CN105570928B - 筒式燃烧室 - Google Patents

筒式燃烧室 Download PDF

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CN105570928B
CN105570928B CN201510735088.6A CN201510735088A CN105570928B CN 105570928 B CN105570928 B CN 105570928B CN 201510735088 A CN201510735088 A CN 201510735088A CN 105570928 B CN105570928 B CN 105570928B
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perforations
combustor
staggered
longitudinal axis
wall
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CN105570928A (zh
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F.鲍姆加特纳
M.T.莫勒
C.格拉伯
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Energy resources Switzerland AG
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Ansaldo Energia Switzerland AG
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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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/02—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in parallel arrangement
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Abstract

一种筒式燃烧室包括容纳多个筒(1)的壳体(11)。各个筒(1)包括壁(2)和围绕壁(2)的穿孔式冷却衬套(4)。相邻的筒(1)的冷却衬套(4)具有交错穿孔(5)。

Description

筒式燃烧室
技术领域
本发明涉及筒式燃烧室。特别地，筒式燃烧室是燃气涡轮的一部分。
背景技术
知道燃气涡轮包括压缩机，空气在压缩机中压缩，然后发送到燃烧室。在燃烧室中，供应燃料，并且燃料与来自压缩机的压缩空气一起燃烧，从而产生热气，热气发送到涡轮，以实现膨胀。
随着时间的推移，针对燃烧室(诸如筒式燃烧室)已经提出了多种不同的构造。筒式燃烧室具有壳体，壳体容纳多个筒；燃料和压缩空气供应到各个筒中，并且进行燃烧；然后来自所有筒的热气发送到涡轮。
各个筒典型地具有带有壁和围绕壁的穿孔冷却衬套的结构；在运行期间，压缩空气传送通过衬套的穿孔且冲击壁，从而冷却壁。
传统上，为了易于设计和制造，燃烧室的所有筒的衬套都是相同的，而且在穿过壳体的纵向轴线的平面上是对称的。在这个构造中，相邻的筒的衬套具有对向穿孔。
对向穿孔可在穿孔之间的区域处产生显著的压降，并且因而使有限的质量流通过穿孔，而且因此降低对筒壁的冷却。另外，由于压力会影响质量流且反之亦然，所以压力和质量流可变得不稳定，而且可开始波动，从而进一步提高压降和降低质量流。所有这些影响在面向涡轮的筒的部分处是最糟糕的，因为在这里典型地，相邻的筒的衬套较接近。
例如，图9显示相邻的筒1的两个部分(例如面向涡轮的筒部分)，它们各自具有围绕燃烧空间3的壁2和具有穿孔5的衬套4；标号6指示壳体轴线。图9显示穿孔5面向彼此，并且标号7指示穿孔之间的区域。
发明内容
本发明的一方面包括提供一种筒式燃烧室，其改进筒壁的冷却。
通过提供根据所附权利要求的筒式燃烧室来实现这些和另外的方面。
附图说明
根据在附图中以非限制性示例的方式示出的筒式燃烧室的优选但非排它性实施例的描述，另外的特性和优点将变得更加显而易见，其中：
图1显示筒式燃烧室的示意性正视图，在此图中，显示了衬套的仅几个穿孔；
图2显示图1的筒式燃烧室的筒的放大侧视图；
图3至7显示筒的不同的实施例；
图8显示图4的放大部分；
图9显示根据现有技术的相邻的筒部分。
部件列表
1筒
2壁
3燃烧空间
4衬套
5穿孔
5a一个衬套的穿孔在另一个衬套上的投影
6壳体轴线
7穿孔之间的区域
10燃烧室
11壳体
13交错长度
14筒的出口
16筒的纵向轴线
17纵向平面
17a平面
18室
19喷燃器。
具体实施方式
参照附图，这些图显示筒式燃烧室10；筒式燃烧室10优选为燃气涡轮的一部分，燃气涡轮还包括用于压缩空气的压缩机和涡轮，涡轮用于使燃料在筒式燃烧室10中与压缩空气燃烧所产生的热气膨胀。
筒式燃烧室10具有壳体11，壳体11容纳多个筒1；即使图中显示了仅六个筒，但是当然根据需要，各个数量的筒是可行的。
各个筒1包括壁2和围绕壁2的穿孔式冷却衬套4。相邻的筒1的冷却衬套4具有交错穿孔5，即，穿孔是不对齐的。
在不同的实施例中，穿孔5可在对应于相邻的筒1的整个长度13的交错长度上交错，如图3中显示的那样，或者仅在比筒长度更短的交错长度13上交错；在后一种情况下，交错长度13优选位于筒的出口14处(即，在面向涡轮的筒1的区域处，图4)，因为相邻的筒的衬套在那里较接近。
各个筒1具有纵向轴线16和穿过纵向轴线16的纵向平面17；穿孔5关于纵向平面17是不对称的。
另外，壳体11具有纵向轴线6，并且筒1的纵向平面17穿过壳体11的纵向轴线6。
穿孔可沿轴向或沿周边(即，在周界上)交错。图8显示两个相邻的筒1的一部分，其中穿孔沿轴向交错；图1显示相邻的筒的穿孔5(仅针对两个筒指示几个穿孔)沿周边交错；图5-7显示沿周边和沿轴向交错的两个相邻的筒的一部分；特别地，图5显示两个相邻的衬套4，而图6和7则显示图5的每一个衬套4；另外，在这些图中，标号5a标识一个衬套的穿孔5在另一个衬套上的投影。在这个示例中，这些投影垂直于穿过轴线6且在两个相邻的筒1之间的平面17a。
优选地，不同的筒1的衬套4的穿孔5具有相同图案，即，在整个衬套4上的图案是相同的，但为了易于设计和制造，衬套的相反的部分(即，面向其它衬套4的部分)彼此是不同的。
筒式燃烧室的运行根据所描述和示出的是显而易见的，并且基本如下。
来自压缩机的压缩空气供应到由壳体11限定的室18中。压缩空气与燃料在喷燃器19(一个或多个喷燃器连接到各个筒上)中混合，并且产生的混合物供应到筒1中。在筒1内发生燃烧，从而产生热气，热气发送到涡轮，以实现膨胀。
在室18内，压缩空气传送通过衬套4的穿孔5，并且冷却壁2(冲击冷却)。由于穿孔5是交错的，所以在其中相邻衬套4非常接近以至于进入一个衬套的穿孔的流可影响传送通过另一个衬套的穿孔的流的区域中没有沿相反方向的分流，使得可限制压降，并且压缩空气质量流较大(比使用现有技术的衬套构造更大)，其好处是壁2得到冷却。
当然所描述的特征可彼此独立地提供。
在实践中，可根据要求和现有技术来随意选择所使用的材料和尺寸。

Claims (9)

1.一种筒式燃烧室，其包括具有纵向轴线(6)并容纳多个筒(1)的壳体(11)，各个筒(1)包括壁(2)和围绕所述壁(2)的穿孔式冷却衬套(4)，其特征在于，相邻的筒(1)的冷却衬套(4)具有交错穿孔(5)，并且各个冷却衬套(4)的穿孔(5)垂直于穿过所述纵向轴线(6)且在两个相邻的筒(1)之间的平面(17a)投影在相邻的筒(1)的衬套(4)上。
2.根据权利要求1所述的筒式燃烧室，其特征在于，所述筒(1)具有纵向轴线(16)和穿过所述纵向轴线(16)的纵向平面(17)，其中，所述穿孔(5)关于所述纵向平面(17)是不对称的。
3.根据权利要求2所述的筒式燃烧室，其特征在于，所述壳体(11)具有纵向轴线(6)，其中，所述筒(1)的纵向平面(17)穿过所述壳体(11)的纵向轴线(6)。
4.根据权利要求3所述的筒式燃烧室，其特征在于，不同的筒(4)的冷却衬套(4)的穿孔(5)具有相同图案。
5.根据权利要求1所述的筒式燃烧室，其特征在于，所述穿孔(5)在相邻的筒(1)的整个长度(13)上是交错的。
6.根据权利要求1所述的筒式燃烧室，其特征在于，所述穿孔(5)在比所述筒的长度更短的长度(13)上是交错的。
7.根据权利要求6所述的筒式燃烧室，其特征在于，所述长度(13) 在所述筒的出口(14)处。
8.根据权利要求1所述的筒式燃烧室，其特征在于，所述穿孔(5)沿轴向交错。
9.根据权利要求1所述的筒式燃烧室，其特征在于，所述穿孔(5)沿周边交错。
CN201510735088.6A 2014-11-03 2015-11-03 筒式燃烧室 Active CN105570928B (zh)

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EP14191480.4A EP3015770B1 (en) 2014-11-03 2014-11-03 Can combustion chamber

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US11326518B2 (en) 2019-02-07 2022-05-10 Raytheon Technologies Corporation Cooled component for a gas turbine engine

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KR20160052410A (ko) 2016-05-12
US11149947B2 (en) 2021-10-19
EP3015770A1 (en) 2016-05-04
JP2016090224A (ja) 2016-05-23
US20160123593A1 (en) 2016-05-05
CN105570928A (zh) 2016-05-11

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