CN103328330A - 涡轮喷气发动机机舱的进气口结构的制造方法 - Google Patents
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Abstract
本发明涉及到一种涡轮喷气发动机机舱的进气口结构(1)的制造方法,所述进气口结构至少包括两部分,即,至少一个进气口唇缘结构(2)和至少一个用于进气口结构的外罩(3),其特征在于,所述方法包括如下步骤:分别制造组成部件,使得每个组成部件包括至少一个部分(2a、3a),所述部分用于覆盖后者所附接的部件;并且牢固地连接所述覆盖部分,尤其是通过粘合和/或使用附接方式来连接。
Description
技术领域
本发明涉及一种用于涡轮喷气发动机机舱的进气口结构。
背景技术
如其本身已知,传统的飞行器推进组件包括容纳于发动机舱内的涡轮喷气发动机。
发动机舱通常具有环形结构,该环形结构包括在涡轮喷气发动机上游的进气口、设计成环绕涡轮喷气发动机的风扇及其壳体的中间段以及设计成环绕涡轮喷气发动机的燃烧室(如果适用的话,并容纳推力反向器装置)的下游段。发动机尾部为喷嘴,该喷嘴的出口位于涡轮喷气发动机的下游。
该进气口结构用于优化对需要供给到涡轮喷气发动机风扇的空气的捕获,并将其引导向该风扇。
空气进气口结构尤其包括位于上游的前缘结构,通常称为空气进气口“唇缘”(lèvre)。
进气口唇缘捕获空气,并附接至进气口结构的余下部分,该余下部分将所捕获的空气引导到涡轮喷气发动机。
为此,进气口结构的余下部分具有基本环形的结构,包括保证发动机舱外部气动连续性的外表面,以及保证发动机舱内部气动连续性的内表面。所述空气进气口唇缘提供了在两个壁之间的上游连接。
整个进气口结构被附接至发动机舱中间段和风扇壳体的上游。
进气口唇缘结构可以包括很多部件。通常地,尤其包括空气动力的表层(可以由夹接在一起的几个扇形制成)、一个或多个加强分区、一个或多个用于分区或用于附接至进气口结构的余下部分的连接截面。
目前,这些元件可以由异质材料制成,尤其是不同的金属合金,典型地是铝基和/或钛基的金属合金。某些元件也可以由合成材料制成。
如今,这些元件必须通过紧固来装配。这导致了显著的装配时间和与这些紧固及装配相关的空气动力学损失。
还已知一种具有进气口结构的所谓层式(laminaires)的发动机舱,该进气口结构具有改善空气动力性能的外部连续性。在文献FR2,906,568中特别描述了这种结构。
目前,可以通过将进气口唇缘和外罩组合在一个单件式结构中来获得这种层式结构,因而,保证了无需紧固件并且优化了的外部空气动力表面。
这种单件式结构不易生产,且需要专用的模具和尺寸合适的设备。因而它很昂贵。而且,在相同的制造技术(单件式生产)中,它很难使可具有显著厚度的唇缘结构和由于承受很小力而具有很小厚度的罩结构一致。
发明内容
本发明的目的在于,通过能够以几个初始部件来实现这种层式结构,来消除这些缺点。
为此,本发明包括一种涡轮喷气发动机舱的进气口结构的制造方法,所述结构包括至少两个部件,包括至少一个进气口唇缘结构和至少一个进气口结构外罩,其特征在于,包括如下步骤:
-分别制造组成部件,使得每个整合至少一个部分,该部分与设计为与其相附接的部分相重叠,所述重叠部分被配置为使得外重叠部分的外表面与关联至内重叠部分的部件的外表面确保连续,
-固定所述重叠部分,尤其是通过胶合和/或紧固方式。
因而,通过设置设计为在所述部件之间提供连接的重叠部分,可以确保对外表面的优化,使得仅有非常有限数量的空气动力学故障。
因而,获得了外轮廓一致的外部结构,在减少组装元件和所需设置这些元件的时间的同时,确保了阻力的最小化和重量的优化。
通过树脂灌注或者树脂注塑类型的制造方法将树脂注入干的加强框架中(例如特别是织布的、编织的或呢绒的),将能够获得具有减少的操作数量的整个进气口外结构。
根据一个优选实施例,通过附着成型所述重叠部分来完成所述固定。
优选地,所述唇缘结构和外罩的重叠部分是基本是纵向的,并且至少是部分外围的,最好是全部外围的。
有利地,形成所述进气口唇缘的部件是单件。它尤其可以由合成材料制成,并且可以使用例如树脂灌注、树脂注入,或树脂传递模塑法来获取。
有利地,形成所述外罩的部件是单件。它尤其可以由合成材料制成,并且可以使用例如树脂灌注、树脂注入,或树脂传递模塑法来获取。
有利地,根据一个可选实施例,构成外罩的部件可以由两个半部件组成,特别地,所述两个半部件设计成相互卡住。这样允许更容易地适应所述进气口唇缘的直径,尤其是在考虑制造公差的情况下。
优选地,所述外罩形成鼓状。
根据一个可选实施例,所述外罩形成了开放的套罩,以便于所述进气口唇缘的整合。
本发明还涉及到一种进气口结构,采用根据本发明的方法获得。
附图说明
参考附图,通过接下来的详细描述,本发明将得到更好的理解。
图1示出了根据本发明的进气口结构的总图示示意图;
图2是图1中进气口结构的局部剖视图的纵向视图;
图3是图2中进气口唇缘与进气口结构外壁之间的连接区域的局部放大视图。
图4到6示出了根据本发明的可选实施例的进气口结构的图示示意图。
图7示出了根据本发明的另一个可选实施例的进气口结构的剖视示意图。
具体实施例
如图1所示,根据本发明的进气口结构1,包括一个进气口唇缘结构2和外壁3,其中进气口唇缘结构2设计成保证最佳地捕获朝向涡轮喷气发动机的空气,外壁3设计成保证所述发动机舱的外部气动连续性,并且其上附接有进气口唇缘结构。
在图1至3所示的示例中,该外圆柱3假定为形成鼓形的整个外围套罩。
外圆柱3可以整合一个或多个加强件,例如,图1、2和4中示出的圆周加强件4。它也可整合其他形式的加强件,纵向或螺旋状或横梁的截面和方向。
外罩3与空气进气口唇缘在分隔件5的上游连接,该分隔件5可以整合到进气口唇缘或套罩中,最好是在外罩3中。
根据本发明,所述进气口结构1的制造包括下述步骤,其首要目的是分别制造出组成部件(在当前示例中,组成部件即,外罩3和空气进气口唇缘2),这样使得每个组成部件将至少一个重叠部分3a或2a与设计成被附接的部分分别整合。所述重叠部分可以通过延伸外表层来制成。
在当前示例中,进气口唇缘的重叠部分2a设计成容纳外罩3的重叠部分3a。
重叠部分3a和2a被配置成使得外重叠部分2a的外表面与罩3的外表面的部件(即与内重叠部分3a相关联的部件)确保连续性。
然后,该重叠部分被固定,尤其是通过胶合和/或使用紧固件被固定。
如果存在的话,上游分隔件5也可以用来设置补充的紧固件6。
图4到6示出了外罩3和进气口唇缘2结构的多个实施例。
图4示出了一种由两个基本上是半圆柱形的半部件30a、30b(尤其是可以彼此相互卡住)构成的外罩。
图5示出了一种以开放的套罩的形式制成的外罩,目的是便于进气口唇缘2的整合,尤其是出于机械加工余量的考虑。
图6示出了一种形成鼓状的单件式外罩32。
尤其有利地,将进气口唇缘2可以是单件。
图7示出了另外一个实施例,其中重叠部分2a、3a通过附着成型来组装。
尽管本发明只描述了一个特定实施例,当然其不仅限于此,还包括了在本发明的范围之内的与所描述的装置相等同的所有技术及其组合。
Claims (9)
1.一种涡轮喷气发动机机舱的进气口结构(1)的制造方法,所述进气口结构包括至少两个组成部件,所述至少两个组成部件包括至少一个进气口唇缘结构(2)和至少一个进气口结构外罩(3),其特征在于,所述制造方法包括如下步骤:
-分别制造组成部件,使得每个组成部件所整合的至少一部分(2a、3a)和设计为与之相附接的部分重叠,所述重叠部分被配置成确保外重叠部分的外表面和与内重叠部分相关的部件的外表面连续,
-固定所述重叠部分,尤其是通过胶合和/或紧固方式。
2.根据权利要求1所述的制造方法,其特征在于,通过将所述重叠部分(2a、3a)附着成型来完成所述固定。
3.根据权利要求1或2所述的制造方法,其特征在于,所述唇缘结构(2)与所述外罩(3)的重叠部分(2a、3a)基本是纵向的,并且至少是部分外围的,最好是全部外围的。
4.根据权利要求1至3中任一项所述的制造方法,其特征在于,形成所述进气口唇缘(2)的部件是单件。
5.根据权利要求1至4中任一项所述的方法,其特征在于,构成所述外罩(32)的部件是单件。
6.根据权利要求1至4中任一项所述的方法,其特征在于,构成所述外罩(3)的部件由两个半部件(30a、30b)制成,特别地,所述两个半部件设计成相互卡住。
7.根据权利要求5或6所述的制造方法,其特征在于,所述外罩(3)形成鼓状。
8.根据权利要求5或6所述的制造方法,其特征在于,所述外罩(3)形成了开放的套罩(31)。
9.一种进气口结构(1),采用根据权利要求1到8中任一项所述的制造方法获得。
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FR11/50890 | 2011-02-04 | ||
FR1150890A FR2971232B1 (fr) | 2011-02-04 | 2011-02-04 | Procede de fabrication d'une structure d'entree d'air de nacelle de turboreacteur |
PCT/FR2012/050230 WO2012104560A1 (fr) | 2011-02-04 | 2012-02-02 | Procédé de fabrication d'une structure d'entrée d'air de nacelle de turboréacteur |
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CA2482168A1 (en) * | 2002-04-15 | 2003-10-30 | Dow Global Technologies Inc. | Improved vehicular structural members and method of making the members |
FR2906568B1 (fr) | 2006-10-02 | 2012-01-06 | Aircelle Sa | Structure d'entree d'air deposable pour nacelle de turboreacteur. |
FR2929991B1 (fr) * | 2008-04-10 | 2010-05-07 | Airbus France | Panneau pour le traitement acoustique integrant un renfort de liaison |
-
2011
- 2011-02-04 FR FR1150890A patent/FR2971232B1/fr active Active
-
2012
- 2012-02-02 EP EP12707850.9A patent/EP2670663B1/fr active Active
- 2012-02-02 CA CA2825982A patent/CA2825982C/fr not_active Expired - Fee Related
- 2012-02-02 RU RU2013139994/11A patent/RU2013139994A/ru not_active Application Discontinuation
- 2012-02-02 CN CN2012800058143A patent/CN103328330A/zh active Pending
- 2012-02-02 BR BR112013016820A patent/BR112013016820A2/pt not_active IP Right Cessation
- 2012-02-02 WO PCT/FR2012/050230 patent/WO2012104560A1/fr active Application Filing
-
2013
- 2013-08-02 US US13/958,246 patent/US9481054B2/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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US4629146A (en) * | 1985-01-30 | 1986-12-16 | Rohr Industries, Inc. | Hold open rod for hinged section of nacelle system |
US6328258B1 (en) * | 1998-12-21 | 2001-12-11 | Aerospatial Natra | Air intake structure for aircraft engine |
US7383679B2 (en) * | 2004-03-29 | 2008-06-10 | Airbus France | Air intake structure for aircraft engine |
CN101835686A (zh) * | 2007-10-22 | 2010-09-15 | 埃尔塞乐公司 | 进气口的压电式除冰 |
Also Published As
Publication number | Publication date |
---|---|
RU2013139994A (ru) | 2015-03-10 |
EP2670663A1 (fr) | 2013-12-11 |
EP2670663B1 (fr) | 2018-03-28 |
WO2012104560A1 (fr) | 2012-08-09 |
BR112013016820A2 (pt) | 2016-09-27 |
FR2971232A1 (fr) | 2012-08-10 |
CA2825982C (fr) | 2019-07-30 |
CA2825982A1 (fr) | 2012-08-09 |
US9481054B2 (en) | 2016-11-01 |
US20130312263A1 (en) | 2013-11-28 |
FR2971232B1 (fr) | 2013-01-18 |
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