持在法定水平以下之间存在平衡作用。
若干类型的公知燃气涡轮发动机设计,例如使用干式低NOx(″DLN″)燃烧器的那些,通常在反应区或燃烧区的上游预混燃料流和空气流,以便通过多个预混燃料喷嘴来降低NOx排放物。这种预混趋于降低整体燃烧温度,且因此降低NOx排放物等。
然而,预混会出现多种操作问题,例如火焰稳定、逆燃、自动点火等。这些问题在使用高反应性燃料的情况下可能要特别考虑。例如,火焰有可能通过任何较大部分的氢或其它类型的燃料而维持在燃料喷嘴上游的头端中。因此,任何类型的富燃料气阱(pocket)都可维持火焰并导致燃烧器损坏。其它预混问题也可因燃料流和空气流方面的无规则性而引起。
因此,期望有一种改进的燃烧器设计。这种燃烧器设计将促进改善的燃料-空气预混,尤其是在使用高反应性燃料的情况下。此类燃烧器设计将促进这种良好混合,同时保持排放物低于法定水平,并避免或限制诸如火焰稳定、逆燃、自动点火等问题。
发明内容
因此,本申请提供了一种用于燃烧燃料流和空气流的燃烧器。燃烧器可包括多个燃料喷嘴、定位在燃料喷嘴上游的贫预喷喷嘴燃料喷射系统,以及定位在燃料喷嘴与贫预喷喷嘴燃料喷射系统之间用以预混燃料流和空气流的预混环形空间(annulus)。
本申请还涉及一种在燃烧器中提供空气流和多个燃料流的方法。该方法可包括以下步骤:将预混燃料流喷射到预混环形空间中、将空气流提供到预混环形空间中、沿预混环形空间将预混燃料流和空气流预混成预混流、将预混流提供给多个燃料喷嘴,以及沿多个燃料喷嘴将另一燃料流喷射到预混流中。
本申请还提供了一种用于燃烧燃料流和空气流的燃烧器。燃烧器可包括:各燃料喷嘴均包括钟形口的多个燃料喷嘴、定位在燃料喷嘴上游的贫预喷喷嘴燃料喷射系统,以及定位在燃料喷嘴与贫预喷喷嘴燃料喷射系统之间用以预混燃料流和空气流的预混环形空间。预混环形空间可沿燃料喷嘴的方向扩张。
对于本领域的普通技术人员而言,通过查阅以下详细描述同时结合多个附图和所附权利要求,本申请的这些及其它特征和改进将变得明显。
附图说明
图1为公知燃气涡轮发动机的简图。
图2为公知的燃烧器的侧截面视图。
图3为可如本文所述那样的具有贫预喷喷嘴燃料喷射系统的燃烧器的侧截面视图。
图4为用于结合具有图3中的贫预喷喷嘴燃料喷射系统的燃烧器使用的燃料喷嘴的侧截面视图。
零件清单
10燃气涡轮发动机
15压缩机
20空气流
25燃烧器
30燃料流
35燃烧气流
40涡轮
45负载
50燃烧室
55燃料喷嘴
60旋流器
65空气通路
70衬套
75壳体
80过渡件
100燃烧器
110燃烧室
120燃料喷嘴
130中央喷嘴
140外喷嘴
150燃料通道
160燃料喷射器
170旋流器
180钟形口
200空气通路
210盖板(cap baffle)
220壳体
230端盖
240端罩
245渐缩形状
250预混环形空间
260转向部分
270贫预喷喷嘴燃料喷射系统
280燃料喷射器
285空气动力翼状形状
290喷射孔
300预混燃料
310预混流
具体实施方式
现参看附图,所有附图中相似的数字表示相似的元件,图1示出了可如本文所述那样的燃气涡轮发动机10的简图。燃气涡轮发动机10可包括压缩机15。压缩机15压缩进入的空气流20。压缩机将压缩的空气流20输送至燃烧器25。燃烧器25使压缩的空气流20与压缩的燃料流30相混合,且点燃混合物以形成燃烧气流35。尽管仅示出了单个燃烧器25,但燃气涡轮发动机10可包括任意数目的燃烧器25。燃烧气流35继而输送至涡轮40。燃烧气流35驱动涡轮40以便产生机械功。在涡轮40中所产生的机械功驱动压缩机15和外部负载45,如发电机等。
燃气涡轮发动机10可使用天然气、各种类型的合成气和/或其它类型的燃料。燃气涡轮发动机10可为由General ElectricCompany(Schenectady,New York)提供的多种不同燃气涡轮发动机中的任一种。燃气涡轮发动机10可具有不同的构造,且可使用其它类型的构件。文中还可使用其它类型的燃气涡轮发动机。多个燃气涡轮发动机、其它类型的涡轮以及其它类型的动力生成设备还可在此一起使用。
图2示出了公知的燃烧器25的简化实例。总的来说,燃烧器25可包括燃烧室50,燃烧室50具有定位于其中的多个燃料喷嘴55。燃料喷嘴55可为预混喷嘴,在其上具有一个或多个旋流器60。旋流器60有助于空气流20和燃料流30的预混。进入空气通路65可限定在燃烧室50的衬套70与壳体75之间。过渡件80可定位在燃烧室50的下游。其它类型的燃烧器构造也是公知的。
空气流20可从压缩机15经由进入空气通路65进入燃烧器25。空气流20可反转方向,且可在燃料喷嘴55和旋流器60附近与燃料流30相预混。混合的空气流20和燃料流30可在燃烧室50内燃烧。然后,燃烧气流35可经由过渡件80朝涡轮40排出。取决于燃烧器25的性质,燃烧器25可使用初级燃料,其可为穿过旋流器60的燃料气体;二级燃料和三级燃料,其可为预混燃料气体;以及贫预喷喷嘴燃料喷射系统,其可仅在旋流器60上游喷射少量燃料。其它类型的燃料回路和构造也是公知的。
图3和图4示出了可如本文所述那样的燃烧器100。类似于上述燃烧器25,燃烧器100包括燃烧室110,在其中定位有多个燃料喷嘴120。在该实例中,中央喷嘴130可由多个外喷嘴140包绕。任何数目的燃料喷嘴120都可在此使用。
总的来说,各燃料喷嘴120均可包括通常用于液体燃料的中央燃料通道150。燃料喷嘴120还可包括多个燃料喷射器160。燃料喷射器160可定位在一个或多个旋流器170附近。燃料喷射器160可结合预混燃料等使用。其它类型的燃料回路也可在此使用。燃料喷嘴120还可包括在其上游端处用于进入空气流20的钟形口180。任何数目或形状的钟形口180都可使用。
燃烧器100还包括进入空气通路200。进入空气通路200可限定在衬套或盖板210与壳体220之间。盖板210可附接到端盖230上,且可沿朝端罩240的方向以外扩形状245扩张。同样,壳体220可为外扩的,使得壳体220在朝端罩240的流动方向上具有较大直径。盖板210和壳体220可限定预混环形空间250。因此,总体的预混环形空间250也朝端罩240扩张。预混环形空间250可具有在端罩240附近朝燃料喷嘴120的平滑转向部分260。预混环形空间250可提供扩散或不提供。其它构造也可在此使用。
贫预喷喷嘴燃料喷射系统270也可围绕位于盖板210与壳体220之间的进入空气通路200定位在端盖230周围。贫预喷喷嘴燃料喷射系统270可具有多个燃料喷射器280。燃料喷射器280可具有空气动力翼状或流线型形状285以优化火焰稳定阻力。燃料喷射器280在其中均可具有多个喷射器孔290。燃料喷射器280的数目和喷射孔290的数目可针对预混而优化。其它构造也可在此使用。预混燃料300可在其中流动。
使用中,预混燃料300经由贫预喷喷嘴燃料喷射系统270的燃料喷射器280喷射到经由进入空气通路200传送的进入空气流20中。燃料喷射器280的空气动力翼状形状285最大限度地减小了喷射器280上或后方的火焰稳定的风险。因此,预混燃料300和空气流20沿预混环形空间250的长度预混成预混流310。由于盖板210和壳体220两者都沿朝端罩240的方向扩张,故预混环形空间250使空气减慢且恢复一定的静压。因此,这种外扩形状容许比典型圆柱形壳体更大的扩散。预混还除去了可能维持火焰的任何富含燃料的气阱。因此,预混环形空间250的长度与喷射器280的数目和间距一起提供了在预混环形空间250内改善的预混。预混流310在离开环形空间250之前将完全混合。
然后,预混流310在转向区段260附近转向并进入燃料喷嘴120。由于空气流20在预混环形空间250内减慢,故预混流310容易在转向区段260附近转向到燃料喷嘴120中,而不会发生再循环或流动不足。因此,燃料喷嘴120可使用钟形口180,与常规流动调节器相反这会导致压降较低。预混流310在燃烧室110中燃烧之前,与来自于燃料喷射器160或其它的常规燃料流30进一步混合。
预混环形空间250可使较大百分比的总燃料流流动,而不会不利地影响排放物。同样,通过卸下燃料喷嘴120,也即通过将燃料带走,则还可增强燃料喷嘴的总体火焰稳定性能。在较宽范围内调节输送至贫预喷喷嘴燃料喷射系统270的总燃料的百分比的能力可提供压力比控制,以便处理燃料组分方面的波动。燃料喷嘴120的总压力比可针对动力进行优化,而不会改变喷嘴当量比等。此外,燃料喷射器160的尺寸也可减小。
因此,使用贫预喷喷嘴燃料喷射系统270的燃料喷射器280和预混环形空间250降低了NOx排放物、减小了压降,以及提供了在MWI(修正沃布指数)能力和燃料反应性两者方面的提高的燃料灵活性。因此,贫预喷喷嘴燃料喷射系统270可为燃料灵活的,包括使用高反应性燃料,如氢、乙烷、丙烷等。
应清楚的是,上文仅涉及本申请的一些实施例,且在不脱离由所附权利要求及其等同方案所限定的本发明的总体精神和范围的情况下,本领域的普通技术人员可作出许多变化和修改。
Claims (15)
1.一种用于燃烧燃料流(30)和空气流(20)的燃烧器(100),包括:
多个燃料喷嘴(120);
定位在所述多个燃料喷嘴(120)上游的贫预喷喷嘴燃料喷射系统(270);以及
定位在所述多个燃料喷嘴(120)与所述贫预喷喷嘴燃料喷射系统(270)之间以预混所述燃料流(30)和所述空气流(20)的预混环形空间(250)。
2.根据权利要求1所述的燃烧器(100),其特征在于,所述多个燃料喷嘴(120)中的各个均包括燃料喷射器(160)和旋流器(170)。
3.根据权利要求1所述的燃烧器(100),其特征在于,所述多个燃料喷嘴(120)中的各个均包括多个外燃料喷嘴(140)。
4.根据权利要求1所述的燃烧器(100),其特征在于,所述多个燃料喷嘴(120)包括钟形口(180)。
5.根据权利要求1所述的燃烧器(100),其特征在于,所述燃烧器(100)还包括盖板(210)和壳体(220),以及其中,所述盖板(210)和所述壳体(220)限定所述预混环形空间(250)。
6.根据权利要求5所述的燃烧器(100),其特征在于,所述盖板(210)和所述壳体(220)包括朝所述多个燃料喷嘴(120)扩张的外扩形状(245)。
7.根据权利要求1所述的燃烧器(100),其特征在于,所述预混环形空间(250)包括邻近所述多个燃料喷嘴(120)的平滑转向部分(260)。
8.根据权利要求1所述的燃烧器(100),其特征在于,所述贫预喷喷嘴燃料喷射系统(270)包括多个燃料喷射器(280)。
9.根据权利要求8所述的燃烧器(100),其特征在于,所述多个燃料喷射器(280)中的各个均包括流线型翼状形状(285)。
10.根据权利要求8所述的燃烧器(100),其特征在于,所述多个燃料喷射器(280)中的各个均包括多个喷射器孔(290)。
11.一种在燃烧器(100)中提供空气流(20)和多个燃料流(30)的方法,包括:
将预混燃料流(300)喷射到预混环形空间(250)中;
将所述空气流(20)提供到所述预混环形空间(250)中;
沿所述预混环形空间(250)将所述预混燃料流(300)和所述空气流(20)预混成预混流(310);
将所述预混流(310)提供给多个燃料喷嘴(120);以及
沿所述多个燃料喷嘴(120)将另一燃料流(30)喷射到所述预混流(310)中。
12.根据权利要求11所述的方法,其特征在于,沿所述预混环形空间(250)将所述预混燃料流(300)和所述空气流(20)预混成预混流(310)的步骤包括沿所述预混环形空间(250)使所述预混流(310)扩张。
13.根据权利要求11所述的方法,其特征在于,所述方法还包括沿所述预混环形空间(250)的转向部分(260)使所述预混流(310)反向的步骤。
14.根据权利要求11所述的方法,其特征在于,所述方法还包括使所述预混流(310)穿过旋流器(170)传送的步骤。
15.根据权利要求11所述的方法,其特征在于,所述方法还包括改变所述预混燃料(300)和所述另一燃料(30)的量的步骤。
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- 2011-10-06 JP JP2011221442A patent/JP6105193B2/ja active Active
- 2011-10-07 DE DE102011054308A patent/DE102011054308A1/de active Pending
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US5081843A (en) * | 1987-04-03 | 1992-01-21 | Hitachi, Ltd. | Combustor for a gas turbine |
CN1032230A (zh) * | 1987-09-04 | 1989-04-05 | 株式会社日立制作所 | 燃气轮机燃烧器 |
CN1095463A (zh) * | 1993-03-18 | 1994-11-23 | 株式会社日立制作所 | 气体燃料与空气混合燃烧的装置和方法 |
JPH07119971A (ja) * | 1993-10-21 | 1995-05-12 | Hitachi Ltd | ガスタービン燃焼器 |
CN1403745A (zh) * | 2001-08-24 | 2003-03-19 | 三菱重工业株式会社 | 燃气涡轮燃烧室 |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104266226A (zh) * | 2014-07-25 | 2015-01-07 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 一种贫燃料多孔喷射燃烧系统 |
CN104266226B (zh) * | 2014-07-25 | 2018-03-16 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 一种贫燃料多孔喷射燃烧系统 |
Also Published As
Publication number | Publication date |
---|---|
DE102011054308A1 (de) | 2012-04-12 |
FR2965894B1 (fr) | 2017-01-27 |
JP6105193B2 (ja) | 2017-03-29 |
US20120085100A1 (en) | 2012-04-12 |
CN102444911B (zh) | 2015-12-09 |
FR2965894A1 (fr) | 2012-04-13 |
JP2012083099A (ja) | 2012-04-26 |
US8991187B2 (en) | 2015-03-31 |
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