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CN112793244A - 防火隔热件产品 - Google Patents

防火隔热件产品 Download PDF

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Publication number
CN112793244A
CN112793244A CN202011271630.4A CN202011271630A CN112793244A CN 112793244 A CN112793244 A CN 112793244A CN 202011271630 A CN202011271630 A CN 202011271630A CN 112793244 A CN112793244 A CN 112793244A
Authority
CN
China
Prior art keywords
fire
layer
insulation product
aes
product
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202011271630.4A
Other languages
English (en)
Inventor
帕布洛·巴斯克斯桑切斯
吉列尔莫·埃尔奈斯洛佩斯
费尔南多·伊涅斯塔洛扎诺
杰西·哈维尔·瓦兹奎兹卡斯特罗
阿尔贝托·阿拉纳伊达尔戈
豪尔赫·巴列斯特罗斯门德斯
亚松森·布特拉格尼奥-马丁尼兹
曼纽尔·肯普夫
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
Original Assignee
Airbus Operations SL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SL filed Critical Airbus Operations SL
Publication of CN112793244A publication Critical patent/CN112793244A/zh
Pending legal-status Critical Current

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  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
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Abstract

本发明涉及一种防火隔热件产品(1)、复合零件、飞行器的后端部、管道、电池壳体和直升机，所述防火隔热件产品包括以下各项的组合：‑碱土硅酸盐(AES)材料(2)，以及‑以下各项中的至少一项：液体屏障膜(5)、FRP(纤维增强塑料)层(4)、软木(3)，‑其中，所述液体屏障膜(5)和所述FRP层(4)被堆叠到所述AES材料(2)上，‑并且其中，所述软木(3)材料也被堆叠到所述AES材料(2)上或嵌入到所述AES材料(2)中，其中所述软木(3)被配置为多个条带，从而形成填充有所述AES材料(2)的网格结构。

Description

防火隔热件产品
技术领域
本发明涉及一种产品，该产品提供了进行保护以免受火灾事件的后果(特别是火焰穿透)的影响的结构及相关系统，并且该产品还提供了隔热能力。本发明特别适用于飞行器和直升机的不同部分。
背景技术
飞行器的许多部件都受到火灾事件的影响，并且为了确保飞行器的正常操作，结构及相关系统必须受到保护以免受火灾事件后果的影响。
为了这些目的，已经试验和设置了若干材料和解决方案以防止火灾事件的后果。根据应用，需要解决两个主要影响：火焰穿透和隔热。
需要解决火焰穿透问题，从而保持将火灾封闭在指定区域中。在另一方面，隔热能力可以允许范围广泛的材料用于具有较低解耦温度需求的结构性应用。
现有技术最广泛使用的解决方案是主要由陶瓷或硅胶层压件与铝片一起制成的隔热包层。这些隔热包层对火焰穿透和隔热是有效的解决方案，但也是昂贵且沉重的。
隔热包层由于其缺乏刚性而可能会出现一些结构性应用上的问题。因此，这些隔热包层会在制造或组装过程中垮塌，从而导致其有效性丧失。
现有技术的另一解决方案是基于通过形成多孔的材料焦层，防止火焰穿透并且提供隔热而对抗火灾事件的材料。该选项由于其性能而与许多应用都相关，但是由于在操作条带件下失去保护，受到振动的结构无法实施该解决方案。
在另一现有技术的解决方案中，添加或使用呈现出更高耐火/防火能力的钛、钢或铬镍铁合金等材料代替通常用于结构零件的常规材料，例如铝、复合材料(CFRP、GFRP等)，以克服火穿透问题。作为示例，在飞行器的APU中可以理解这一点，该APU可以被钛防火壁包围，以防止铝(作为结构性材料)受到损坏，从而在火灾事件中使火从尾锥中出来。
发明内容
本发明的目的是提供一种产品，该产品是防火的并且还具有良好的隔热能力，这样能够避免火源周围的结构处的高温不会损坏所述结构。
本发明提供了一种防火隔热件产品，该防火隔热件产品包括以下各项的材料组合：
-碱土硅酸盐(AES)材料，以及
-以下各项中的至少一项：液体屏障膜、FRP(纤维增强塑料)层、软木，
其中，液体屏障膜和FRP层被堆叠到AES材料上，并且其中，软木材料也被堆叠到AES材料上或嵌入所述AES材料中，并且在最后一种情况下，其中软木被嵌入到AES材料中，软木被配置为多个条带，从而形成填充有AES材料的网格结构。
本发明提供了以下优点：
--成本低于现有技术的解决方案。
-使用低密度材料，从而减轻了重量并且提供比现有技术更轻的解决方案。
-通过测试确保了防火和隔热能力。
-环境友好。
-集成在结构面板中从而降低了潜在的成本，同时避免在制造和/或组装过程中使隔绝材料垮塌的问题。
-由于热和结构要求的脱钩，因此能够在具有有限高温强度能力的火灾区指定区域中使用结构材料。
本发明的其他特性和优点将从下面与附图相关的对说明其目的的若干实施例的详细描述中变得清楚。
附图说明
图1示出了根据本发明的第一优选的实施例的防火隔热件产品的示意图。
图2示出了软木的热性能的示意图。
图3示出了根据本发明的第二优选的实施例的防火隔热件产品的示意图。
图4a至图4c示出了根据本发明的不同优选的实施例的防火隔热件产品的示意图。图4a示出了俯视图。图4b示出了根据本发明的第三优选的实施例的防火隔热件产品的截面视图。图4c示出了根据本发明的第四优选的实施例的防火隔热件产品的截面视图。
图5a示出了在其后端部上具有APU隔室的飞行器，其中至少一个防火壁包括本发明的防火隔热件产品。图5b示出了APU隔室的详细视图。
图6a和图6b分别示出了APU隔室的前防火壁。
图7a示出了电池及其壳体的分解视图。图7b示出了壳体的主要元件的透视图。
图8示出了包括本发明的防火隔热件产品的直升机的发动机台。
图9示出了具有包括本发明的防火隔热件产品的中央壁的直升机发动机隔室。
具体实施方式
重要的是考虑由比如以下航空法规所限定的“防火”概念：
-FAR/JAR 25.1191：防火壁—定义。
-FAR/JAR 25.865：飞行控制件、发动机安装件和其他飞行结构的防火保护。
图1示出了本发明的防火隔热件产品1的第一优选构型，该防火隔热件产品包括层的堆叠，所述层的堆叠包括软木层3和碱土硅酸盐材料(AES)层2，该碱土硅酸盐材料层在产品1的旨在面向火的一侧。AES层2主要充当防火屏障，并且在第二水平充当隔热件，而软木层3充当隔热件。
对于大多数可能的应用，AES层2和软木层3需要结合有针对侵蚀性流体的保护，主要针对AES 2。为此，将一对液体屏障膜5和一对FRP(纤维增强塑料)层4放置在产品1的两侧处。这对FRP 4层旨在粘合至AES和软木。
优选地，液体屏障膜5是PVF(聚氟乙烯)膜或类似的材料(PEEK、PDVF、PET…)。并且优选地，FRP层4是GFRP层。
图1所示的实施例是用于非结构保护的良好解决方案，可以将其作为附加组件放置在许多区域中的结构上，以保护该结构不受火灾和温度的影响。
除了通过软木材料本身的低导热性进行隔热之外，这种材料还呈现出针对此特定应用的以下重要特征。如图2所示，闭孔(微)结构充当阻挡热火气体的有效屏障，并且在严重的热冲击下该结构的降解在指向火/热源的表面上产生进一步的隔热焦层。热解气体被认为也提供了一定的隔绝作用。
图3示出了本发明的防火隔热件产品1的第二优选的构型，该防火隔热件产品包括层的堆叠，所述层的堆叠包括碱土硅酸盐材料(AES)层2、在层AES 2的两侧处的一对FRP(纤维增强塑料)层4、以及在FRP层4的两侧处的一对液体屏障膜5。在此第二优选的构型中，(一个或多个)AES层充当防火屏障和隔热解决方案。
类似于图1的实施例，此第二优选的构型是用于非结构保护的良好解决方案，可以将其作为附加组件放置在许多区域中的结构上，以保护该结构不受火灾和温度的影响。
图4a至图4c示出了防火隔热件产品1的另一优选的实施例。在此实施例中，产品1包括层的堆叠，所述层的堆叠包括由AES 2和软木3形成的层，软木3被配置为多个条带，这些条带形成填充有AES材料2的网格结构(格架)。图4a示意性地描绘了此产品。
引入此选项作为更坚固的保护，可以将该产品放置在结构上或包含在用作夹层面板芯部的结构层压件内部。另外，在这种情况下，软木充当刚性结构，该刚性结构防止隔热件材料在高压釜中的固化过程中由于施加的高压而垮塌。
图4b示出了第三优选的实施例，其中由填充有AES 2的软木格架3形成的层进一步包括沉积在由AES+软木构成的层上的附加AES层2、在AES+软木层和附加AES层2的两侧处的一对FRP(纤维增强塑料)层4、以及在FRP层4的两侧处的一对液体屏障膜5。在此第三优选的构型中，一个或多个AES层充当防火屏障和隔热解决方案。优选地，FRP层4是GFRP层。
图4c示出了第四优选的实施例，其中由填充有AES 2的软木格架3形成的层进一步包括在由AES+软木构成的层的两侧处的一对FRP(纤维增强塑料)层4，以及在FRP层4的两侧处的一对液体屏障膜5。在此第四优选的构型中，FRP层充当防火屏障和隔热解决方案。此第四实施例对于直接集成为复合结构的一部分是非常有前途的。优选地，FRP层4是CFRP层。
第一优选的实施例(图1)已经通过本生(bunsen)试验进行了测试。测试样本具有2mm的AES层2和8mm的软木层3，并且应用以下条件：
-直接火焰冲击15min。
-1100℃的校准火焰。
-不施加载荷或振动。
-防护覆盖两个层的GFRP和PVF免受流体的影响。
在所要求的1100℃火焰15分钟之后的结果是不仅没有火焰穿过，而且在试样的后部处测得的温度为220℃。
已经测试的第三优选的实施例(图4b)满足有关防火壁FAR/JAR25.1191和FAR/JAR25.865的FAR/JAR 25法规，即：
-直接火焰冲击15min。
-在距试样100mm的距离处的1100℃的经校准的火焰。
-经校准的热通量。
-试样处于50Hz的振动下(在5min之后减小至16.6Hz)。
-不施加载荷。
-防护覆盖填充芯部GFRP和PVF免受流体的影响。
在所要求的1100℃火焰15分钟之后的结果是不仅没有火焰穿过，而且在试样的后部处测得的温度为240℃，其中在紧固件热点上的峰值约为300℃。
根据另一方面，本发明还涉及一种复合零件(非结构零件)，该复合零件包括如在第一或第二优选实施例中所示的防火隔热件产品。在这些情况下，产品借助于紧固件，通过粘接或维可牢尼龙搭扣(Velcro)型连结附接至零件。在借助于紧固件进行附接的情况下，将优选地使用垫圈，并且安装垫圈，从而在零件与产品之间形成气室。
根据另一优选的实施例，复合零件(结构零件)包括如在第三或第四优选的实施例中所示的防火隔热件产品。在这些情况下，产品1粘结或共固化至零件。
以下是所提出的发明的潜在实施例的列表：
·飞行器后端部的防火壁：
-尺寸限制：防火和热保护
-修改：基于提出的解决方案(优选地第一或第二优选的实施例)，用新的保护替换当前的钛防火壁。
-优点：安全性提高、RC减少，在火灾的情况下，火焰和热量都不会影响飞行器后端部的结构，因此，在火灾事件后无需更换。
根据另一方面，本发明还涉及一种飞行器6的后端部，该后端部包括由包括防火隔热件产品1的至少一个防火壁8、9、10、11隔绝的APU隔室7。图5a示出了在该飞行器的后端部具有APU隔室7的飞行器6。图5b示出了APU隔室7和该APU隔室的大部分壁的详细视图：前防火壁8、侧向防火壁9、后防火壁10和上部防火壁11，其中这些壁中的至少一个壁包括防火隔热件产品1。
·飞行器后端部的前防火壁：
-尺寸限制：防火和热保护
-修改：基于提出的解决方案(优选地第三或第四优选的实施例)，以新的保护替换当前的钛防火壁和铝桁梁。
-优点：安全性提高、RC减少，在火灾的情况下，火焰和热量都不会影响防火壁的结构，因此，在火灾事件后无需更换。
根据另一方面，本发明还涉及包括防火隔热件产品1的前防火壁8。图6a和图6b示出了APU隔室的前防火壁8。图6b示出了可以用提出的发明替换的桁梁13。
·电池壳体：
-尺寸限制：热保护
-修改：基于提出的解决方案，用复合金属壳体替换当前的金属壳体，
-优点：安全性提高、RC减少、重量减轻。
根据另一方面，本发明还涉及包括防火隔热件产品1的电池壳体14。图7a示出了电池及其壳体的分解视图。图7b示出了壳体的主要元件的透视图。
·复合防火管道：
-尺寸限制：热保护
-修改：基于提出的解决方案、优选地第三选项，用复合管道替换当前的钛管道。
-优点：安全性提高、RC减少。
根据另一方面，本发明还涉及包括防火隔热件产品1的管道。
·直升机发动机台：
-尺寸限制：主结构、热保护
-修改：用具有集成的火和热保护的复合夹层替换当前的钛蒙皮和桁梁。
-优点：通过实现CFRP复合发动机台设计来减轻重量，发动机台与CFRP复合机架之间的热膨胀系数不匹配。
根据另一方面，本发明还涉及包括防火隔热件产品1的直升机发动机台15。图8示出了在通常由铝制成的机架16上的包括钛蒙皮、桁梁、夹子和角撑板的发动机台15。
·直升机发动机隔室中央防火壁：
-尺寸限制：加强面板、热保护
-修改：用具有集成的火和热保护的复合夹层替换当前的加强钛蒙皮。
-优点：减少维护和维修、为客户增加价值
根据另一方面，本发明还涉及具有包括中央防火壁17的发动机隔室的直升机，该中央防火壁包括防火隔热件产品1。图9示出了具有包括防火隔热件产品1的中央壁17的直升机发动机隔室。
尽管已经结合优选实施例充分描述了本发明，但是明显的是在本发明的范围内可以引入修改，而不将本发明的范围视为受这些实施例的限制，而是受到所附权利要求的内容的限制。

Claims (15)

1.-一种防火隔热件产品(1)，所述防火隔热件产品包括以下各项的组合：
-碱土硅酸盐(AES)材料(2)，以及
-以下各项中的至少一项：液体屏障膜(5)、FRP(纤维增强塑料)层(4)、软木(3)，
-其中，所述液体屏障膜(5)和所述FRP层(4)被堆叠到所述AES材料(2)上，
-并且其中，所述软木(3)材料也被堆叠到所述AES材料(2)上或嵌入到所述AES材料(2)中，其中所述软木(3)被配置为多个条带，从而形成填充有所述AES材料(2)的网格结构。
2.-根据权利要求1所述的防火隔热件产品(1)，其中，所述液体屏障膜(5)为热塑性膜、优选为PVF(聚氟乙烯)膜、PEEK膜、PDVF膜或PET膜。
3.-根据前述权利要求中任一项所述的防火隔热件产品(1)，其中，所述FRP层(4)为GFRP(玻璃纤维增强塑料)层或CFRP(碳纤维增强塑料)层。
4.-根据前述权利要求中任一项所述的防火隔热件产品(1)，进一步包括粘合剂层(6)，以将所述液体屏障膜(5)粘合至所述AES材料(2)。
5.-根据前述权利要求中任一项所述的防火隔热件产品(1)，所述防火隔热件产品包括层的堆叠，所述层的堆叠由第一软木层(3)、第二AES层(2)和至少一个FRP层(4)形成，所述至少一个FRP层在一侧包围由所述第一层(3)和所述第二层(2)形成的堆叠。
6.-根据权利要求1至4中任一项所述的防火隔热件产品(1)，所述防火隔热件产品包括层的堆叠，所述层的堆叠由嵌入到所述AES材料(2)中第一软木层(3)、以及在所述软木层和AES层顶部上的至少一个AES材料层(2)或FRP层(4)形成，以增强所述产品(1)的防火性。
7.-根据权利要求6所述的防火隔热件产品(1)，进一步包括至少在所述产品(1)的一侧处的液体屏障膜(5)和/或FRP(纤维增强塑料)层(4)。
8.-一种复合零件，所述复合零件包括根据权利要求1至5中任一项所述的防火隔热件产品(1)，其中，所述产品(1)借助于紧固件附接至所述零件，并且优选地通过垫圈安装、通过粘接或通过维可牢尼龙搭扣(Velcro)型连结，从而在所述零件与所述产品(1)之间形成气室。
9.-一种复合零件，所述复合零件包括根据权利要求6至7中任一项所述的防火隔热件产品(1)，其中，所述产品(1)粘结或共固化至所述零件。
10.-一种飞行器(6)的后端部，所述后端部包括由至少一个防火壁(8，9，10，11)隔绝的APU隔室(7)，所述至少一个防火壁包括根据权利要求1至7中任一项所述的防火隔热件产品(1)。
11.-一种飞行器(6)的后端部，所述后端部包括具有至少一个前防火壁(8)的APU隔室(7)，所述至少一个前防火壁包括根据权利要求6至7中任一项所述的防火隔热件产品(1)。
12.-一种管道，所述管道包括根据权利要求6至7中任一项所述的防火隔热件产品(1)。
13.-一种电池壳体(14)，所述电池壳体包括根据权利要求1至7中任一项所述的防火隔热件产品(1)。
14.-一种直升机，所述直升机具有发动机台(15)，所述发动机台包括根据权利要求1至7中任一项所述的防火隔热件产品(1)。
15.-一种直升机，所述直升机具有包括中央防火壁(17)的发动机隔室，所述中央防火壁包括根据权利要求1至7中任一项所述的防火隔热件产品(1)。
CN202011271630.4A 2019-11-14 2020-11-13 防火隔热件产品 Pending CN112793244A (zh)

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