CN105829800B - 用于空气协助的燃料喷射的燃料喷嘴结构 - Google Patents
用于空气协助的燃料喷射的燃料喷嘴结构 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
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- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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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
- F23R3/02—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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/386—Nozzle cleaning
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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
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03343—Pilot burners operating in premixed mode
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
Abstract
一种燃料喷嘴,包括:外本体(36),其平行于中心线轴线(26)延伸,具有大体上圆柱形外表面(88)、前端(82)和后端(84),以及穿过外表面(88)的多个开口(94);与外本体(36)协作以限定环形空间(96)的外本体(36)内的内本体(32);环形空间(96)内的主喷射环(24),主喷射环(24)包括从其延伸的燃料柱(104);各个燃料柱(104),其与开口(94)中的一个对准,并且由与环形空间(96)连通的周边间隙(110)与开口(94)分开;主喷射环(24)中的周向主燃料通道(76);以及多个主燃料孔口(78),各个孔口(78)与主燃料通道(76)连通,并且延伸穿过燃料柱(104)中的一个。
Description
相关申请的交叉引用
本申请请求享有当前未决的2013年12月23日提交的美国临时专利申请61/920,002的权益。
技术领域
本发明涉及燃气涡轮发动机燃料喷嘴,并且更具体地涉及用于排出和吹扫燃气涡轮发动机燃料喷嘴的设备。
背景技术
飞行器燃气涡轮发动机包括燃烧器,其中燃烧焚烧来将热输入至发动机循环。典型燃烧器并入一个或更多个燃料喷射器,其功能在于将液体燃料引入到空气流中,使得其可雾化和焚烧。
分级燃烧器开发成以低污染、高效率、低成本、高发动机输出和良好发动机可操作性操作。在分级燃烧器中,燃烧器的喷嘴能够操作成通过两个或更多个分立级选择性地喷射燃料,各个级由燃料喷嘴内的独立燃料流动路径限定。例如,燃料喷嘴可包括连续地操作的引导级,以及仅在较高发动机功率水平下操作的主级。燃料流速还可能够在级中的各个内变化。
主级包括具有多个燃料喷射端口的环形主喷射环,该多个燃料喷射端口通过包绕的中心体将燃料排放到旋流混合器空气流中。关于该类型的燃料喷嘴的需要在于确保燃料不吸入到其中其可点燃而引起内部损坏和可能的不稳定操作的燃料喷嘴内的空隙中。
发明内容
该需要由本发明解决,本发明提供了一种并入构造成生成空气流的喷射结构的燃料喷嘴,该空气流吹扫和协助燃料流渗透到高速空气流中。
根据本发明的一个方面,一种用于燃气涡轮发动机的燃料喷嘴设备包括:环形外本体,外本体平行于中心线轴线延伸,外本体具有在前端与后端之间延伸的大体上圆柱形的外表面,并且具有穿过外表面的多个开口;设置在外本体内,与外本体协作来限定环形空间的环形内本体;设置在环形空间内的环形主喷射环,主喷射环包括从其沿径向向外延伸的燃料柱的环形阵列;各个燃料柱与外本体中的开口中的一个对准,并且由与环形空间连通的周边间隙与开口分开;沿周向方向在主喷射环内延伸的主燃料通道;以及多个主燃料孔口,各个主燃料孔口与主燃料通道连通,并且延伸穿过燃料柱中的一个。
根据本发明的另一个方面,各个开口与形成在外本体的内表面上的圆锥形井入口连通;并且各个燃料柱在形状上为截头圆锥形,并且包括圆锥形侧表面和平面径向面向的外表面,其中周边间隙限定在井入口与侧表面之间。
根据本发明的另一方面,各个燃料柱包括限定圆柱形侧表面的周壁和从周壁的远端表面沿径向向内凹入以限定喷雾井的沿径向面向外的底部;并且周边间隙限定在开口与侧表面之间。
根据本发明的另一方面,燃料柱沿径向向外延伸超过外本体的外表面。
根据本发明的另一方面,凹形倒角设置在燃料柱与主喷射环之间的接合部处。
根据本发明的另一个方面,凸形弯曲倒角毗邻开口形成在外本体中。
根据本发明的另一方面,协助端口在周壁与底部的交点附近形成在周壁中。
根据本发明的另一方面,各个燃料柱在平面视图中为长形的,并且包括限定侧表面的周壁和从周壁的远端表面沿径向向内凹入以限定喷雾井的沿径向面向外的底部;并且周边间隙限定在开口与侧表面之间。
根据本发明的另一方面,燃料柱中的至少一个并入沿平行于远端表面的线延伸的斜面形斜接口,斜接口具有在喷雾井处的最大径向深度,并且沿径向高度向外成锥形,在远离喷雾井的一定距离处连结远端表面。
根据本发明的另一方面,各个燃料柱的周壁在平面视图中为跑道形。
根据本发明的另一方面,设备还包括:设置在内本体内的包括最小直径的喉部的环形文氏管;设置在文氏管内的环形分流器;在文氏管与分流器之间延伸的外旋流导叶的阵列;设置在分流器内的引导燃料喷射器;以及在分流器与引导燃料喷射器之间延伸的内旋流导叶的阵列。
根据本发明的另一方面,设备还包括:能够操作成在变化的流速下供应液体燃料流的燃料系统;联接在燃料系统与引导燃料喷射器之间的引导燃料导管;以及联接在燃料系统与主喷射环之间的主燃料导管。
附图说明
本发明可通过参照连同附图进行的以下描述来最佳地理解,在该附图中:
图1为根据本发明的方面构造的燃气涡轮发动机燃料喷嘴的示意性截面视图;
图2为图1的燃料喷嘴的一部分的放大视图,示出了其主燃料喷射结构;
图3为图2中所示的燃料喷射结构的俯视平面视图;
图4为燃料喷嘴的一部分的截面视图,示出了备选的主燃料喷射结构;
图5为图4中所示的燃料喷射结构的俯视平面视图;
图6为燃料喷嘴的一部分的截面视图,示出了备选的主燃料喷射结构;以及
图7为图6中所示的燃料喷射结构的俯视平面视图。
具体实施方式
大体上,本发明提供一种具有喷射环的燃料喷嘴。主喷射环并入喷射结构,其构造成生成穿过包绕燃料孔口的受控间隙的空气流,其使燃料从主喷射环流动,并且有助于燃料流从燃料孔口渗透到高速空气流中。
现在,参照附图,其中相同的附图标记遍及各个视图表示相同元件,图1绘出了构造成将液体烃燃料喷射到燃气涡轮发动机燃烧器(未示出)的空气流中的类型的燃料喷嘴10的示例。燃料喷嘴10为"分级"类型的,意味着其能够操作成将燃料选择性地喷射穿过两个或更多个分立的级,各个级由燃料喷嘴10内的独立燃料流动路径限定。燃料流速还可能够在级中的各个内变化。
燃料喷嘴10连接于已知类型的燃料系统12,其能够操作成根据操作需要在变化的流速下供应液体燃料流。燃料系统将燃料供应至联接于引导燃料导管16的引导控制阀14,引导燃料导管16继而将燃料供应至燃料喷嘴10的引导器18。燃料系统12还将燃料供应至联接于主燃料导管22的主阀20,主燃料导管22继而供应燃料喷嘴10的主喷射环24。
出于描述目的,将参照燃料喷嘴10的中心线轴线26,其大体上平行于燃料喷嘴10将用于其中的发动机(未示出)的中心线轴线。所示燃料喷嘴10的主要构件设置成平行于且包绕中心线轴线26延伸,大体上作为一系列同心环。从中心线轴线26开始并且沿径向向外行进,主要构件为:引导器18、分流器28、文氏管30、内本体32、主环支承件34、主喷射环24和外本体36。将详细描述这些结构中的各个。
引导器18设置在燃料喷嘴10的上游端处,与中心线轴线26对准,并且由整流罩38包绕。
所示引导器18包括大体上圆柱形的轴向长形引导中心体40。引导中心体40的上游端连接于整流罩38。引导中心体40的下游端包括带圆锥形出口的会聚-发散的排放孔口42。
计量塞44设置在引导中心体40的中心开孔46内。计量塞44与引导燃料导管连通。计量塞44包括传递孔48,其使燃料流至限定在计量塞44与中心开孔46之间的供给环带50,并且还包括成角喷雾孔52阵列,其布置成接收来自供给环带50的燃料,并且以具有切向速度分量的旋流模式使其朝排放孔口42流动。
环带分流器28包绕引导喷射器18。其包括以轴向顺序的大体上圆柱形的上游区段54、最小直径的喉部56,以及下游扩散区段58。
内空气旋流器包括内旋流导叶60的径向阵列,其在引导中心体40与分流器28的上游区段54之间延伸。内旋流导叶60成形和定向成将旋流引起到穿过内空气旋流器的空气流中。
环形文氏管30包绕分流器28。其包括以轴向顺序的大体上圆柱形的上游区段62、最小直径的喉部64,以及下游扩散区段66。限定外空气旋流器的外旋流导叶68的径向阵列在分流器28与文氏管30之间延伸。外旋流导叶68、分流器28和内旋流导叶60物理地支承引导器18。外旋流导叶68定形和定向成将旋流引起到穿过外空气旋流器的空气流中。文氏管30的开孔限定用于穿过燃料喷嘴10的引导空气流的流动路径,大体上标为"P"。呈环形沿径向延伸的板的形式的热障层70可设置在扩散区段66的后端处。已知类型的热障涂层(TBC)(未示出)可施加于热障层70和/或扩散区段66的表面上。
环形内本体32包绕文氏管30,并且用作径向热障层以及下文所述的其它功能。
环形主环支承件34包绕内本体32。主环支承件34可连接于整流罩38,并且用作主喷射环24与静止安装结构如燃料喷嘴柄(其一部分示为物品72)之间的机械连接。
为环形形式的主喷射环24包绕文氏管30。其可由一个或更多个主支承臂74连接于主环支承件34。
主喷射环24包括沿周向方向延伸的主燃料通道76(见图2),其联接于主燃料导管22并且由主燃料导管22供应燃料。形成在主喷射环24中的主燃料孔口78的径向阵列与主燃料通道76连通。在发动机操作期间,燃料排放穿过主燃料孔口78。一个或更多个引导燃料通道80紧邻主燃料通道76延伸穿过主喷射环24。在发动机操作期间,燃料不断地循环穿过引导燃料通道80,以冷却主喷射环24,并且防止主燃料通道76和主燃料孔口78的结焦。
环形外本体36包绕主喷射环24、文氏管30和引导器18,并且限定燃料喷嘴10的外部范围。在组装时,外本体36的前端82连结于柄72(见图1)。外本体36的后端可包括并入引导在热障层70处的冷却孔86的环形沿径向延伸的挡板84。大体上圆柱形的外表面88在前端与后端之间延伸,大体上圆柱形的外表面88在操作中暴露于混合器空气流,其大体上表示为"M"。外本体36限定与文氏管30和内本体32协作的二次流动路径90。穿过该二次流动路径90的空气排放穿过冷却孔86。
外本体36包括称为"喷雾井"92的凹口的环形阵列。喷雾井92中的各个由与主喷射环24协作的外本体36中的开口94限定。主燃料孔口78中的各个与喷雾井92中的一个对准。
外本体36和内本体32协作,以限定被保护而免受包绕的外部空气流的环形第三空间或空隙96。主喷射环24容纳在该空隙中。在燃料喷嘴10内,流动路径提供用于末端空气流,以与空隙96连通,并且向空隙96供应保持高于喷雾井92附近的位置处的外部压力的小压力裕度所需的最小流。在所示实例中,该流由分别设置在文氏管30和内本体32中的小供应槽口98和供应孔100提供。
燃料喷嘴10和其构成的构件可由一种或更多种金属合金构成。适合的合金的非限制性实例包括镍基和钴基合金。
燃料喷嘴10的全部或部分,或其部分可为单个整体、一件式或整体式构件的部分,并且可使用制造过程制造,该制造过程涉及逐层构造或添加制作(与材料除去相反,如同常规机加工过程一样)。此类过程可称为"快速制造过程"和/或"添加制造过程",其中用语"添加制造过程"是本文中用于大体上表示此类过程的用语。添加制造过程包括但不限于:直接金属激光熔化(DMLM)、激光近净形制造(LNSM)、电子束烧结、选择性激光烧结(SLS)、3D打印如通过喷墨和激光喷射、立体光刻(SLS)、电子束熔化(EBM)、激光工程近净形(LENS),以及直接金属沉积(DMD)。
主喷射环24、主燃料孔口78,以及喷雾井92可构造成提供受控的二次吹扫空气路径,以及主燃料孔口78处的空气协助。参照图2和3,开口94为大体上圆柱形,并且沿径向方向定向。各个开口94与形成在外本体36的壁中的圆锥形井入口102连通。如图3中所示,邻近开口94的外本体36的局部壁厚可增大,以提供厚度来限定井入口102。
主喷射环24包括从其沿径向向外延伸的多个升高的燃料柱104。燃料柱104在形状上为截头圆锥形,并且包括圆锥形侧表面106和平面径向面向的外表面108。各个燃料柱104与开口94中的一个对准。开口94和相关联的燃料柱104一起限定喷雾井92中的一个。燃料柱104定位成与相关联的圆锥形井入口102协作限定环形间隙110。主燃料孔口78中的一个穿过燃料柱104中的各个,通过外表面108离开。
燃料柱104周围的这些小的受控间隙110用于两个目的。首先,窄通路容许最少吹扫空气流过,以保护内部末端空间或空隙96免于燃料进入。第二,离开间隙110的空气流提供空气协助,以便于从主燃料孔口78流动的燃料穿过喷雾井92且到局部高速混合器空气流M中的渗透。
图4和5示出了用于提供受控吹扫空气离开和喷射空气协助的备选构造。具体而言,这些图示出了主喷射环224和外本体236的一部分,它们可替换上文所述的主喷射环24和外本体36。本文中并未特别描述的主喷射环224和外本体236的任何结构或特征可假定为与上文所述的主喷射环24和外本体36相同。外本体236包括开口294的环形阵列,开口294大体上为圆柱形并且沿径向方向定向。
主喷射环224包括从其沿径向向外延伸的多个升高的燃料柱204。燃料柱204包括周壁202,其限定圆柱形侧表面206。径向面向的底部208从周壁202的远端表面212凹入,并且与周壁202组合来限定喷雾井292。主燃料孔口278中的各个与主燃料通道276连通,并且穿过燃料柱204中的一个,通过燃料柱204的底部208离开。各个燃料柱204与开口294中的一个对准,并且定位成与相关联的开口294协作限定环形间隙210。围绕燃料柱204的这些小受控间隙210容许最小吹扫空气流过,以保护内部末端空间或空隙296免于燃料进入。燃料柱204的基部214可构造有环形凹形倒角,并且外本体236的壁可包括开口294处的环形凸形弯曲倒角216。通过提供入口通路的平滑转向和面积减小,该构造促进了穿过环形间隙210的吹扫空气流的均匀分布和最大可达到的速度。
一个或更多个小直径协助端口218形成穿过各个燃料柱204的周壁202(在其与主喷射环224的底部208的交点附近)。穿过协助端口218的空气流提供空气协助,以便于从主燃料孔口278流动的燃料穿过喷雾井292并且到局部高速混合器空气流M中的渗透。
图6和7示出了用于提供受控吹扫空气离开和喷射空气协助的另一个备选构造。具体而言,这些图示出了主喷射环324和外本体336的一部分,它们可替换上文所述的主喷射环24和外本体36。本文中并未特别描述的主喷射环324和外本体336的任何结构或特征可假定为与上文所述的主喷射环24和外本体36相同。外本体336包括开口394的环形阵列,开口394在平面视图中为大体长形。它们可为卵形、椭圆形或其它长形形状。在所示特定实例中,它们为"跑道形"。如本文中使用的,用语"跑到形"意思是包括由半圆形端部连接的两个直平行侧的形状。
主喷射环324包括从其沿径向向外延伸的多个升高的燃料柱304。燃料柱304包括限定侧表面306的周壁302。在平面视图中,燃料柱304为长形,并且可为例如卵形、椭圆形或如所示的跑道形。圆形开孔形成在燃料柱304中,限定了从周壁302的远端表面312凹入的底部308,并且与周壁302组合限定喷雾井392。主燃料孔口378中的各个与主燃料通道376连通,并且穿过燃料柱304中的一个,通过燃料柱304的底部308离开。各个燃料柱304与开口394中的一个对准,并且定位成与相关联的开口394协作限定周边间隙310。围绕燃料柱304的这些小受控间隙310容许最小吹扫空气流过,以保护内部末端空间免于燃料进入。燃料柱304的基部314可构造有环形凹形倒角,并且外本体336的壁可包括加厚部分316,其可定形为开口394处的凸形弯曲倒角。通过提供入口通路的平滑转向和面积减小,该构造促进了穿过周边间隙310的吹扫空气流的均匀分布和高速。
一个或更多个小直径协助端口318形成穿过各个燃料柱304的周壁302,在其与主喷射环324的底部308的交点附近。穿过协助端口318的空气流提供空气协助,以便于从主燃料端口378流动的燃料穿过喷雾井392并且到局部高速混合器空气流M中的渗透。
燃料柱304的长形形状提供表面面积,以使燃料柱304中的一个或更多个的远端表面312可构造成并入斜面形"斜接口"。斜接口可布置成生成相邻主燃料孔口378之间的局部静压差。相邻主燃料孔口378之间的这些局部静压差可用于在仅引导操作的时段期间吹扫来自主喷射环324的停滞的主燃料,以便避免主回路结焦。
当在如图6中所见的截面中观看时,斜接口320在其与相关联的喷雾井392的界面处具有其最大或最高径向深度(关于远端表面312测得),并且在径向高度上向外成斜面或锥形,在远离喷雾井392的一定距离处连结远端表面312。在平面视图中,如图7中所见,斜接口320沿平行于远端表面312的线322远离主燃料端口378延伸,并且沿侧向宽度渐缩至其远端处的最小宽度。线322延伸的方向限定斜接口320的方位。图7中所示的斜接口320称为"下游"斜接口,因为其平行于旋转或旋流混合器空气流M的流线,并且具有关于混合器空气流M位于相关联的主燃料孔口378下游的其远端。
斜接口320的存在或不存在和斜接口320的方位在发动机操作期间确定相关联的主燃料孔口378处存在的空气静压。混合器空气流M呈现"旋流",即,其速度具有关于中心线轴线26的轴向和切向分量两者。为了实现以上提到的吹扫功能,喷雾井392可布置成使得主燃料孔口378中的不同主燃料孔口在发动机操作期间暴露于不同静压。例如,不与斜接口320相关联的主燃料孔口378中的各个将暴露于混合器空气流M中的大体上普遍的静压。出于描述的目的,这些在本文中称为"中性压力端口"。如图7中所见,与"下游"斜接口320相关联的主燃料孔口378中的各个将暴露于关于混合器空气流M中的普遍静压减小的静压。出于描述的目的,这些在本文中称为"低压力端口"。尽管未示出,但还有可能的是,一个或更多个斜接口320可定向成与下游斜接口320的方位相反。这些将为"上游斜接口",并且相关联的主燃料孔口378将暴露于关于混合器空气流M中的普遍静压的增大的静压。出于描述的目的,这些在本文中称为"高压力端口"。
主燃料孔口378和斜接口320可以以将生成有效驱动吹扫功能的压差的任何构造布置。例如,正压力端口可与中性压力端口交错,或者正压力端口可与负压力端口交错。
上文所述的本发明具有若干益处。其提供了用以防止燃料喷嘴内的空隙免于吸入燃料并且协助燃料渗透到空气流中的手段。
前文描述了用于燃气涡轮发动机燃料喷嘴的主喷射结构。本说明书(包括任何所附权利要求、摘要和附图)中公开的所有特征和/或如此公开的任何方法或过程的所有步骤可以以除其中此类特征和/或步骤中的至少一些互斥的组合外的任何组合来组合。
本说明书(包括任何所附权利要求、摘要和附图)中公开的各个特征可由用于相同、等同或类似目的的备选特征替换,除非明确另外指出。因此,除非明确另外指出,公开的各个特征为普通的一系列等同或类似特征的仅一个实例。
本发明不限于前述(多个)实施例的细节。本发明延伸至本说明书(包括任何所附权利要求、摘要和附图)中公开的特征中的任何新颖的一个或任何新颖的组合,或如此公开的任何方法或过程的步骤中的任何新颖的一个或任何新颖的组合。
Claims (15)
1.一种用于燃气涡轮发动机的燃料喷嘴设备,包括:
环形外本体,所述外本体平行于中心线轴线延伸,所述外本体具有在前端与后端之间延伸的大体上圆柱形外表面,并且具有穿过所述外表面的多个开口;
环形内本体,其设置在所述外本体内,与所述外本体协作以限定环形空间;
设置在所述环形空间内的环形主喷射环,所述主喷射环包括从其沿径向向外延伸的燃料柱的环形阵列;
各个燃料柱,其与所述外本体中的所述开口中的一个对准,并且由与所述环形空间连通的周边间隙与所述开口分开;
主燃料通道,其沿周向方向在所述主喷射环内延伸;以及
多个主燃料孔口,各个主燃料孔口与所述主燃料通道连通,并且延伸穿过所述燃料柱中的一个;
所述各个燃料柱包括限定侧表面的周壁,以及从所述周壁的远端表面沿径向向内凹入以限定喷雾井的沿径向面向外的底部,并且所述周边间隙限定在所述开口与所述侧表面之间。
2.根据权利要求1所述的设备,其特征在于,
所述侧表面包括圆柱形侧表面,所述底部包括环形凹槽。
3.根据权利要求2所述的设备,其特征在于,所述燃料柱沿径向向外延伸超过所述外本体的外表面。
4.根据权利要求2所述的设备,其特征在于,凹形倒角设置在所述燃料柱与所述主喷射环的接合部处。
5.根据权利要求2所述的设备,其特征在于,凸形弯曲倒角毗邻所述开口形成在所述外本体中。
6.根据权利要求2所述的设备,其特征在于,协助端口在所述周壁与所述底部的交点附近形成在所述周壁中。
7.根据权利要求1所述的设备,其特征在于,
各个燃料柱在平面视图中为长形。
8.根据权利要求7所述的设备,其特征在于,凹形倒角设置在所述燃料柱与所述主喷射环的接合部处。
9.根据权利要求7所述的设备,其特征在于,凸形弯曲倒角毗邻所述开口形成在所述外本体中。
10.根据权利要求7所述的设备,其特征在于,协助端口在所述周壁与所述底部的交点附近形成在所述周壁中。
11.根据权利要求7所述的设备,其特征在于,所述燃料柱中的至少一个并入沿平行于所述远端表面的线延伸的斜面形斜接口,所述斜接口具有在所述喷雾井处的最大径向深度,并且在径向高度上向外成锥形,在远离所述喷雾井的一定距离处连结所述远端表面。
12.根据权利要求7所述的设备,其特征在于,各个燃料柱的所述周壁在平面视图中为跑道形。
13.根据权利要求1所述的设备,其特征在于,所述设备还包括:
设置在所述内本体内的包括最小直径的喉部的环形文氏管;
设置在所述文氏管内的环形分流器;
在所述文氏管与所述分流器之间延伸的外旋流导叶的阵列;
设置在所述分流器内的引导燃料喷射器;以及
在所述分流器与所述引导燃料喷射器之间延伸的内旋流导叶的阵列;
空气流经分别设置在所述文氏管和内本体中的供应槽口和供应孔提供至所述周边间隙。
14.根据权利要求13所述的设备,其特征在于,所述设备还包括:
能够操作成在变化流速下供应液体燃料流的燃料系统;
联接在所述燃料系统与所述引导燃料喷射器之间的引导燃料导管;以及
联接在所述燃料系统与所述主喷射环之间的主燃料导管。
15.一种用于燃气涡轮发动机的燃料喷嘴设备,包括:
环形外本体,所述外本体平行于中心线轴线延伸,所述外本体具有在前端与后端之间延伸的大体上圆柱形外表面,并且具有穿过所述外表面的多个开口;
环形内本体,其设置在所述外本体内,与所述外本体协作以限定环形空间;
设置在所述环形空间内的环形主喷射环,所述主喷射环包括从其沿径向向外延伸的燃料柱的环形阵列;
各个燃料柱,其与所述外本体中的所述开口中的一个对准,并且由与所述环形空间连通的周边间隙与所述开口分开;
主燃料通道,其沿周向方向在所述主喷射环内延伸;以及
多个主燃料孔口,各个主燃料孔口与所述主燃料通道连通,并且延伸穿过所述燃料柱中的一个;
其中,各个开口与形成在所述外本体的内表面上的圆锥形井入口连通;并且
各个燃料柱在形状上为截头圆锥形,并且包括圆锥形侧表面和平面径向面向的外表面,其中所述周边间隙限定在所述圆锥形井入口与所述圆锥形侧表面之间。
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US20200041128A1 (en) | 2020-02-06 |
US20220186930A1 (en) | 2022-06-16 |
JP6606080B2 (ja) | 2019-11-13 |
WO2015147934A1 (en) | 2015-10-01 |
US10451282B2 (en) | 2019-10-22 |
CA2933536A1 (en) | 2015-10-01 |
JP2020034271A (ja) | 2020-03-05 |
US11300295B2 (en) | 2022-04-12 |
CN105829800A (zh) | 2016-08-03 |
US20170003030A1 (en) | 2017-01-05 |
JP2017502243A (ja) | 2017-01-19 |
EP3087321A1 (en) | 2016-11-02 |
EP3087321B1 (en) | 2020-03-25 |
CA2933536C (en) | 2018-06-26 |
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