CN110683060A - 吸声面板及其生产方法、插入件、飞行器及其发动机短舱 - Google Patents

吸声面板及其生产方法、插入件、飞行器及其发动机短舱 Download PDF

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CN110683060A
CN110683060A CN201910586899.2A CN201910586899A CN110683060A CN 110683060 A CN110683060 A CN 110683060A CN 201910586899 A CN201910586899 A CN 201910586899A CN 110683060 A CN110683060 A CN 110683060A
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composite structure
insert
during
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hole
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T·里科贝内
H·梅纳
J·拉兰纳
A·波特
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Airbus Operations SAS
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Abstract

一种吸声面板的生产方法，包括：生产步骤，在该步骤期间生产复合结构；提供步骤，在该步骤期间提供插入件，每个插入件包括喷口和盖帽，喷口是具有通孔的中空圆柱体的形式，盖帽包括圆柱体形式的底座和圆锥体形式的覆盖件，底座容纳在孔中；定位步骤，在该步骤期间，插入件通过覆盖件穿入复合结构中而定位在复合结构中，使得孔在复合结构的一侧和另一侧开口；聚合步骤，在该步骤期间，具有插入件的复合结构被聚合；移除步骤，在该步骤期间，移除盖帽；第一组装步骤，在该步骤期间，蜂巢结构固定至聚合复合结构；第二组装步骤，在该步骤期间，后蒙皮固定至蜂巢结构。此方法能够获得具有非常小的直径的孔的吸声面板，确保低频声波的更好衰减。

Description

吸声面板及其生产方法、插入件、飞行器及其发动机短舱
技术领域
本发明涉及一种包括插入件的吸声面板的生产方法、一种使用这种生产方法获得的吸声面板、一种包括这种吸声面板的飞行器短舱、以及一种包括至少一个这种短舱的飞行器。
背景技术
飞行器推进系统包括发动机(尤其是涡轮喷气发动机)以及围绕发动机的短舱。为了吸收发动机所产生的噪声，短舱包括吸声面板。每个吸声面板包括复合结构，蜂巢形式的结构和后蒙皮相继固定至该复合结构。
复合结构朝向穿过短舱的气流定向，并且钻有孔以允许声波通向蜂巢结构。
尽管这种吸声面板完全令人满意，但新一代发动机产生较低频率的噪声。为了吸收这些频率，必需减小孔的直径。通过工具对已聚合的复合结构钻孔仅限于直径为1mm的孔，并且钻孔可能进一步使得复合结构的复合纤维的切断。
为了改善对这些新频率的吸收，期望找到这样的方法，该方法使得能够以新构架生产尤其具有非常小直径的孔的吸声面板。
发明内容
本发明的目的是提供一种吸声面板的生产方法，该吸声面板使得能够吸收具有低频率的声波。
为此，提出了一种吸声面板的生产方法，所述生产方法包括：
-生产步骤，在所述生产步骤期间生产复合结构，
-提供步骤，在所述提供步骤期间提供插入件，并且其中，每个插入件包括喷口和盖帽，所述喷口是具有通孔的中空圆柱体的形式，所述盖帽包括圆柱体形式的底座和圆锥体形式的覆盖件，并且其中，所述底座容纳在所述孔中，
-定位步骤，在所述定位步骤期间，所述插入件通过所述覆盖件穿入所述复合结构中而定位在所述复合结构中，使得所述孔在所述复合结构的一侧和另一侧开口，
-聚合步骤，在所述聚合步骤期间，具有所述插入件的所述复合结构被聚合，
-移除步骤，在所述移除步骤期间，移除所述盖帽，
-第一组装步骤，在所述第一组装步骤期间，蜂巢结构固定至所述聚合复合结构，以及
-第二组装步骤，在所述第二组装步骤期间，后蒙皮固定至所述蜂巢结构。
这种生产方法使得能够获得具有非常小的、尤其是小于1mm的直径的孔的吸声面板，该吸声面板确保了低频声波的更好衰减。
有利地，在所述提供步骤之前是包覆成型步骤，在所述包覆成型步骤期间，所述喷口包覆成型在所述底座上。
本发明还提出了一种插入件，所述插入件用于实施根据上述变型之一所述的生产方法、并且包括：喷口和盖帽，所述喷口是具有通孔的中空圆柱体的形式，所述盖帽包括圆柱体形式的底座和圆锥体形式的覆盖件，并且其中，所述底座容纳在所述孔中。
本发明还提出了一种使用根据前述实施例之一所述的生产方法获得的吸声面板。
本发明还提出了一种用于发动机的短舱，所述短舱包括根据前一变体所述的至少一个吸声面板。
本发明还提出了一种飞行器，所述飞行器包括根据前一变体所述的至少一个短舱。
附图说明
通过阅读以下对实施例的描述，将更清楚地理解本发明的上述特征和其他的特征，所述描述参照附图给出，在附图中：
图1是根据本发明的飞行器的侧视图，
图2是根据本发明的吸声面板的侧向截面视图，
图3示出了放置在复合结构中的前部插入件，并且
图4示出了根据本发明的吸声面板的生产方法的算法。
具体实施方式
图1示出了飞行器10，该飞行器包括至少一个推进系统12，该推进系统包括发动机(尤其是双流式涡轮喷气发动机)以及围绕发动机的短舱14。
短舱14集成有吸声面板，这些吸声面板安排在流过短舱14的气流周围。
图2示出了吸声面板20的结构。
吸声面板20包括抵靠气流50定位的复合结构22、固定至复合结构22的蜂巢结构24和固定至蜂巢结构24的后蒙皮26。
蜂巢结构24和后蒙皮26的固定通过粘合剂结合进行。
图3示出了插入件28，该插入件包括喷口30和盖帽32。喷口30是具有通孔34的中空圆柱体的形式。盖帽32包括圆柱形式的底座36和圆锥体形式的覆盖件38。底座36的直径被适配于孔34的直径，以便使得能够将底座36插入孔34中和将其移除。
孔34可以尤其具有小直径，尤其是小于1mm。
复合结构22包括喷口30，并且每个喷口30嵌入复合结构22中，使得孔34在复合结构22的一侧和另一侧开口。因此，喷口30的长度至少等于复合结构22的厚度。
在复合结构22生产期间，插入件28集成在复合结构22中，然后盖帽32被抽取出，以便仅留下喷口30并因此释放孔34。插入件28的定位通过将覆盖件38穿入复合结构22中来进行，直到盖帽32从复合结构22露出并且孔34在复合结构22的一侧和另一侧开口。例如，通过施加侧向力来执行盖帽32的移除，这使得盖帽32能够从喷口30移除。
图4示出了吸声面板20的生产方法40。生产方法40包括：
-生产步骤42，在该生产步骤期间生产复合结构22，
-提供步骤43，在该提供步骤期间提供插入件28，并且其中，每个插入件28包括喷口30和盖帽32，该喷口为具有通孔34的中空圆柱体的形式，该盖帽包括圆柱体形式的底座36和圆锥体形式的覆盖件38，并且其中底座36容纳在孔34中，
-定位步骤44，在该定位步骤期间，通过将覆盖件38(即圆锥体)穿入复合结构22中而使得插入件28定位在复合结构22中，
-聚合步骤46，在该聚合步骤期间，具有插入件28的复合结构22被聚合，
-移除步骤48，在该移除步骤期间移除盖帽32，
-第一组装步骤50，在该第一组装步骤期间，蜂巢结构24固定至已聚合的复合结构22，以及
-第二组装步骤52，在该第二组装步骤期间，后蒙皮26固定至蜂巢结构24。
在聚合之前插入件28的定位防止复合结构22的尚未固化的复合纤维断裂。
每个插入件28手动定位或使用合适的例如枪型的工具定位。覆盖件38的圆锥体形状有助于插入件28穿入复合结构22中。
在聚合之前盖帽32的存在防止孔34在聚合期间被复合结构22的树脂阻塞。
为了确保喷口30被更好地保持在复合结构22中并且降低复合结构22的树脂迁移的风险，喷口30包括加宽的底座39。
如果喷口30和盖帽32彼此独立地生产，则可以手动地执行底座36到孔34中的插入。然而，喷口30优选地通过包覆成型在底座36上来生产。

Claims (6)

1.一种吸声面板(20)的生产方法(40)，所述生产方法(40)包括：
-生产步骤(42)，在所述生产步骤期间生产复合结构(22)，
-提供步骤(43)，在所述提供步骤期间提供插入件(28)，并且其中，每个插入件(28)包括喷口(30)和盖帽(32)，所述喷口是具有通孔(34)的中空圆柱体的形式，所述盖帽包括圆柱体形式的底座(36)和圆锥体形式的覆盖件(38)，并且其中，所述底座(36)容纳在所述孔(34)中，
-定位步骤(44)，在所述定位步骤期间，所述插入件(28)通过所述覆盖件(38)穿入所述复合结构(22)中而定位在所述复合结构(22)中，使得所述孔(34)在所述复合结构(22)的一侧和另一侧开口，
-聚合步骤(46)，在所述聚合步骤期间，具有所述插入件(28)的所述复合结构(22)被聚合，
-移除步骤(48)，在所述移除步骤期间，移除所述盖帽(32)，
-第一组装步骤(50)，在所述第一组装步骤期间，蜂巢结构(24)固定至所述聚合复合结构(22)，以及
-第二组装步骤(52)，在所述第二组装步骤期间，后蒙皮(26)固定至所述蜂巢结构(24)。
2.根据权利要求1所述的生产方法(40)，其特征在于，在所述提供步骤(43)之前是包覆成型步骤，在所述包覆成型步骤期间，所述喷口(30)包覆成型在所述底座(36)上。
3.一种插入件(28)，所述插入件用于实施根据权利要求1或2所述的生产方法(40)、并且包括：喷口(30)和盖帽(32)，所述喷口是具有通孔(34)的中空圆柱体的形式，所述盖帽包括圆柱体形式的底座(36)和圆锥体形式的覆盖件(38)，并且其中，所述底座(36)容纳在所述孔(34)中。
4.一种使用根据权利要求1或2所述的生产方法获得的吸声面板(20)。
5.一种用于飞行器发动机的短舱(14)，所述短舱包括至少一个根据权利要求4所述的吸声面板(20)。
6.一种飞行器(10)，所述飞行器包括至少一个根据权利要求5所述的短舱。
CN201910586899.2A 2018-07-04 2019-07-02 吸声面板及其生产方法、插入件、飞行器及其发动机短舱 Pending CN110683060A (zh)

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