CN101272951A - 提供有预冷却器的双流涡轮发动机 - Google Patents

提供有预冷却器的双流涡轮发动机 Download PDF

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CN101272951A
CN101272951A CNA2006800353007A CN200680035300A CN101272951A CN 101272951 A CN101272951 A CN 101272951A CN A2006800353007 A CNA2006800353007 A CN A2006800353007A CN 200680035300 A CN200680035300 A CN 200680035300A CN 101272951 A CN101272951 A CN 101272951A
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A·波特
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    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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    • F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
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Abstract

本发明涉及设置有预冷却器的双流涡轮发动机。本发明的特征在于排走加热后的冷空气流(24)，至少一个排出管(25)被设置在室(12)内并将预冷却器(18)连接到至少一个排出孔(26)，所述排出孔被设置在排气喷管(3)的输出端内的内部整流器(10)上，而且至少差不多在机翼(16)的对面。

Description

提供有预冷却器的双流涡轮发动机
本发明涉及一种提供有预冷却器的双流式涡轮发动机。
已知，在飞行器上，有必要使热空气可用于实施某些功能，例如驾驶舱和客舱内的空气调节，或用于除去所述飞行器的某些部分上的冰。
还已知，这个热空气从所述飞行器的涡轮喷气发动机获取，而且必须在使用之前被显著地冷却。为此，提供热交换器，这一般公知为预冷却器，在所述热交换器中，从涡轮喷气发动机的中央发生器放出的热空气被来自风扇管道的冷空气冷却。
当然，在这个热交换过程期间；不仅从中央发生器放出的热空气被风扇管道的冷空气冷却，而且这个冷空气也被所述热空气加热。因此需要将这个加热后的冷空气排放到外部。
通常，这个加热后的冷空气在风结构的前面，在发动机悬挂吊架的上部被排放到外部，而且这导致增大所述飞行器的阻力的紊流和空气动力学干扰。
为了避免这个缺点，美国文件US-A-5729969提出将加热后的冷空气排放到环形横截面的室内，在中央热流发生器和风扇管道的内部整流器之间形成所述室，所述室于是装备有至少一个指向所述冷流的喷出孔。然而，例如这样的设置带有干扰热流发生器的热量调节的危险，因此带有加速涡轮发动机磨损的危险。
本发明的目的是弥补现有技术中的缺点。
为此，根据本发明，用于飞行器的双流式涡轮发动机包括：
-纵轴上的中空吊舱，在前部设置有进气口，在后部设置有喷管；
-中央热流发生器，被轴向地定位在所述吊舱内；
-风扇，被定位在所述中央发生器的前方的所述吊舱内，而且能产生用于所述涡轮发动机的冷流；
-由所述吊舱在内部承载的外部整流器和围绕所述中央发生器的内部整流器，所述外部和内部整流器在其间形成用于所述冷流的环形横截面的风扇管道，所述内部整流器与所述中央发生器限定围绕所述中央发生器的环形横截面的室；和
-预冷却器，接收从所述中央发生器放出的热空气流和从所述冷流放出的冷空气流，使得产生冷却后的热空气流，用来在飞行器上实施功能，例如空气调节或除冰，所述预冷却器同时产生加热后的冷空气流，
其特征在于，为了排出所述加热后的冷空气流，所述双流式涡轮发动机包括至少一个定位在所述室内的排出管，将所述预冷却器连接到至少一个排出孔，所述排出孔被设置在所述喷管离开吊舱处的所述内部整流器上，并至少近似地向上面对所述机翼。
从而，根据本发明，所述加热后的冷空气在出口处从所述涡轮发动机排出到所述冷流中(因此不引起紊流和空气动力学干扰，而且不在风扇管道的之内干扰所述冷流)，而在同时，所述加热后的冷空气在所述室内被所述排出管从大气隔离(因此不干扰所述中央热流发生器的热量调节)。
此外，可以理解，所述排出孔因此位于涡轮发动机的上部区域内，所述上部区域被设计成没有任何设备，以便防止涡轮发动机内的任何失火通过所述悬挂吊架波及到飞行器的机翼上。因此有利的是，所述排出管被至少部分地封装在所述室的上部内。也可以理解，在所述涡轮发动机的上部区域中定位所述加热后的冷空气排出管不会使涡轮发动机可能着火的状况加剧。无论怎样，这个排出管可有利地由能够承受高温的耐火材料制成，例如所述涡轮发动机的陶瓷。
在通常的方法中，所述预冷却器也可被定位在所述涡轮发动机的上部之内。然而，由于所述排出管，所述预冷却器可被封装在所述涡轮发动机的许多其他不同的位置上。
例如，在已知方法中，所述预冷却器可被定位在风扇管道中。所述预冷却器于是被浸入来自风扇的冷流之中，而且经受这个冷流的直接作用。作为替换方案，可以设置将一些所述冷流送到所述预冷却器的戽斗。这个替换形式是特别有利的，因为其允许调节阀被定位在所述戽斗和所述预冷却器之间，所以冷却后的热空气流的温度可通过调节冷空气进入预冷却器之内的吸入量而至少被部分地调节。
在另一个实施例中，所述预冷却器可以被定位在围绕中央发生器的所述室内。在该情况下，为了把冷空气流送到所述预冷却器，至少提供一个抽气管，所述抽气管被至少部分地定位在所述室中，并将所述预冷却器连接到至少一个抽气孔，所述抽气孔被设置在所述内部整流器上。于是有利的是，为所述抽气孔装备戽斗，用于从所述冷流抽入冷空气。
例如这样的实施例具有的优点是，调节阀可被安装在所述抽气管上以至少部分地允许热空气流的温度调节，所述热空气流通过进入到所述预冷却器之内的冷空气的吸入而被冷却。
附图的图示将使得容易理解本发明是如何被具体实施的。在这些附图中，相同的标记指示同样的元件。
图1以示意的轴向截面示出根据本发明的双流式涡轮发动机的第一实施例；
图2示意性地以透视图示出用于图1中的涡轮发动机的预冷却器的一个示范实施例；
图3和4以类似于图1的视图示出根据本发明的涡轮发动机的实施例的两个替换形式；
图5示意性地以透视图示出用于图3和4中的涡轮发动机的预冷却器的一个示范实施例；
图1、3和4中的每一个所示的双流式涡轮发动机包括纵轴L-L上的中空吊舱1，其在前部设置有进气口2，在后部设置有喷管3。所述中空吊舱1在内部承载整流器4，优选至少部分地涂覆声衰减涂层5，用于减小所述涡轮发动机的内部噪音。
在中空吊舱1的内部定位有：
-中央热流发生器6，其以公知的方式包括：低压和高压压缩机，燃烧室，低压和高压涡轮，而且所述中央热流发生器产生所述涡轮发动机的轴向热流7；
-风扇8，被定位在所述中央发生器6的前面，并产生用于所述涡轮发动机的环形冷流9；和
-内部整流器10，环绕所述中央发生器6，并在其自身和这个发生器的外壳11之间形成环绕所述发生器的环形横截面的室12。
内部整流器10和在其外部的整流器4在其间形成围绕中央发生器6的环形横截面的风扇管道13，冷流9流动经过所述风扇管道。
在内部整流器10和中央发生器6之间形成的是：在前部的环形进气狭缝14，以及在后部的环形排气狭缝15。因此，室12可被冷空气流f扫过，所述冷空气流在前部狭缝14处从冷流9流出，并在后部狭缝15处排出到热流7之中，这个冷空气流f为中央发生器6提供温度调节。
此外，在通常的方法中，吊舱1由飞行器的机翼16(该机翼被部分地示出)通过悬挂吊架17支撑。
在图1所示的本发明的实施例中，提供了预冷却器18，所述冷却器被定位在风扇管道13的上部13S内。通过导管20从中央发生器6为这个预冷却器18提供热空气19，在所述导管20上有热空气调节阀21。由预冷却器18产生的冷却后的热空气22通过导管23送至用户设备(未示出)，所述导管23经过悬挂吊架17并可以设置有调节阀23V。对预冷却器18产生的加热后的冷空气24来说，其通过排出管25在喷管3的出口排出到冷流9中，所述排出管被定位在环形横截面的室12内，而且把预冷却器18连接到排出孔26，在所述喷管3后面的内部整流器10内形成所述排出孔，而且所述排出管至少近似地向上面对机翼16和吊架17，也就是在所述内部整流器10的上部。
导管25由能够承受高温的耐火材料制成，例如由陶瓷制成，而且优选完全被定位在室12的上部12S内。
预冷却器18可具有图2所示的公知的结构。在这个图2的示范实施例中，预冷却器18包括交换器管道的集合体27，所述交换器管道共同由导管20提供热空气19，而且通过冷流9穿过所述集合体27来冷却。所述交换器管道共同连接于导管23，冷却后的热空气流22流动经过所述导管23。
例如，交换器管道的集合体27具有船的船头的形状，而且在后部通过隔壁28封闭，使得形成空腔29，冷流9的一部分进入所述空腔，经过所述集合体27并被所述集合体的交换器管道加热以形成加热后的冷空气流24。用于排出气流24的导管25通过空腔29的开口30与所述空腔29连通，所以所述导管25能通过室12的上部128运送所述气流24直到孔26。
在图3所示的本发明的实施例中，可以再次看到具有标记1至12、12S、13S、13至17、19至26和23V的全部元件，而且已经参照图1在上文对所述元件进行了描述。然而，与图1的实施例相比，预冷却器18已被预冷却器31替换，所述预冷却器31的示范实施例由图5示出。另外，在风扇8这一侧有戽斗32，能够抽入一些冷流9并沿着设置有调节阀34的导管33将其送至预冷却器31。
在图5的示例中，预冷却器31包括交换器管道的集合体35，所述交换器管道共同由导管20提供热空气19，而且被冷流9的一部分冷却，所述冷流被戽斗32吸取并由导管33运送。所述集合体35的交换器管道共同连接于导管23，冷却后的热空气流22流动经过所述导管23。
交换器管道的集合体35形成外壳36的一个壁，由戽斗32吸取的冷流9的所述部分进入所述外壳，经过所述集合体35并形成加热后的冷空气流24。用于排出气流24的导管25通过外壳36的开口37与所述外壳36连通，所以所述导管25能通过室12的上部12S运送所述气流24直到孔26。
在图4所示的本发明的实施例中，可以再次看到具有标记1至12、12S、13S、13至17、19、20、和22至26的全部元件，而且已经参照图1在所述元件进行了描述。在这个实施例中，阀21和23V被省略，尽管它们可以存在。另外，与图1的实施例相比，封装在风扇管道13的上部13S内的预冷却器18已被封装在室12的上部12S内的预冷却器38替换。这个预冷却器38可以是与图5的预冷却器31相似的类型。
定位在室12的上部12S中的抽气管39把预冷却器38连接到抽气孔40，所述抽气孔被设置在内部整流器10的前部。所述抽气孔40设置有戽斗41。因此，由孔40和戽斗41吸取的冷流9的一部分被送至预冷却器38以冷却热空气流19，并产生冷却后的热空气流22和加热后的冷空气流24。所述加热后的冷空气流从预冷却器38通过导管25排出，所述导管将所述加热后的冷空气流送至孔26。
调节阀42被安装在抽气管39上以控制冷空气的吸入量和冷却后的热空气流22的温度。

Claims (10)

1.一种用于飞行器的双流式涡轮发动机，所述涡轮发动机通过悬挂吊架(17)从这个飞行器的机翼(16)悬挂，所述涡轮发动机包括：-纵轴(L-L)上的中空吊舱(1)，在前部设置有进气口(2)，在
后部设置有喷管(3)；
-中央热流发生器(6)，被轴向地定位在所述吊舱(1)内；
-风扇(8)，被定位在所述中央发生器(6)的前方的所述吊舱(1)内，而且能产生用于所述涡轮发动机的冷流(9)；
-由所述吊舱(1)在内部承载的外部整流器(4)和围绕所述中央发生器(6)的内部整流器(10)，所述外部和内部整流器在其间形成用于所述冷流(9)的环形横截面的风扇管道(13)，所述内部整流器(10)与所述中央发生器(6)限定围绕所述中央发生器(6)的环形横截面的室(12)；和
-预冷却器(18、31、38)，接收从所述中央发生器(6)放出的热空气流(19)和从所述冷流(9)放出的冷空气流，使得产生冷却后的热空气流(22)，用来在飞行器上实施功能，例如空气调节或除冰，所述预冷却器同时产生加热后的冷空气流(24)，
其特征在于，为了排出所述加热后的冷空气流(24)，所述双流式涡轮发动机包括至少一个定位在所述室(12)内的排出管(25)，将所述预冷却器(18、31、38)连接到至少一个排出孔(26)，所述排出孔被设置在所述喷管(3)离开吊舱(1)处的所述内部整流器(10)上，并至少近似地向上面对所述机翼(16)。
2.根据权利要求1所述的涡轮发动机，其特征在于：所述排出管(25)被至少绝大部分地定位在所述室(12)的上部(12S)内。
3.根据权利要求1和2中任一项所述的涡轮发动机，其特征在于：所述排出管(25)由能够承受高温的耐火材料制成。
4.根据权利要求1至3中任一项所述的涡轮发动机，其特征在于：所述预冷却器(18、31)被定位在所述风扇管道(13)内。
5.根据权利要求4所述的涡轮发动机，其特征在于：所述预冷却器(18)承受所述冷流(9)的直接作用，而且调节阀(21)被设置在导管(20)上，所述导管将所述热空气流(19)送至所述预冷却器(18)。
6.根据权利要求4所述的涡轮发动机，其特征在于：设置戽斗(32)，用于将一些所述冷流(9)送至所述预冷却器(31)，而且调节阀(34)被设置在所述戽斗(32)和所述预冷却器(31)之间。
7.根据权利要求1至3中任一项所述的涡轮发动机，其特征在于：所述预冷却器(38)被定位在围绕所述中央发生器(6)的所述室(12)内。
8.根据权利要求7所述的涡轮发动机，其特征在于：为了把所述冷空气流送到所述预冷却器(38)，至少有一个抽气管(39)被至少部分地定位在所述室(12)中，并将所述预冷却器(38)连接到至少一个抽气孔(40)，所述抽气孔被设置在所述内部整流器(10)上。
9.根据权利要求8所述的涡轮发动机，其特征在于：所述抽气孔(40)设置有戽斗(41)。
10.根据权利要求8和9中任一项所述的涡轮发动机，其特征在于：调节阀(42)被设置在所述抽气管(39)上。
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CN109564074A (zh) * 2016-08-08 2019-04-02 通用电气公司 用于热交换器应用的故障容错通道布置的系统
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CN109723558B (zh) * 2017-10-30 2022-07-29 通用电气公司 包括热管理系统的燃气涡轮发动机及其操作方法
CN111319776A (zh) * 2018-12-14 2020-06-23 空中客车简化股份公司 飞行器的推进系统和飞行器
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CN111305952A (zh) * 2020-02-26 2020-06-19 北京航空航天大学 一种基于外涵道加热的混合排气涡扇发动机推进系统
CN111577466A (zh) * 2020-06-22 2020-08-25 中国航空发动机研究院 航空发动机防冰引气预热与涡轮冷却引气预冷系统

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CA2621195C (fr) 2013-06-11
US7926261B2 (en) 2011-04-19
ATE420024T1 (de) 2009-01-15
JP2009510304A (ja) 2009-03-12
CN100542894C (zh) 2009-09-23
US20080230651A1 (en) 2008-09-25
WO2007034050A1 (fr) 2007-03-29
DE602006004767D1 (de) 2009-02-26
CA2621195A1 (fr) 2007-03-29
JP4805352B2 (ja) 2011-11-02

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