CN112793762A - 防火隔热产品、复合零件、飞行器后端部、管道及直升机 - Google Patents

防火隔热产品、复合零件、飞行器后端部、管道及直升机 Download PDF

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CN112793762A
CN112793762A CN202011268879.XA CN202011268879A CN112793762A CN 112793762 A CN112793762 A CN 112793762A CN 202011268879 A CN202011268879 A CN 202011268879A CN 112793762 A CN112793762 A CN 112793762A
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fire
product
insulation product
fire protection
film
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雅维耶·格雷罗梅尔廷
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·巴列斯特罗门德斯
亚松森·布特拉格尼奥-马丁尼兹
曼纽尔·肯普夫
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Airbus Operations SL
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Abstract

本发明涉及一种防火隔热产品(1)、复合零件、飞行器后端部、管道及直升机，所述防火隔热产品包括填充有碱土硅酸盐(AES)材料(2)的蜂窝芯体(3)。所述蜂窝芯体(3)的材料可以是金属或聚合物。所述产品(1)可以进一步包括FRP层(4)和/或液体阻挡薄膜(5)，所述液体阻挡薄膜优选地是热塑性材料。粘合剂层(6)可以进一步沉积在填充有AES(2)的所述蜂窝芯体(3)的层与所述FRP(4)的层之间。

Description

防火隔热产品、复合零件、飞行器后端部、管道及直升机
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产品，该防火隔热产品包括填充有碱土硅酸盐(AES)材料的蜂窝芯体。
该产品作为防火隔热装置，可以用于结构性和非结构性应用。
本发明提供了以下优点：
-比现有技术解决方案成本更低。
-经填充的蜂窝芯体使用低密度材料，重量减轻，比现有技术解决方案更轻。
-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3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示意图。
图4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示意图。
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7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8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
本发明包括一种防火隔热产品，该防火隔热产品避免了火源周围的结构性部件达到可能导致其退化的高温。该产品可以用于结构性和非结构性应用。
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。
根据本发明，该产品包括填充有碱土硅酸盐(AES)材料的蜂窝芯体。蜂窝芯体的材料可以是金属或聚合物。
图1示出了本发明的防火隔热产品1的第一优选实施例，该防火隔热产品包括层的堆叠，所述层的堆叠包括由一对FRP 4层包围的填充有AES 2的蜂窝芯体3。优选地，FRP 4层是GFRP(玻璃纤维增强塑料)层。
图2示出了防火隔热产品1的第二优选实施例，该防火隔热产品附加地包括粘合剂层6，该粘合剂层沉积在填充有AES 2的蜂窝芯体3与FRP层4之间。
该产品可以用于结构性和非结构性应用。
图3示出了可以用于结构性应用的防火隔热产品1的第三优选实施例，该防火隔热产品包括层的堆叠，所述层的堆叠包括由FRP层4包围(在底部处有至少一个FRP层4，而在产品1的顶部上有若干层)的填充有AES 2的蜂窝芯体3。
在需要的情况下，通过用液体阻挡薄膜5覆盖经填充的芯3，可以保护经填充的蜂窝芯体3免受侵蚀性流体的影响。这种阻挡件可以优选地是热塑性薄膜，比如PVF(聚氟乙烯)薄膜、PEEK薄膜、PDVF薄膜、或PET薄膜。图4示出了这种情况的实施例，优选地用于非结构性应用。
由于本发明的产品比具有隔热包层的现有技术解决方案更加刚性，因此它克服了它们在复合零件中的结构性集成的限制。例如，绝缘体材料在高压釜中固化期间由于施加的高压而垮塌。
由用AES填充的蜂窝芯体构成的新的解决方案已经经过试验，符合关于防火壁的FAR/JAR 25规定，即FAR/JAR25.1191&FAR/JAR25.865：
-直接火焰冲击15分钟。
-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5分钟之后减小至16.6Hz)。
-不施加载荷。
-保护覆盖经填充的芯的GFRP和PVF免受流体的影响。
根据另一个方面，本发明还涉及一种包括本发明的防火隔热产品的复合零件。
产品可以藉由紧固件附接至零件，并且优选地通过安装的垫圈在零件与产品之间形成空气腔室。替代性地，产品藉由粘合剂薄膜、糊状粘合剂、或点击粘结而被粘结至零件。并且替代性地，产品藉由共固化、共粘结、或二次粘结而被集成到零件中。
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：根据所提出的解决方案，用新的保护措施替换当前的钛防火壁。蜂窝芯体可以弯曲，以适配拐角和弯曲面板。
-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及其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：根据所提出的解决方案，用新的保护措施替换当前的钛防火壁和铝桁条。
-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。·复合防火管道：
-尺寸限制：热保护
-修改：根据所提出的解决方案，用复合材料导管替换当前的钛、钢、或铬镍铁合金导管。
-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复合发动机舱设计来减轻重量，发动机舱与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的直升机发动机舱15。图7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舱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8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 (13)

1.-一种防火隔热产品(1)，所述防火隔热产品包括填充有碱土硅酸盐(AES)材料(2)的蜂窝芯体(3)。
2.-根据权利要求1所述的防火隔热产品(1)，进一步包括FRP层(4)，所述FRP层堆积在填充有AES材料(2)的所述蜂窝芯体(3)上，所述FRP层(4)优选地是GFRP(玻璃纤维增强塑料)层。
3.-根据权利要求2所述的防火隔热产品(1)，进一步包括粘合剂层(6)，所述粘合剂层沉积在填充有AES(2)的所述蜂窝芯体(3)与所述FRP层(4)之间。
4.-根据权利要求1所述的防火隔热产品(1)，进一步包括液体阻挡薄膜(5)，所述液体阻挡薄膜优选地是热塑性薄膜，比如PVF(聚氟乙烯)薄膜、PEEK薄膜、PDVF薄膜、或PET薄膜。
5.-根据权利要求2或3和权利要求4所述的防火隔热产品(1)，其中，所述液体阻挡薄膜(5)沉积在所述FRP层(4)上、接触所述FRP层(4)以保护所述产品(1)免受流体的影响。
6.-一种复合零件，所述复合零件包括根据前述权利要求中任一项所述的防火隔热产品(1)，其中，所述产品(1)藉由紧固件附接至所述零件，并且优选地通过安装的垫圈在所述零件与所述产品(1)之间形成空气腔室。
7.-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产品(1)，其中，所述产品(1)藉由粘合剂薄膜、糊状粘合剂、或点击粘结而被粘结至所述零件。
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产品(1)，其中，所述产品(1)藉由共固化、共粘结、或二次粘结而被集成到所述零件中。
9.-一种飞行器(6)的后端部，所述飞行器的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5中任一项所述的防火隔热产品(1)。
10.-一种飞行器(6)的后端部，所述飞行器的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1至5中任一项所述的防火隔热产品(1)。
11.-一种管道，所述管道包括根据权利要求1至5中任一项所述的防火隔热产品(1)。
12.-一种直升机，所述直升机具有包括根据权利要求1至5中任一项所述的防火隔热产品(1)的发动机台(15)。
13.-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5中任一项所述的防火隔热产品(1)。
CN202011268879.XA 2019-11-14 2020-11-13 防火隔热产品、复合零件、飞行器后端部、管道及直升机 Pending CN112793762A (zh)

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