CN102310945B - 用于飞行器的流体/流体热交换器的预热装置 - Google Patents
用于飞行器的流体/流体热交换器的预热装置 Download PDFInfo
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- 230000000903 blocking effect Effects 0.000 claims abstract description 5
- 238000002844 melting Methods 0.000 claims abstract description 5
- 230000008018 melting Effects 0.000 claims abstract description 5
- 238000010257 thawing Methods 0.000 claims 1
- 239000004215 Carbon black (E152) Substances 0.000 description 37
- 239000000446 fuel Substances 0.000 description 37
- 229930195733 hydrocarbon Natural products 0.000 description 37
- 150000002430 hydrocarbons Chemical class 0.000 description 37
- 239000013078 crystal Substances 0.000 description 13
- 238000001816 cooling Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 208000036828 Device occlusion Diseases 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- 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
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
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- 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
- 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
- F28D7/16—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 the conduits being arranged in parallel spaced relation
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- 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
- 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
- F28D7/16—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 the conduits being arranged in parallel spaced relation
- F28D7/1615—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 the conduits being arranged in parallel spaced relation the conduits being inside a casing and extending at an angle to the longitudinal axis of the casing; the conduits crossing the conduit for the other heat exchange medium
- F28D7/1623—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 the conduits being arranged in parallel spaced relation the conduits being inside a casing and extending at an angle to the longitudinal axis of the casing; the conduits crossing the conduit for the other heat exchange medium with particular pattern of flow of the heat exchange media, e.g. change of flow direction
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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
- F28F19/00—Preventing the formation of deposits or corrosion, e.g. by using filters or scrapers
- F28F19/006—Preventing deposits of ice
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- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
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- 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
- 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
- F28D2021/008—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for vehicles
- F28D2021/0089—Oil coolers
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
本发明的目的是提供一种飞行器,该飞行器包括一个在第一流体和有待冷却的第二流体之间的热交换器,第一流体在所述热交换器的窄导管(22)中流动,并且可以包括一些适合于融化的固体成分,其特征在于,飞行器在热交换器的导管(22)的上游包括第一流体的预热装置,该预热装置包括多个导管,这些导管设置在至少一个与第一流体流动方向相割的平面中,相邻两个导管之间的间隙适合于挡住大尺寸的固体成分,这些固体成分只有在至少部分融化时才能通过。
Description
技术领域
本发明涉及用于流体热交换器/飞行器流体,特别是用于飞行器发动机的碳氢燃料/油的交换器的预热装置。
背景技术
飞行器包括一个机舱和至少一个推进系统。根据一种广泛使用的实施方式,推进系统通过机翼支柱悬挂在机翼下。更一般地,该推进系统通过机翼支柱与机舱连接。
推进系统包括一个带有电机冷却回路的涡轮机,载热流体(或冷却流体)特别是油在该回路中流动。
利用碳氢燃料回路为涡轮机供应碳氢燃料,该碳氢燃料回路从一个设置在机舱处的油箱开始延伸。
在某些情况下,可以用多个冷却源来冷却涡轮机的油,特别是通过在电机冷却回路处的碳氢燃料/油热交换器,并且用碳氢燃料作为载热流体,以便冷却涡流机的油。
这种布置主要在法国专利申请FR-2936224中做过描述,该申请提出的方法是用碳氢燃料作为机舱和推进系统之间的载热流体。
根据图1所示的实施方式,热交换器包括油在其内流通的至少一个腔室10以及碳氢燃料在其内的流动的多根导管12,这些导管穿过所述腔室10。在这种情况下,导管12的内表面与碳氢燃料接触,而所述导管的外表面与油接触。这些导管基本是直的,并且有恒定的直径D。
该热交换器在上游还包括一根碳氢燃料供应导管14,该导管可以与未示出的总管连接。
通过一块包括多个孔18的板16将腔室10与该导管分开,孔的截面为D,保持恒定,每一个孔与导管12配合。
在某些飞行情况下,会在碳氢燃料中出现一些冰晶状的固体成分,这种固体成分的尺寸会很大,这种尺寸阻止它们通过孔18进入到导管12中。这样,朝向碳氢燃料供应导管14的板16的表面就可能成为会堆积冰晶的区域,从而就有可能限制碳氢燃料流向机动化系统(motorisation)的流量。
文献FR-2318314提出用第二热交换器来对碳氢燃料进行预热,以便限制冰晶堆积在第一热交换器中。但是,冰晶堆积的风险转向了第二热交换器处。
发明内容
因此,本发明旨在克服现有技术的这些缺陷,提出一种用于碳氢燃料/油热交换器的装置,这种装置可以限制碳氢燃料流动的导管堵塞的风险。
为此,本发明的目的在于一种飞行器,该飞行器包括一个在第一流体和有待冷却的第二流体之间的热交换器,第一流体在所述热交换器的狭窄导管中流动,并且可以包括一些适合于融化的固体成分,其特征在于飞行器在热交换器的导管的上游包括第一流体的预热装置,该预热装置包括多个导管,这些导管设置在至少一个与第一流体流动方向相割的平面中,相邻两个导管之间的间隙适合于挡住大尺寸的固体成分,这些固体成分只有在至少部分融化时才让通过。
附图说明
通过阅读下面仅作为例子的说明并结合附图将会更清楚地理解本发明的其他特征和优点,其中:
图1是说明现有技术的碳氢燃料/油热交换器的示意图;
图2是沿图1的热交换器的线II-II作的剖视图;
图3是说明在本发明热交换器入口处的碳氢燃料的预热装置的示意图;
图4是说明用于本发明热交换器的碳氢燃料的导管入口截面的剖视图;和
图5-7是本发明碳氢燃料的预热装置的不同步骤的示意图。
具体实施方式
图3中仅仅是示意性地示出了两种流体之间特别是碳氢燃料和油之间的热交换器的一部分。该热交换器包括一个油在其内流动的腔室20,油流动穿过导管22,而碳氢燃料在这些导管中流动。为促进热交换,热交换器包括多根狭窄的导管。
根据一个实施方式,导管是直径为D的圆形截面。
该热交换器尤其是用于飞行器的机动化,碳氢燃料供飞行器的机动化系统使用,油用于冷却。但是,并不限于油和碳氢燃料,可以适合于两种流体,其中一种流体在热交换器的可以含有固体成分的窄导管中流动,这种固体成分能够像冰晶一样融化。
油的入口和出口以及碳氢燃料的出口不再详细描述,因为它们是本领域技术人员公知的,它们可以是与现有技术的热交换器的相同。
该热交换器在上游包括被分开成多根导管22的至少一根碳氢燃料供应导管24。根据一个实施方式,该热交换器包括一块将供应导管24和用于油的腔室20分开的板26,所述板包括多个孔,每一个孔与一根导管22配合。板26和导管22之间的连接不再描述,因为这种连接可以用与现有技术的热交换器相同的方法实现。
根据本发明,碳氢燃料回路在导管22的上游包括一个预热装置,以便限存在制碳氢燃料中能够融化的大尺寸固体成分,这种固体成分很可能堆积在热交换器的导管22的入口或导管内。
例如,处在碳氢燃料中的能够融化的固体成分可以是冰晶。但是,本发明不限于这种能够融化的固体成分。
最好将预热装置设置在热交换器的供应导管24处。
根据本发明,预热装置包括至少一个预热回路,温度可以使冰晶融化的所述载热流体在该回路中流动,所述回路包括至少一个将需要再加热的碳氢燃料和所述载热流体分开的壁。
根据本发明,预热回路在供应导管24中包括多个彼此间隔开的导管28,载热流体在这些导管中流动。这些导管28可以有不同的截面形状。因此,它们可以是圆形的,或者可以很薄。
载热流体最好是用于通过热交换器的油。这样,在热交换器中用碳氢燃料再冷却的热油用于对热交换器上游的碳氢燃料进行预热。导管28最好是直的。最好将导管28设置在一个与碳氢燃料在所述供应导管24中流动的方向相割的平面中。根据这种情况,可以将这些导管设置在同一平面中或多个平面中。
使每相邻两个导管之间的间隙适于留住大尺寸的冰晶,只有在这些冰晶至少部分融化时才让它们通过,以限制这些冰晶有害地堆积在导管22的上游或堆积在这些导管中的风险。从而不影响飞行器的机动化系统的运行。
预热回路最好包括至少两组导管28,第一组30.1的各导管之间的距离为D1,第二组30.2的各导管之间的距离为D2,第三组30.3的各导管之间的距离为D3,以此类推。
同一组的各导管之间是平行的,将这些导管设置在至少一个与碳氢燃料在所述供应导管24中流动的方向基本上相割的平面中。可以将同一组的导管设置在与碳氢燃料在所述供应导管24中流动的方向相割的同一平面中或多个平面中。
根据本发明的另一特征,各导管之间的间隙沿碳氢燃料的流动方向从一组到另一组是减小的。这样,D1大于D2,D2自身大于D3,以此类推。由此,每一组构成一个适合于挡住冰晶的筛子,挡住的冰晶的大小随着它们接近热交换器的导管22而减小。
就是在用于预热碳氢燃料的各组导管28处,这种布置可以限制堵塞的风险。
直径D1最好小于或约等于3D,更好的是大于或等于2D,直径D2最好小于或约等于2D,更好的是大于或等于1.3D,直径D3最好小于或约等于1.3D,更好的是大于或等于D。
根据一个实施方式,用储槽32供应第一组30.1的各导管28,该储槽将油分配到第一组的所有导管28中。然后,利用收集器/分配器34将第一组30.1的导管28与第二组30.2的导管相连,利用收集器/分配器36将第二组30.2的导管28与第三组的导管28相连。最后,最后一组的导管,在此情况下是第三组30.3的导管通到一个收集器38中,该收集器与热交换器中的油的入口相连。
根据本发明的另一方面,热交换器的导管22的端部或板26的孔为圆锥形,它们朝向供应导管24的方向扩大。
根据一个实施方式,导管或孔的最大截面的直径约为1.5D。
根据本发明的另一方面,相邻两个导管的孔距小于或等于2.5D,也就是相邻两个导管的两个最大截面之间的间隙小于或等于D。
在热交换器的导管或热交换器的板26的端部处的这些布置有助于限制冰晶堆积的风险。
Claims (8)
1.一种飞行器,该飞行器包括一个在第一流体和有待冷却的第二流体之间的热交换器,第一流体在所述热交换器的窄导管(22)中流动,并且含有一些适合于融化的固体成分,其特征在于,所述飞行器在热交换器的窄导管(22)的上游包括第一流体的预热装置,该预热装置包括多个导管(28),所述预热装置的多个导管(28)设置在至少一个与第一流体流动方向相割的平面中,所述预热装置的相邻两个导管之间的间隙适合于挡住大尺寸的固体成分,这些大尺寸的固体成分只有在至少部分融化时才能通过。
2.根据权利要求1所述的飞行器,其特征在于,所述预热装置设置在热交换器的第一流体供应导管(24)处。
3.根据权利要求1或2所述的飞行器,其特征在于,所述预热装置的载热流体是热交换器的有待冷却的第二流体。
4.根据权利要求1或2所述的飞行器,其特征在于,所述预热装置包括至少一个预热回路,所述预热回路包括至少两组导管(28),所述预热回路的各导管(28)之间的间隙沿第一流体的流动方向从一组到另一组是减小的。
5.根据权利要求4所述的飞行器,其特征在于,所述预热回路包括第一组(30.1)的导管(28),所述第一组(30.1)的各导管之间的距离(D1)小于或等于热交换器的窄导管(22)直径的3倍,并且包括第二组(30.2)的导管(28),所述第二组(30.2)的各导管之间的距离(D2)小于或等于热交换器的窄导管(22)直径的2倍。
6.根据权利要求5所述的飞行器,其特征在于,所述预热回路包括第三组(30.3)的导管(28),所述第三组(30.3)的各导管之间的距离(D3)小于或等于热交换器的窄导管(22)直径的1.3倍。
7.根据权利要求1或2所述的飞行器,所述热交换器具有一块将容纳有第二流体的外壳(10)和第一流体供应导管(24)分开的板(26),所述板包括多个孔,每一个孔与热交换器的一根窄导管(22)配合,其特征在于,所述热交换器的窄导管(22)的端部或板(26)的孔沿第一流体的流动反方向扩大。
8.根据权利要求7所述的飞行器,其特征在于,所述热交换器的窄导管(22)的端部的最大截面的直径或板(26)的孔的最大截面的直径等于所述热交换器的窄导管(22)直径的1.5倍。
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Application Number | Priority Date | Filing Date | Title |
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FR1054392 | 2010-06-04 | ||
FR1054392A FR2960955A1 (fr) | 2010-06-04 | 2010-06-04 | Dispositif de prechauffage pour un echangeur thermique fluide/fluide d'un aeronef |
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CN102310945A CN102310945A (zh) | 2012-01-11 |
CN102310945B true CN102310945B (zh) | 2016-02-10 |
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US (1) | US9016351B2 (zh) |
EP (1) | EP2392798B1 (zh) |
CN (1) | CN102310945B (zh) |
BR (1) | BRPI1103150A2 (zh) |
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US9745069B2 (en) * | 2013-01-21 | 2017-08-29 | Hamilton Sundstrand Corporation | Air-liquid heat exchanger assembly having a bypass valve |
US20160376986A1 (en) * | 2015-06-25 | 2016-12-29 | Hrst, Inc. | Dual Purpose Heat Transfer Surface Device |
US10295279B2 (en) * | 2015-11-20 | 2019-05-21 | Hamilton Sundstrand Corporation | Heat exchanger |
US10703500B2 (en) | 2018-07-10 | 2020-07-07 | Hamilton Sundstrand Corporation | Heated pipe for liquid flows |
CN112963861B (zh) * | 2021-03-11 | 2022-08-30 | 哈尔滨工业大学 | 一种换热面积可分配式双燃料预冷器 |
Citations (5)
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US2006649A (en) * | 1930-12-15 | 1935-07-02 | Modine Mfg Co | Radiator core |
US4041697A (en) * | 1975-07-17 | 1977-08-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Oil cooling system for a gas turbine engine |
JPS5553694A (en) * | 1978-10-16 | 1980-04-19 | Hitachi Ltd | Heat exchanger |
EP1061243A2 (en) * | 1999-06-16 | 2000-12-20 | ROLLS-ROYCE plc | An apparatus for and a method of filtering a fluid |
CN101595360A (zh) * | 2007-07-11 | 2009-12-02 | 株式会社电装 | 热交换器 |
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US2055549A (en) * | 1934-05-18 | 1936-09-29 | Modine Mfg Co | Heat exchange device |
US3307623A (en) * | 1965-08-18 | 1967-03-07 | Schwarza Chemiefaser | Device for rapid melting of solid materials |
US4020632A (en) * | 1975-07-17 | 1977-05-03 | The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp | Oil cooling system for a gas turbine engine |
US4151710A (en) * | 1977-03-11 | 1979-05-01 | United Technologies Corporation | Lubrication cooling system for aircraft engine accessory |
US4462547A (en) * | 1977-10-21 | 1984-07-31 | Baltimore Paint & Chemical Co., A Division Of Dutch Boy, Inc. | Method of applying marking lines to a road surface |
US4773212A (en) * | 1981-04-01 | 1988-09-27 | United Technologies Corporation | Balancing the heat flow between components associated with a gas turbine engine |
CA2044825C (en) * | 1991-06-18 | 2004-05-18 | Marc A. Paradis | Full-range, high efficiency liquid chiller |
US20020162651A1 (en) * | 1999-01-20 | 2002-11-07 | Hino Motors, Ltd. | EGR cooler |
DE112008001782T5 (de) * | 2007-07-11 | 2010-08-05 | DENSO CORPORATION, Kariya-shi | Wärmetauscher |
FR2936224B1 (fr) | 2008-09-25 | 2012-07-13 | Airbus France | Systeme de gestion des flux thermiques d'un aeronef. |
-
2010
- 2010-06-04 FR FR1054392A patent/FR2960955A1/fr not_active Withdrawn
-
2011
- 2011-05-30 CN CN201110156846.0A patent/CN102310945B/zh not_active Expired - Fee Related
- 2011-05-31 EP EP20110305664 patent/EP2392798B1/fr active Active
- 2011-06-01 US US13/150,439 patent/US9016351B2/en active Active
- 2011-06-02 BR BRPI1103150 patent/BRPI1103150A2/pt not_active IP Right Cessation
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2006649A (en) * | 1930-12-15 | 1935-07-02 | Modine Mfg Co | Radiator core |
US4041697A (en) * | 1975-07-17 | 1977-08-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Oil cooling system for a gas turbine engine |
JPS5553694A (en) * | 1978-10-16 | 1980-04-19 | Hitachi Ltd | Heat exchanger |
EP1061243A2 (en) * | 1999-06-16 | 2000-12-20 | ROLLS-ROYCE plc | An apparatus for and a method of filtering a fluid |
CN101595360A (zh) * | 2007-07-11 | 2009-12-02 | 株式会社电装 | 热交换器 |
Also Published As
Publication number | Publication date |
---|---|
BRPI1103150A2 (pt) | 2012-11-20 |
CN102310945A (zh) | 2012-01-11 |
EP2392798A1 (fr) | 2011-12-07 |
US9016351B2 (en) | 2015-04-28 |
FR2960955A1 (fr) | 2011-12-09 |
US20110297352A1 (en) | 2011-12-08 |
EP2392798B1 (fr) | 2013-04-10 |
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