CN1025725C - 空气循环环境控制系统及其空气调节方法 - Google Patents
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Abstract
在一个空气循环环境控制系统中,被压缩的环境空气先在第一透平机中膨胀,再由冷凝器将它所含的水蒸汽除去。然后将来自第一透平机的已冷却的输出空气在冷凝器中用作冷却剂,以在该处吸收被冷凝的水蒸汽的蒸发热。在通过冷凝器后,被加热了的冷却剂在第二透平机中膨胀。当压缩环境空气压力降得低于预定值时,那些削弱系统性能或成为不必要的部分循环被旁路绕开。
Description
本发明涉及空调用空气循环环境控制系统。
在稀薄大气中飞行的飞机通常用一个空气循环环境控制系统来冷却、过滤、压缩及用其它方法调节机舱空气。大多数装置中,由发动机压缩机部分、辅助动力装置或由它们两者提供的压缩的环境空气在一个空气循环透平机中得以膨胀,以提供机舱所需的冷而新鲜的空气源。为提供这个冷而新鲜的空气源,需要付出两方面的代价。第一,由于完成这些装置组装所需的诸组件有一定数量及各有其相应尺寸,这些设备就相当地增大了飞机的毛重。第二,贮存于被压缩的环境空气中的相当多量的能量要能满足一架即使是一般大小的飞机的冷却要求。在一个面临燃料涨价和提高环境关心的工业中,要以相当大的努力去减少这些系统的重量和能耗,而不损害各系统的性能。
由于被压缩的环境空气很易获得,它便成了一种用于机载环境控制系统的方便的风源。在大多数系统中,环境空气经过一个由来自飞机外的空气冷却的换热器,以将其温度降到周围的环境空气温度。为了进一步降低压缩的环境空气的温度,要将它在一个透平机中加以膨胀。如被膨胀的空气温度低于其露点时,其中所带的水蒸汽就会冷凝。当将压缩的环境空气进一步膨胀,以降温到低于其冰点时,冷凝的水就结冰了。当达到足够数量时,形成的冰就限制了系统中的流通并降低其性能,有可能达到系统不能工作的程度。
许多现有技术的系统利用一项或两项技术以确保不产生要堵住系统的冰。这些技术措施中的第一条就是简单地将透平机设计得使
其输出空气的温度保持在冰点之上。这样,不仅不会形成冰,而且可减小换热器这一占整套系统的重量的相当大百分比的笨重的组件的尺寸。但是,为了产生所需要的冷却能量,该种特点的系统要具有的能量远比透平机输出空气温度可低于冰点的这种系统的要多。
在这些系统中采用的第二种技术措施是将透平机运转到低于冰点,且为该系统提供有两种能力,即能感测出冰的存在及能给表明积累的冰已达到不允许的量的区域输送化冰的热流。这种系统的优点是:化冰机构是需要时使用的,因此,只要当探测出冰之时才从系统中提取能量。然而,输送化冰的热流需要附加的装置,这样也就增加了整个系统的重量。在美国专利3177679中,当位于两只透平机的每个的出口的诸恒温器指示出低于冰点的温度时,在连接透平机诸出口与诸热空气源的管道中的诸阀门就打开。在美国专利4127011中,一个压力通风系统将透平机的出口包围住。当该透平机出口的温度低于冰点时,阀门打开以将热空气送入压力通风系统,以防在透平机出口内表面上积聚冰。
关于第二技术措施的另一种方法是:将系统诸透平机运转到低于冰点,并在透平机输出空气中混入一股连续的热空气流,以提高输出空气的温度。在美国专利3877246中,描述了一个具有两只透平机的系统采用了该技术。第一透平机的输出空气与从机舱中的再循环回风和被压缩的热空气相混合,使它能在冰点下工作。该混合空气然后在第二透平机中膨胀。在进入机舱之前,从第二透平机中排出的输出空气先通过一沉淀器(precipitator),以除去任何夹带的水蒸汽。为使第二透平机下游的空气的温度保持在冰点之上,要调节位于连接第二透平机入口与第二透平机出口的管道中的阀门。在美国专利2628481中描述了一个类似的系统,只不过只具有一只透平机。再循环的机舱回风先被过滤,再将它分开。该经分开的再循环回风的第一半部分直接与离开透平机的空气相混合。然后在一水分
离器中除去夹带在该混合空气中的水蒸汽。离开分离器的空气流则在进入飞机之前,与经再循环的机舱回风的第二半部分相混合。
美国专利RE32100(美国专利4209993的再版)和4430867均描述了单透平机系统,该系统也使用包含在经再循环的空气中的热量,以使透平机下游的空气的温度保持在冰点之上。在进入透平机入口之前,压缩的环境空气首先通过一主冷凝器的热通道,以除去夹带的水蒸汽。离开冷凝器热通道的除湿的空气再在透平机中得以膨胀。在美国专利RE32100中,离开该透平机的输出空气则与热的机舱再循环回风相混合,并通过冷凝器的冷通道。在美国专利4430867中,离开透平机的输出空气,在进入机舱前,首先进入一换热器的冷通道。通过换热器的热通道的流体首先流过一设在机舱内的副冷凝器的冷通道。再循环回风经过该副冷凝器的热通道被放出,在当它流回到机舱之前被除湿。在副冷凝器冷通道中被加热的流体,在循环返回换热器之前,接着流入主冷凝器的冷通道。
揭示在美国专利RE32100和4430867中的诸系统,设置有用于在透平机中膨胀之前从空气流中除去水蒸汽的装置,这些系统能使透平机在较有效的低于冰点的温度下运转。但是,这些系统,在水蒸气从透平机输入流冷凝时,不能回收蒸发热,以致导致总的循环效率和冷却能量的丧失。
本发明的目的包括通过回收蒸发热提高空气循环环境控制系统的效率,上述蒸发热贮存于包含于压缩的环境空气中的水蒸汽中。
本发明的又一目的包括在这样的系统中提供一种装置,用此装置可在环境情况变化时改变循环,以求获得最佳的系统效率。
按照本发明,在冷凝进入第一透平机中的压缩的环境空气中的水蒸汽之后,离开系统第一透平机的空气在一第二透平机中得以膨胀。
还按照本发明,该系统包括这样的装置,它能使部分循环被旁
路,这部分循环使系统性能被削弱,或当供给该系统的压缩的环境空气的特性变化时使这部分循环成为不必要了。
由于依靠回收蒸发热而实现了提高热效率,本发明的诸实施例具有比同样重量和尺寸的现有技术系统更大些的空气流量和冷却能力,或者,具有与较重而大的现有技术系统相等的空气流量和冷却能力。
此外,第一和第二透平机的膨胀比可选择得使第一透平机输出空气流保持于冰点之上,而不在该透平机提取的能量将由第二透平机回收。这样就减轻了对结冰问题的牵挂,只要设一中等的化冰装置。
在巡航高度遇到的干燥低压大气中,本发明还可有选择地使第一透平机级和冷凝换热器旁路开,将空气流直接通到第二透平机。由于第一透平机的喷嘴面积比第二透平机的小,且压缩机限制气流,将此两部分旁路则能提高通过系统的容积流动速率。即使在较低压的大气中,当第二透平机的喷嘴面积太小而不能保证有足够的质量流量时,也可将第二透平机旁路,而达到通过系统的最大流量。
在对下面的、如附图表示的本发明的实施例的详尽描述后,本发明的上述和其它目的、特点和优点将会更清晰明了。
唯一的附图是包含有本发明的一空气循环环境控制系统的示意图。
如图所示,被压缩的环境空气9通过一导管10进入一空气循环环境控制系统。该空气源(未表示出)可是一辅助动力装置,燃气透平发动机的压缩机部分,或是这两者。进入系统的压缩空气的流动速率是由一与通向主换热器16的热通道的导管14相连的阀门12调节的。为了在该热通道中冷却空气,较冷的外部环境空气17流入一位于飞机(未表示出)外部的开孔20中,并通过一冷却通道。
为了在低空气流速航行中保持有足够的流量流过该冷却通道,有一通过一轴23由一对透平机24,26驱动的风机22通过一导管28与冷却通道的出口相连,以抽吸被加热的外部环境空气29流过该通道并经一导管30排出风机。在该风机排气导管30中的一阀门32可被调制,以调节冷却空气流动速率。
在主换热器16的热通道中冷却之后,主换热器输出空气33经过一导管34流到一也是由两透平机24,26驱动的压缩机36中。由该压缩级加热的压缩机输出空气37,接着通过一导管38流到副换热器40的热通道中,在此,该输出空气由通过一冷却通道流入的外部环境空气17所冷却,这情况与上述的主换热器16的冷却装置相似。
离开副换热器40的热通道的副换热器输出空气47,接着经过一导管48流到一冷凝器46的冷凝通道中。该冷凝器46中的传热表面的温度保持在等于或低于副换热器输出空气47的露点值。副换热器的输出空气从而得到除湿,并随后经过一导管56流入第一透平机24。在第一透平机中膨胀后的输出空气经过一导管50流入冷凝器46的冷却通道中,以冷却传热表面和吸收被冷凝的水蒸汽的蒸发热。所以,第一透平机24的膨胀比选择得能使第一透平机输出空气49温度保持得足够高,以防在冷凝器46的热通道中结冰,而提供通过系统的足够的质量流动速率。在大多数使用情况中,所需的第一透平机输出空气49的温度在35°F到40°F(1.7℃到4.4℃)之间,当实际的第一透平机输出空气温度降得低于所需值时,或如利用一些装置感测到在冷凝器46中出现了冰时,打开一阀门58,除湿的第一透平机输入空气59就流经一导管60并混和和加热第一透平机输出空气49。
有许多方法可用来感测冰的积聚。可将一压力传感器(未表示出)放在冷凝器46的热通道的入口和出口处。当通过热通道后的压
降超过某一预定值时,可断定在热通道中已形成了相当多的冰,以致限制了流通。另外的办法是,可设置一与一冷的高压空气源相连的节流孔的输出端,以将该冷空气排入到冷凝器46的热通道中。该节流孔尺寸要选择得使通过它的气流量较少。当监测流入该节流孔的空气的流动传感器或压力传感器表明压力增高了或流量减少了时,就可断定形成了冰并堵住了喷嘴开孔。
随着副换热器输出空气47流过冷凝器46的冷凝通道,由于冷凝作用,任何与输出空气混合的水蒸汽的蒸发热被冷却通道中的第一透平机输出空气49所回收了。所以,贮存在冷凝器冷却通道输出空气61中的全部回收的能量是该被回收的蒸发热和任何未被第一透平机24回收的能量之和。为了回收该能量,冷凝器冷却通道输出空气61流过一导管63并在第二透平机26中得以膨胀。
为使通入飞机机舱62中的空气流量和温度适中,第二透平机输出空气65流入一混合器64,在此,该输出空气就与再循环的机舱回风69混合。一风机68经过一导管66和一过滤器67从机舱62抽吸该再循环回风69。风机68的速度是可调的,以经过导管70向混合器64中提供为满足全部循环要求所需的再循环回风69的质量流动速率。
按照本发明的该系统还能随环境和工作条件作些改变,如不这样,将会降低整个系统的操作性和效率。一旦压缩环境空气9的压力太低,例如由一热线风速计73测得的质量流量低于必须满足机舱新鲜空气流量要求的值。此时,一主旁通阀72就打开,气流绕过冷凝器46和第一透平机24,而使副换热器输出空气47直接经过导管74循环流到第二透平机26中。当飞机巡航高度在较高时,若其外部环境空气17以及也包括压缩环境空气9的压力和湿度较低,主旁通路72通常就打开了。两只透平机24,26的膨胀比和喷嘴尺寸选择得:能在对其湿度关注的较低飞行高度中的较高压力环境空
气条件下使系统性能最佳。
第二透平机用于膨胀事先由第一膨胀机膨胀过的空气,所以其喷嘴较大,比起第一透平机喷嘴,其节流作用小的多。所以,直接流到第二透平机26的气流所受到的限制,比起首先流到冷凝器46和第一透平机24的气流所受的限制小得多。如减少对气流的节制,当压缩环境空气压力较低时,在数个周期中可保持较大的容积流动速率,使进入机舱的空气的质量流动速率足够大。
当主旁通阀72全开,且热线风速计73指示出:压缩的环境空气9的质量流动速率尚低于系统指定的最低速率时,副旁通阀76也就打开。除了第一透平机24和冷凝器46外,气流还绕过第二透平机26,而使副换热器输出空气47直接经过一第二旁通导管78流入混合器64。在这情况下,由于透平机24,26均不转动,所以压缩机36和风机22也停转。此时,压缩机36用作一节流器,压缩机出口端的压力低于入口压力。这样就使一位于一连接压缩机入口和出口的导管44中的单向阀42打开,使主换热器输出空气33绕过压缩机而直接流入副换热器40中。因此,在这些条件下,压缩的环境空气9直接从主换热器16流到副换热器40,并再流入混合器64中,使通过系统的容积流量最大。
即使当压缩的环境空气9的质量流动速率足够大,第二旁通阀76能被调节,以调节冷却性能和流过系统的容积流量。当容积流动速率或离开第二透平机出口的空气65的温度太低,第二旁通阀76就会打开。
尽管本发明已公开并对其实施例作了描述,那些熟悉本领域的技术人员会懂得:只要不离开本发明的精神实质和范围,在本发明中作些改变,省略和增加某些内容均是可以的。
Claims (14)
1、一种在封闭罩内进行空气调节用的空气循环环境控制系统,包括:
一冷凝器(46),由冷凝通道和冷却通道组成,所述的冷凝通道串接在一副换热器(40)的热通道导管(48)和第一透平(24)入口之间,所述的冷却通道串接在所述第一透平(24)的出口和所述第二透平(26)的入口之间;
一连接在所述冷凝器(46)的冷却通道出口和所述第一透平机(24)的入口之间的输送导管(56);
一连接于所述冷凝器(46)的冷却通道的入口与第一透平机(24)的出口之间的输送管道(50);其特征在于,还包括:
一连接于冷凝器(46)的冷却通道出口与第二透平机(26)的入口之间的输送导管(63)。
2、如权利要求1所述的系统,其特征在于,所述第一透平机(24)膨胀比这样确定,即使所述第一透平机(24)输出空气的温度在所述压缩环境空气的露点与所述冷凝器(46)的冰点之间。
3、如权利要求1所述的系统,其特征在于,还包括一由阀(58)和第一旁通导管(60)串接组成的旁路装置,所述阀(58)的入口和导管(60)的出口分别并接于所述的第一透平机(24)的输入导管(56)和第一透平机(24)的输出导管(50)之间。
4、如权利要求1所述的系统,其特征在于,还包括由一导管(74)和主旁通阀(72)所组成的第一直送装置,所述的导管(74)和主旁通阀(72)依次串接在一副换热器(40)输出空气导管(48)与第二透平机(26)的输入导管(63)之间。
5、如权利要求1所述的系统,其特征在于,还包括由依次串接的副旁通阀(76)和第二旁通导管(78)所组成的一第二直送装置,所述的副旁通阀(76)与主旁通阀(72)相连接,所述的第二旁能管(78)连接于副旁通阀(76)与混合器(64)之间。
6、一种空气循环控制系统包括:
一被压缩的环境内的带水蒸汽的空气源(9);
一接收和冷却所述压缩环境空气的主换热器(16);
一从所述主换热器(16)接收输出空气的压缩机(36);
一接收和冷却来自所述压缩机(36)的输出空气的副换热器(40),所述副热热器(40)的热导管(34)与压缩机(36)的出口相连接;
一接收和除去来自从所述副换热器(40)出来的输出空气的水蒸汽的冷凝器(46),所述冷凝器(46)的冷凝通道与所述的副换热器(40)的热导管出口连接;
所述第一透平机(24)接收和膨胀来自所述冷凝器(46)的输出空气;
导管(50),它连接于第一透平机(24)的出口和冷凝器(46)的冷却通道入口之间;其特征在于:
还包括一第二透平机(26),它通过一导管(63)使其入口与冷凝器(46)的冷却通道出口连通;所述的压缩机(36)通过一共同轴(23)由第一和第二透平(24、26)机共同驱动。
7、如权利要求6所述的系统,其特征在于,还包括:
安置在冷凝器(46)的冷凝通道的入口和出口处的流动传感器或压力传感器;以及
一阀(58)和导管(60),所述阀(58)的入口和导管(60)的出口分别并接于所述的第一透平机(24)的输入导管(56)和第一透平机(24)的输出导管(50)之间。
8、如权利要求6所述的系统,其特征在于,还包括一热线风速计(73),它设置在压缩环境空气(9)的进入导管(10)和其调节阀门(12)之间。
9、如权利要求8所述的系统,其特征在于,还包括一主旁通阀(72)和导管(74),它们依次地串接在副换热器(40)的热通道出口和冷凝器(46)的冷却通道出口的管道之间,并与所述第二透平机(26)的出口连接管道(63)连通。
10、如权利要求8所述的系统,其特征在于,还包括一副旁通阀(76)和第二旁通管(78);它们依次地串接在主旁通阀(72)的混合器(64)之间。
11、一种在一封闭罩内的空气调节方法包括的诸步骤为:
从被压缩的环境空气冷凝和除去水蒸汽;
在一第一透平机(24)中膨胀在所述冷凝步骤中除湿的空气;
在所述冷凝步骤中将在所述第一透平机(24)中膨胀的空气用作冷却剂;其特征在于,还包括:
在一第二透平机(26)中膨胀在所述冷凝步骤中被加热的所述冷却剂。
12、如权利要求11所述的方法,其特征在于,还包括评估所述压缩环境空气的质量流动速率的步骤。
13、如权利要求12所述的方法,其特征在于,还包括在所述压缩环境空气的质量流动速率降至低于一第一预选值时,将所述压缩环境空气直接送到所述第二透平机(26)入口的步骤。
14、如权利要求12所述的方法,其特征在于,还包括在所述压缩环境空气的质量流动速率降至低于一第二预选值时,将所述压缩环境空气直接送到所述第二透平机(26)出口的步骤。
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US07/570,100 | 1990-08-17 |
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- 1991-05-20 WO PCT/US1991/003529 patent/WO1992003338A1/en active IP Right Grant
- 1991-05-20 DE DE69104369T patent/DE69104369T2/de not_active Expired - Lifetime
- 1991-05-20 JP JP3515585A patent/JPH0796936B2/ja not_active Expired - Lifetime
- 1991-05-20 EP EP91916454A patent/EP0542909B1/en not_active Expired - Lifetime
- 1991-06-11 CA CA002044292A patent/CA2044292C/en not_active Expired - Lifetime
- 1991-06-24 CN CN91104413A patent/CN1025725C/zh not_active Expired - Lifetime
- 1991-08-02 IL IL9906191A patent/IL99061A/en not_active IP Right Cessation
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CN1898129B (zh) * | 2003-12-30 | 2012-11-07 | 空中客车德国运营有限责任公司 | 用于对飞机的内舱段进行温度调节的装置与方法 |
CN103010466A (zh) * | 2012-11-27 | 2013-04-03 | 北京航空航天大学 | 双级压缩空气循环制冷系统 |
Also Published As
Publication number | Publication date |
---|---|
EP0542909A1 (en) | 1993-05-26 |
NO924996D0 (no) | 1992-12-23 |
KR0163407B1 (ko) | 1998-12-01 |
JPH05509390A (ja) | 1993-12-22 |
IL99061A (en) | 1995-06-29 |
JPH0796936B2 (ja) | 1995-10-18 |
DE69104369D1 (de) | 1994-11-03 |
NO176266B (no) | 1994-11-28 |
DE69104369T2 (de) | 1995-05-18 |
WO1992003338A1 (en) | 1992-03-05 |
KR937001320A (ko) | 1993-06-11 |
IL99061A0 (en) | 1992-07-15 |
EP0542909B1 (en) | 1994-09-28 |
NO924996L (no) | 1992-12-23 |
US5086622A (en) | 1992-02-11 |
CA2044292A1 (en) | 1992-02-18 |
CN1060270A (zh) | 1992-04-15 |
CA2044292C (en) | 1994-10-25 |
NO176266C (no) | 1995-03-08 |
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C15 | Extension of patent right duration from 15 to 20 years for appl. with date before 31.12.1992 and still valid on 11.12.2001 (patent law change 1993) | ||
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