CN107036334B - 改进的热交换器 - Google Patents

改进的热交换器 Download PDF

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CN107036334B
CN107036334B CN201611014814.6A CN201611014814A CN107036334B CN 107036334 B CN107036334 B CN 107036334B CN 201611014814 A CN201611014814 A CN 201611014814A CN 107036334 B CN107036334 B CN 107036334B
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air
heat exchanger
recirculation
inches
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L.J.梅奥
B.R.希
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Hamilton Sundstrand Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
    • F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
    • F28F3/025—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being corrugated, plate-like elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B39/00—Evaporators; Condensers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D9/0031—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other
    • F28D9/0037—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other the conduits for the other heat-exchange medium also being formed by paired plates touching each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D9/0062—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by spaced plates with inserted elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D9/0062—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by spaced plates with inserted elements
    • F28D9/0068—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by spaced plates with inserted elements with means for changing flow direction of one heat exchange medium, e.g. using deflecting zones
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0688—Environmental Control Systems with means for recirculating cabin air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2215/00—Fins
    • F28F2215/04—Assemblies of fins having different features, e.g. with different fin densities
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2250/00—Arrangements for modifying the flow of the heat exchange media, e.g. flow guiding means; Particular flow patterns
    • F28F2250/10—Particular pattern of flow of the heat exchange media
    • F28F2250/106—Particular pattern of flow of the heat exchange media with cross flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract

提供一种用在飞机的环境控制系统中的再循环热交换器，所述再循环热交换器具有多个交替堆叠的第一流体层和第二流体层。矩形芯具有约4.750英寸(12.065 cm)的宽度和约10.6英寸(26.924 cm)的长度。第一空气集管与所述芯的第一表面相邻布置，并且第二空气集管与所述芯的第二相背对表面相邻布置。所述第一空气集管和所述第二空气集管形成第一流体的流动路径的一部分。第一流体集管与第三表面相邻布置，并且第二流体集管与所述芯的第四表面相邻布置。所述第一流体集管和所述第二流体集管形成第二流体的流动路径，所述流动路径具有多通道配置。

Description

改进的热交换器
技术领域
本发明的示例性实施方案大体上涉及飞机的环境控制系统，并且更具体地说，涉及这种环境控制系统得到再循环热交换器。
背景技术
飞机和其他交通工具的环境控制系统(ECS)用于为飞机机舱内的乘客和机组人员提供调节的气流。一种类型的环境控制系统通常通过从位于ECS设备舱附近的冲压空气入口接收新鲜空气来操作。新鲜冲压空气被供应到至少一个电动机驱动的空气压缩机，所述空气压缩机将空气压力升高到例如机舱的期望空气压力。从至少一个空气压缩机，空气被供应到任选的臭氧转换器。因为空气压缩机产生热，空气随后被供应到空调包，在所述空调包中空气在输送到机舱之前被冷却。
从机舱排出的空气(还被称为再循环空气)被提供给再循环热交换器，其中空气在与冷的新鲜空气混合之前被冷却并返回到机舱。随着飞机机舱的尺寸和机舱热负载增加，对ECS的需求也增加。常规ECS难以满足这种飞机的更大冷却要求。
发明内容
根据本发明的一个实施方案，提供用在飞机的环境控制系统中的再循环热交换器，所述再循环热交换器具有多个交替堆叠的第一流体层和第二流体层。矩形芯具有约4.750英寸(12.065 cm)的宽度和约10.6英寸(26.924 cm)的长度。第一空气集管与芯的第一表面相邻布置，并且第二空气集管与芯的第二相背对表面相邻布置。第一空气集管和第二空气集管形成第一流体的流动路径的一部分。第一流体集管与第三表面相邻布置，并且第二流体集管与芯的第四表面相邻布置。第一流体集管和第二流体集管形成第二流体的流动路径，所述流动路径具有多通道逆流配置。
附图说明
在本说明书的结论处的权利要求书中具体指出并明确要求保护被认为是本发明的主题。本发明的前述和其他特征以及优点从结合附图进行的以下详细描述中显而易见，在附图中：
图1是飞机的环境控制系统的示意图；
图2是根据本发明的实施方案的再循环热交换器的透视图；
图3是根据本发明的实施方案的图2的再循环热交换器的芯的透视图；
图4是根据本发明的实施方案的芯的第一流体层的实例的前视图；并且
图5是根据本发明的实施方案的芯的第二流体层的实例的前视图。
详细描述参考附图通过实例的方式来解释本发明的实施方案以及优点和特征。
具体实施方式
现参考图1，更详细地示出飞机的环境控制系统(ECS) 20的实例的示意图。ECS 20被配置来从飞机的外部接收空气作为新鲜的冲压空气并且从飞机机身或另一内部空间接收空气作为再循环空气。新鲜冲压空气被供应给包括多个常规部件的ECS包22，所述常规部件包括至少一个热交换器(未示出)。在ECS包22内，新鲜空气通过与冲压空气的热交换被调节，使得冷的加压空气被提供给下游混合器24并随后提供给飞机分配系统26。
在提供给ECS包22之前，冲压空气被配置来穿过液体冷却回路28的热交换器30。在热交换器30内，冲压空气被配置来吸收热，从而冷却蒸汽冷却回路28内的液体。液体冷却回路28另外包括再循环热交换器32。
多数再循环空气使用再循环风扇34从机舱传递回到ECS 20。再循环风扇34被配置来将再循环空气供应到再循环热交换器32以进行冷却之前通过过滤器36抽吸再循环空气。冷却的再循环空气离开再循环热交换器32并且随后在供应到飞机分配系统26之前与混合器24中的新鲜空气混合。
现在参考图2，更详细地示出再循环热交换器26的实例。再循环热交换器26为大体矩形形状。空气入口集管70、空气出口集管72、液体入口集管74以及液体出口集管76布置成与热交换器32的芯80流体连通，使得热被配置来在热交换器32内从再循环空气传递到液体。如图所示，空气入口集管70和空气出口集管72与相背对表面例如像芯80的前面和背面相邻设置。然而，在其他实施方案中，诸如在热交换器32内的空气流具有多通道配置的情况下，空气入口70和空气出口72可与芯80的同一表面相邻定位。类似地，图2中示出的液体入口74和液体出口76分别与芯80的相背对表面例如芯80的右侧面和左侧面相邻布置。然而，在其他实施方案中，诸如在穿过热交换器32的液体流动路径具有多通道配置的情况下，液体入口74和液体出口76可布置在芯80的同一侧面上。
图3-5中示出再循环热交换器32的芯80的构造的细节。更具体地，再循环热交换器32的芯80具有板翅构造，具有穿过其的第一温流体(空气)和第二冷流体的交叉流。在一个实施方案中，芯80具有约4.750英寸(12.065 cm)的宽度W和约10.6英寸(26.924 cm)的长度L。热交换器32的芯80包括多个第一流体层100和第二流体层200。第一流体层100具有流体通路，使得第一流体例如像温暖再循环空气在由箭头F1指示的第一方向上流过芯80。第二流体层200具有流体通路，使得第二流体例如液体冷却剂在由箭头F2指示的第二方向上流过芯80。在一个实施方案中，第二流体流的方向基本垂直于第一流体流的方向。第一流体层100和第二流体层200沿所述芯的高度H交替堆叠。薄板300将相邻流体层100、200分开。在一个实施方案中，薄板300具有约0.016英寸(0.0406 cm)的厚度。
参考图4-5，相应地示出第一流体层100和第二流体层200的实例。每个第一流体层100和第二流体层200分别具有多个波纹翅片102、202，所述波纹翅片102、202跨每个流体层形成流体通路。示例性第一流体层100的波纹翅片102从流体联接到空气入口70的相邻第一入口边104延伸到流体联接到空气出口72的第二出口边106。第一流体跨第一流体层100在入口边104与出口边106之间流动的距离为第一流体流动长度LF1。类似地，示例性第二流体层200的波纹翅片202从流体联接到液体入口集管74的第一入口边210延伸到流体连接到液体出口76的层200的第二出口边212。第二流体层200的翅片202可布置成限定每个层200内的多个通道。在示出的非限制性实施方案中，每个第二流体层200具有三通道逆流配置。第二流体穿过第二流体层200的流动路径的总距离为第二流体流动长度LF2。
第一流体层100和第二流体层200两者的翅片配置可能但不必在芯80的高度H上保持恒定。第一流体层100和第二流体层200的波纹翅片102、202的配置由翅片高度、翅片厚度以及每长度翅片的数量限定。第一流体层100的波纹翅片102具有约0.324英寸(0.8230 cm)的翅片高度、约0.003英寸(0.0076 cm)的翅片厚度以及约26.5翅片/英寸(10.43翅片/厘米)的翅片密度。第二流体层200的波纹翅片202具有约0.087英寸(0.2210 cm)的翅片高度、约0.004英寸(0.0106 cm)的翅片厚度以及约30翅片/英寸(11.81翅片/厘米)的翅片密度。除了入口边104和出口边106之外的层的其他边由封闭杆108、204、208覆盖以便防止替换路径中的流体流。在一个实施方案中，封闭杆108、204、208具有约0.150英寸(0.381 cm)的宽度或高度。
如图4所示，第一流体层100的翅片配置跨层的流动长度不均匀。在一个实施方案中，防护翅片120与每个第一流体层100的入口104和出口106相邻。防护翅片120可具有直的或波纹配置。第一流体层100的防护翅片120可具有约0.324英寸(0.86 cm)的翅片高度、约0.012英寸(0.0305 cm)的翅片厚度以及约每英寸9个翅片(每厘米3.54个翅片)的翅片密度。
在再循环热交换器内，使用液体冷却剂冷却来自飞机机舱的温暖再循环空气。此外，取决于ECS的冷却要求和空气分配架构，与常规ECS相比较，再循环热交换器32可布置在飞机内的不同位置处。在一个实施方案中，再循环热交换器32定位在分配舱内。在其他实施方案中，再循环热交换器32位于未加压设备舱内。通过重新定位再循环热交换器32，热交换器的尺寸可增加，导致更有效的热传递。
虽然仅结合有限数量的实施方案对本发明进行了详细描述，但应易于理解，本发明不限于此类公开的实施方案。相反，可对本发明进行修改，以并入以上未描述但与本发明精神和范围相称的任何数量的变化、改变、替代或等同布置。另外，虽然已描述了本发明的各种实施方案，但应理解，本发明的方面可仅包括所述实施方案中的一些。因此，不应认为本发明受限于前面的描述，而是仅受限于所附的权利要求书的范围。

Claims (8)

1.一种飞机的环境控制系统，其被配置来从飞机的外部接收空气作为新鲜的冲压空气并且从飞机机身或另一内部空间接收空气作为再循环空气，包括：
ECS包，其中，新鲜空气通过与ECS包内的冲压空气的热交换被调节，使得冷的加压空气被提供给下游混合器并随后提供给飞机分配系统；
液体冷却回路的热交换器，其中，在提供给ECS包之前，冲压空气被配置来穿过液体冷却回路的热交换器，并且其中，在液体冷却回路的热交换器内，冲压空气被配置来吸收热，从而冷却蒸汽冷却回路内的液体；
液体冷却回路的再循环热交换器；
再循环风扇，其中，所述再循环风扇被配置来将再循环空气供应到再循环热交换器以进行冷却之前通过过滤器抽吸再循环空气，并且其中，冷却的再循环空气离开再循环热交换器并且随后在供应到飞机分配系统之前与混合器中的新鲜空气混合；
所述再循环热交换器包括：
矩形芯，其具有多个交替堆叠的第一流体层和第二流体层，其中所述矩形芯具有4.750英寸的宽度W和10.6英寸的长度L；
第一空气集管，其与所述芯的第一表面相邻；
第二空气集管，其与所述芯的第二相背对表面相邻，
其中所述第一空气集管和所述第二空气集管形成第一流体的流动路径的一部分；
第一流体集管，其与所述芯的第三表面相邻；以及
第二流体集管，其与所述芯的第四表面相邻；
其中所述第一流体集管和所述第二流体集管形成第二流体的流动路径的一部分，并且所述第二流体的所述流动路径具有多通道逆流配置，
其中所述第一流体是来自机舱的再循环空气，以及所述第二流体是液体冷却剂；
其中所述再循环热交换器安装在所述飞机的分配舱内；
其中每个第一流体层和第二流体层包括多个波纹翅片，所述波纹翅片在入口边与出口边之间延伸以形成流体的流动路径；
所述再循环热交换器还包括与所述第一流体层的所述入口边和所述出口边相邻的多个防护翅片，其中所述防护翅片具有第一翅片配置并且所述多个波纹翅片具有第二不同翅片配置。
2.如权利要求1所述的环境控制系统，其中至少一个第一流体层包括多个波纹翅片，所述波纹翅片具有0.324英寸的翅片高度、0.003英寸的翅片厚度以及每英寸26.5个翅片的翅片密度。
3.如权利要求1所述的环境控制系统，其中至少一个第二流体层包括多个波纹翅片，所述波纹翅片具有0.087英寸的翅片高度、0.004英寸的翅片厚度以及每英寸30个翅片的翅片密度。
4.如权利要求1所述的环境控制系统，其中所述防护翅片具有0.324英寸的翅片高度、0.012英寸的翅片厚度以及每英寸9个翅片的翅片密度。
5.如权利要求4所述的环境控制系统，其中所述多个防护翅片是直的。
6.如权利要求1所述的环境控制系统，其中所述多个第一流体层和所述多个第二流体层通过具有0.016英寸的厚度的板彼此分开。
7.如权利要求1所述的环境控制系统，其中所述第二流体层具有三通道逆流配置。
8.如权利要求1所述的环境控制系统，其中所述多个第二流体层的所述流动路径垂直于所述多个第二流体层的所述流动路径。
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