CN103958350A - 具有内置取样收集器的复合面板 - Google Patents

具有内置取样收集器的复合面板 Download PDF

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CN103958350A
CN103958350A CN201280055083.3A CN201280055083A CN103958350A CN 103958350 A CN103958350 A CN 103958350A CN 201280055083 A CN201280055083 A CN 201280055083A CN 103958350 A CN103958350 A CN 103958350A
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panel
composite panel
uppermost layer
opening
sampling
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CN103958350B (zh
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弗兰克·洛朗
弗朗索瓦·贝列特
让-菲利普·若勒
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Safran Nacelles SAS
Safran Nacelles Ltd
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Hurel Hispano SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
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    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
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    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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    • 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
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    • B32B2605/00—Vehicles
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • 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
    • B64D2241/00—NACA type air intakes
    • 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
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
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    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
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    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
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    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
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    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
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    • Y10T428/24182—Inward from edge of web or sheet
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Abstract

本发明涉及一种复合面板(30)，包含至少一个内表层(3)和一个外表层(2)，并且具有至少一个用于接收取样收集器的开口(5)，所述开口(5)形成通道，并且该采样开口与所述外表层连通，其特征在于，所述外表层被成形为使得在开口处同样形成取样收集器的过流面的至少一部分。

Description

具有内置取样收集器的复合面板
技术领域
本发明涉及一种集成到复合面板中的用于涡轮喷气发动机机舱的收集器。
背景技术
飞行器由数个均安置在机舱内的涡轮喷气发动机驱动。每个机舱内部也容纳有一组与操作相关的辅助设备，并且所述辅助设备在当所述涡轮喷气发动机运行或停止时提供多种功能。
机舱通常具有管状结构，所述管状结构包括在涡轮喷气发动机前面的进气口、中部、后部和排气喷嘴，所述中部用于包围涡轮喷气飞机的风扇，所述后部可以可选地包含推力反向装置并且用于包围涡轮喷气发动机的燃烧室，所述排气喷嘴的出口设置在涡轮喷气发动机的下游。
现代机舱通常用于容纳双流涡轮喷气发动机，所述发动机能够通过旋转风扇叶片产生来自涡轮喷气发动机燃烧室的热空气流(也称为一次流)。
机舱典型地具有称为外部固定结构(OFS)的外部固定结构，所述外部固定结构和被称为内部固定结构(IFS)的同轴内部固定结构，包括在风扇下包围涡轮喷气发动机本身的整流罩一起限定了也被称为管的环形流道，所述环形流道引导也被称为二次流的在涡轮喷气发动机外部流动的冷空气气流。
所述一次流和二次流在机舱的后部排出涡轮喷气发动机。
每个飞机推进装置因此由机舱和涡轮喷气发动机组成，并且悬挂在飞机的固定结构上，例如，在机翼的下面或者在机身上，通过挂架或者杆固定到机舱的涡轮喷气发动机上。
机舱外部结构的后部，通常是由两个大体上半圆柱状的整流罩在机舱的对称垂直纵向平面的每一侧上形成，并且可活动地安装，以便在工作位置和进入涡轮喷气发动机的维护位置之间延伸。
相同的结构也适用于中部，所述中部适于被打开以允许进入风扇。
因此应该注意的是飞机推进装置集成了功能子装置，所述子装置具有相对运动，并且在它们之间应该进行密封。
更具体地，应该注意的是所述后部和中部包括分别用作排气喷嘴的外壳和风扇的外壳的子装置，所述推进装置对气流生成和定向起重要作用。
为了给飞机提供配风回路(空气调节、座舱增压等)，在涡轮喷气发动机压缩机处的空气被取样。该空气当然是非常热的并且必须要被冷却。具体的是通过预冷装置(“预冷器”)进行冷却，所述预冷装置使用由称作预冷机收集器的收集器取样的冷空气。
另一方面，所述机舱子装置要经受使它们膨胀和引起变形，特别是径向变形的温度。
因此，当风扇罩和所述风扇叶片之间的间距必须被控制以保证风扇最佳效率时，所述罩的径向膨胀可以导致该间距的增加，并且因此导致风扇性能的降低，因为更多的未压缩的空气将通过该间隙逸出。
为了克服该缺点，该卡特风扇将称为TTC(涡轮机间隙控制)的冷空气配风回路装配到其表面上。该冷空气通常是由位于冷空气流流通区域(管区域)的称为TTC收集器的收集器取样。
该原理也适用于机舱的其他部件，例如所述排气喷嘴。
所述取样收集器因此通常是用来保证将取样的空气输送到冷却回路。
为此，所述收集器具有大体上管状通道的形式，所述管状通道具有一定轮廓的取样开口，以允许限制由取样引入的空气动力干扰。
穿过与冷空气流接触的壁插入所述收集器，所述空气取样开口引入到所述取样空气流的流通区域中。该区域特别可以朝向二次流的流通管的IFS外侧板。
在面板是由金属合金制成的情况下，所述收集器通常是被引入到切口中，并且在它的取样开口处具有外围法兰，所述法兰用于保证面板表面的空气动力连续性，并且通过铆接或者焊接将所述收集器固定到该面板上。
复合材料在机舱面板的制造中的广泛使用对于这些收集器的设置带来大的挑战。
事实上，目前，收集器结构必须用和金属合金面板相同的方式附接到面板上，也就是基本上按所述收集器的形状来制作面板切口。
但是，制作复合面板切口通常是不明智的，这样的切口会引起复合面板的纤维和内部结构(芯部)的断裂，这可能会影响它的完整性和机械抗力。
由于相同的原因，存在固定装置穿过即使是部分穿过复合面板结构也是不受欢迎的。
因此需要一种允许克服至少部分上述缺点的并且允许通过复合材料面板设置取样收集器的方案。
发明内容
为此，本发明涉及一种复合面板，所述复合面板至少包括内表层和外表层，并且至少具有用于接收形成管道的取样收集器的开口、其取样开口嵌入到所述外表层中，其特征在于所述外表层被成形为在所述开口处形成取样收集器的过流面的至少一部分。
因此，通过直接由复合面板本身制作取样收集器的过流面的一部分，并且更具体地通过根据合适的轮廓形成其中的外表层，获得了所述收集器和这样的复合面板的更好集成。因此能够限制切口，并且，因此，限制对复合面板的结构完整性的损害。
通过限制在面板结构和收集器之间的间隙和缝隙，这也有助于保证最佳的空气流动连续性。
值得注意的是，尽管本发明是以预冷机收集器和TCC来介绍的，但它并没有限制在此，并且可包括任何形式的空气取样收集器，特别是穿过如IFS面板的复合面板插入的收集器。
有利地，形成收集器过流面的外表层是通过将外表层在厚度上向面板的内部冲压和弯曲形成的。
互补部分可以被添加且通过任何方式(胶合、铆接、等等)将其固定，并且其可由任何合适的材料制成。
优选地，所述外表层被弯曲至少超过面板的厚度。
根据可替换的优选实施例，由外表层形成的过流面沿着用于取样收集器的开口的整个外围延伸。因此，收集器的取样开口完全由面板本身构成，这保证了最佳流动和集成。
有利地，所述取样收集器完全由外表层构成，并且在适当的时候由外表层和内表层构成。尤其是当由复合面板制成的收集器的一部分超过所述面板的厚度时是这种情况。所述内表层将会提供收集器部分的外周长，所述外表层提供形成的管道的内周长。
根据一实施例，所述面板包括至少一个配置在所述内表层和所述外表层之间的芯部。
可选地，用于取样收集器的开口位于所述面板的包括芯部的区域，该区域称为夹层区域。
可选地，当所述面板不包括任何芯部的时候，用于取样收集器的开口可以位于所述面板的不包括任何芯部的区域，该区域称为单层区域。
本发明也涉及包括取样收集器的复合面板，其特征在于，所述复合面板是根据本发明的面板。
有利地，所述取样收集器包括添加到所述面板的内表层的固定边缘。
这样的面板尤其可以是涡轮喷气发动机机舱的内部结构的面板，用来包围所述涡轮喷气发动机的燃烧室。
附图说明
根据下面具体的描述，并参考附图，本发明将会被更好地理解，其中：
图1是根据现有技术的用于接收取样收集器的复合面板的示意图，
图2是根据本发明的用于接收在所述面板单层区域的取样收集器的横截面示意图，
图3是根据本发明的包括安装在所述面板的夹层区域的取样收集器的复合面板的顶视示意图，
图4是对应于图3的底视示意图，
图5是对应于图4的不包括所述取样收集器部分的底视示意图，
图6和7分别是根据本发明的包括集成到面板且完全由所述面板形成的取样收集器的复合面板的顶视示意图和底视示意图，
图8是图6和7的面板的横截面示意图。
具体实施方式
如图1所示，复合面板1通常包括外表层2和内表层3以及可选择地包括芯部4。
面板1包括芯部4的的部分被称作夹层区域。面板1不包括芯部的部分被称作单层区域。这些通常是面板1的末端和边缘部分。
该复合面板1具有开口5，该开口用来接收形成管道的空气取样收集器(未展示)、其取样开口通向外表层。
根据现有技术和现行方法，所述开口是由面板1的简单切口制成的，该切口导致前述缺点：在夹层区域暴露出芯部4、外表层2和内表层3的结构的破裂，以及更普遍地会破坏复合面板的完整性、面板上收集器的调节空隙和间隙、引起空气动力干扰的固定。
为了克服这些缺点，根据本发明，复合面板将通过对外表层成形来获得，使得它在所述开口处形成取样收集器的过流面的至少一部分。
图2到7示出了根据本发明的用于收集器的复合面板的多种实施例。
图2是具有用于位于单层区域的取样收集器的开口5的复合面板10的横截面视图。特别地，所述开口5通过在夹层区域的芯部4的内表层3和外表层2形成的外围法兰来限定。
根据本发明，该外围法兰，因此对应的外表层，被成形为在面板10的上游区域形成朝向接收收集器的开口5的过流面，用来将待采样的气流向上游定向。该过流面因此形成收集器过流面的一部分。
收集器7的其余结构可以被加入到面板10上的开口5中，并且将所述开口的下游与环形件6固定，所述环形件6通过插入到开口10的法兰上来保持。
该环形件，当然，只是可能的固定的一个例子，并且本领域技术人员熟知的任何固定模式(铆接、螺栓连接、胶合、等等)都可以考虑。
因此，收集器被部分地集成到复合面板中并且改善了空气取样。
图3和4示出了类似于图2中面板的复合面板20，除了收集器7的开口5位于芯部4夹层区域。图3示出了外表层3，它被弯曲到以嵌入到面板20的厚度中，从而保证由收集器7形成的取样管道的空气动力连续性。
图5对应于不包括嵌入到面板的收集器7结构的图3和4的实施例。可注意到在开口的上游区域的外表层2和内表层3之间厚度递减，所述开口用于在待取样的空气流方向上定向。
图6和7示出了复合面板30，其中收集器结构是完全由面板30的外表层2和内表层3制成，所述内表层2和外表层3被连接以形成取样收集器的管道。
因此，收集器被集成到面板上，并且过流面是空气动力最佳的。
图8更具体地示出了面板结构30。可注意到由收集器形成的管道装配有外围密封件31，所述外围密封件31由固定在面板30的内表层2和外表层3的固定夹32支撑。
尽管以实施例的具体例子来描述本发明，但是，当然，本发明不受其限制，并且包括已经描述的装置的所有的技术等同方案和它们的结合，如果它落在本发明的范围内。

Claims (10)

1.一种复合面板(10、20、30)，其至少包括内表层(3)和外表层(2)，并且具有至少一个开口(5)，所述开口(5)用于接收形成管道的取样收集器(7)，取样开口引入所述外表层，其特征在于，所述外表层被成形为以便在所述开口处形成取样收集器的过流面的至少一部分。
2.如权利要求1所述的复合面板(10、20、30)，其特征在于，形成收集器过流面的所述外表层(2)是通过将外表层在厚度上朝向面板的内部冲压和弯曲形成的。
3.如权利要求2所述的复合面板(10、20、30)，其特征在于，所述外表层(3)被弯曲至少超过面板的厚度。
4.如权利要求1至3中任一项所述的复合面板(30)，其特征在于，由所述外表层(3)形成的过流面沿着用于取样收集器的开口的整个外围延伸。
5.如权利要求4所述的复合面板(30)，其特征在于，所述取样收集器完全由外表层构成，并且在适当的时候由外表层和内表层构成。
6.如权利要求1至5中任一项所述的复合面板(20、30)，其特征在于，它包括至少一个配置在所述内表层(3)和所述外表层(2)之间的芯部(4)。
7.如权利要求6所述的复合面板(20、30)，其特征在于，用于所述取样收集器(7)的所述开口(5)位于所述面板的包括所述芯部(4)的区域中，所述区域称为夹层区域。
8.如权利要求1至5中任一项所述的复合面板(10)，其特征在于，用于所述取样收集器(7)的所述开口(5)位于所述面板的不包括任何芯部(4)的区域，所述区域称为单层区域。
9.包括取样收集器(7)的复合面板(10、20、30)，其特征在于，所述复合面板是根据权利要求1至8中任一项所述的面板。
10.如权利要求9所述的复合面板(10、20)，其特征在于，所述取样收集器(7)包括添加到所述面板的内表层(3)上的固定边缘(6)。
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106995049A (zh) * 2017-03-23 2017-08-01 西安飞机工业（集团）有限责任公司 一种飞机匣体结构
CN110863909A (zh) * 2018-08-27 2020-03-06 赛峰短舱公司 用于飞行器的进气口

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11022047B2 (en) * 2019-08-07 2021-06-01 Raytheon Technologies Corporation External turning vane for IFS-mounted secondary flow systems
FR3142177A1 (fr) * 2022-11-22 2024-05-24 Airbus Operations (S.A.S.) Aéronef comprenant au moins un dispositif d’admission d’air configuré pour limiter l’apparition de bruits aérodynamiques

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2352790A (en) * 1941-03-29 1944-07-04 United Aircraft Corp Air intake scoop
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US6050527A (en) * 1997-12-19 2000-04-18 The Boeing Company Flow control device to eliminate cavity resonance
FR2879564A1 (fr) * 2004-12-20 2006-06-23 Airbus France Sas Agencement d'entree d'air de ventilation a element d'obturation mobile
CN101084367A (zh) * 2004-12-20 2007-12-05 法国空中巴士公司 通风进气装置
CN101687552A (zh) * 2007-04-24 2010-03-31 空中巴士营运公司 用于交通工具特别是飞行器的空气吸入设备
CN101842628A (zh) * 2007-08-20 2010-09-22 埃尔塞乐公司 具有整体式配合表面的密封接头
CN102216159A (zh) * 2008-10-07 2011-10-12 空中客车运营简化股份公司 飞行器用的进气设备

Family Cites Families (58)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1608727A (en) * 1925-04-04 1926-11-30 Rodic Rubber Co Coated rubber and process for producing the same
US2699906A (en) * 1949-10-25 1955-01-18 Northrop Aircraft Inc Air inlet for airplane gaseous combustion turbine engines
US2721715A (en) * 1951-09-28 1955-10-25 Chance Vought Aircraft Inc Flush inlet
FR1081201A (fr) * 1953-04-24 1954-12-16 Sncaso Perfectionnements aux réacteurs auxiliaires pour avions
US3578526A (en) * 1968-01-22 1971-05-11 United Aircraft Corp Method of making reinforced honeycomb sandwich
DE2201319C3 (de) * 1972-01-12 1978-10-12 Klepper-Werke, 8200 Rosenheim Verfahren und Vorrichtung zur Herstellung einer ausgeschäumten Bootsschale für ein Segelboot
FR2241695B1 (zh) * 1973-08-21 1978-03-17 Bertin & Cie
US4132240A (en) * 1977-03-28 1979-01-02 General Electric Company Variable double lip quiet inlet
US4121606A (en) * 1977-10-25 1978-10-24 General Dynamics Corporation Inflatable air inlet duct
US4378097A (en) * 1980-11-24 1983-03-29 The Boeing Company High performance submerged air inlet
US4418879A (en) * 1980-12-29 1983-12-06 The Boeing Company Scoop and inlet for auxiliary power units and method
JPS57173126A (en) * 1981-04-20 1982-10-25 Nissan Motor Co Ltd Working method for edge section of composite material
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
US4738416A (en) * 1986-09-26 1988-04-19 Quiet Nacelle Corporation Nacelle anti-icing system
IT1208852B (it) * 1987-02-17 1989-07-10 Fiat Auto Spa Dispositivo per contrastare fenomeni di imbrattamento dei gruppi ottici posteriori di autoveicoli
US4826106A (en) * 1987-02-18 1989-05-02 Grumman Aerospace Corporation Advanced composite aircraft cowl
US5049342A (en) * 1987-12-29 1991-09-17 Sundstrand Corporation Method of fabricating composite structures
US4993663A (en) * 1989-06-01 1991-02-19 General Electric Company Hybrid laminar flow nacelle
US5083426A (en) * 1989-10-02 1992-01-28 Rohr Industries, Inc. Integrated engine shroud for gas turbine engines
DE4008956A1 (de) * 1990-03-20 1991-09-26 Messerschmitt Boelkow Blohm Einlaufsystem fuer ueber- oder hyperschallflugzeuge
GB2259328B (en) * 1991-09-03 1995-07-19 Gen Electric Gas turbine engine variable bleed pivotal flow splitter
US5269135A (en) * 1991-10-28 1993-12-14 General Electric Company Gas turbine engine fan cooled heat exchanger
FR2730275B1 (fr) * 1995-02-03 1997-03-28 Aerospatiale Dispositif d'etancheite entre une entree d'air et un carter de soufflante de turboreacteur a double flux
US5654060A (en) * 1995-06-16 1997-08-05 The Boeing Company High temperature insulation system
US6179943B1 (en) * 1997-07-30 2001-01-30 The Boeing Company Method for forming a composite acoustic panel
US6129311A (en) * 1997-07-30 2000-10-10 The Boeing Company Engine nacelle outer cowl panel with integral track fairings
DE19904986A1 (de) * 1999-02-08 2000-08-10 Benien Produktionstechnik Gmbh Schallabsorbierende Abdeckung und Verfahren zur Herstellung derselben
CA2423665A1 (en) * 2000-10-02 2002-04-11 Bell Helicopter Textron Inc. Composite skin panel opening edge and method for manufacture
US7588212B2 (en) * 2003-07-08 2009-09-15 Rohr Inc. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
GB2407142B (en) * 2003-10-15 2006-03-01 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
US7798873B1 (en) * 2005-06-22 2010-09-21 The United States Of America As Represented By The Secretary Of The Navy Design of a flush inlet as integrated with a ship hull for waterjet propulsion
US7967105B2 (en) * 2006-06-19 2011-06-28 Yen Tuan Aero-acoustic aviation engine inlet for aggressive noise abatement
US8839805B2 (en) * 2006-10-12 2014-09-23 United Technologies Corporation Passive boundary layer bleed system for nacelle inlet airflow control
GB2443830B (en) * 2006-11-15 2010-01-20 Rolls Royce Plc Cowling arrangement
US7556223B2 (en) * 2006-12-04 2009-07-07 The Boeing Company Vent system for an aerospace vehicle
US7665310B2 (en) * 2006-12-27 2010-02-23 General Electric Company Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl
US7966831B2 (en) * 2007-08-28 2011-06-28 General Electric Company Apparatus and method for suppressing dynamic pressure instability in bleed duct
GB2452298B (en) * 2007-08-30 2010-01-13 Gkn Aerospace Services Ltd Composite structure
US20090175718A1 (en) * 2007-12-31 2009-07-09 Carlos Diaz System and method for passive cooling of gas turbine engine control components
EP2318683A2 (fr) * 2008-07-30 2011-05-11 Aircelle Panneau d'atténuation acoustique pour nacelle de moteur d'aéronef
FR2935017B1 (fr) * 2008-08-13 2012-11-02 Snecma Paroi interne d'une nacelle de turbomachine
FR2936776A1 (fr) * 2008-10-08 2010-04-09 Aircelle Sa Structure d'entree d'air de nacelle
US7798285B2 (en) * 2008-11-14 2010-09-21 Rohr, Inc. Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers
US8128037B2 (en) * 2009-01-19 2012-03-06 The Boeing Company Apparatus and method for passive purging of micro-perforated aerodynamic surfaces
DE102009011635A1 (de) * 2009-03-04 2010-09-09 Rolls-Royce Deutschland Ltd & Co Kg Luftleitelement eines Laufspalteinstellungssystems einer Fluggasturbine
US8197191B2 (en) * 2009-04-14 2012-06-12 Rohr, Inc. Inlet section of an aircraft engine nacelle
GB0908540D0 (en) * 2009-05-19 2009-06-24 Rolls Royce Plc A gas turbine engine having a nacelle and a breather duct
US8726673B2 (en) * 2010-01-11 2014-05-20 Honeywell International Inc. Turbine engine bypass fan-bleed noise reduction
US20110265490A1 (en) * 2010-04-30 2011-11-03 Kevin Samuel Klasing Flow mixing vent system
FR2960216B1 (fr) * 2010-05-19 2013-02-15 Aircelle Sa Element d'aerodynamisme pour une nacelle d'aeronef
GB201013093D0 (en) * 2010-08-04 2010-09-15 Rolls Royce Plc Ventilation inlet
CN101994570A (zh) * 2010-11-19 2011-03-30 南京航空航天大学 基于旋涡排泄的埋入式进气道及使用该进气道的飞行器
US20130075539A1 (en) * 2011-09-26 2013-03-28 Mark J. Seger Composite aerospace structure with integrated conveyance element
US9200570B2 (en) * 2012-02-24 2015-12-01 Pratt & Whitney Canada Corp. Air-cooled oil cooler for turbofan engine
US9403600B2 (en) * 2012-05-01 2016-08-02 Lockheed Martin Corporation Integrated thermal protection and leakage reduction in a supersonic air intake system
US9194330B2 (en) * 2012-07-31 2015-11-24 United Technologies Corporation Retrofitable auxiliary inlet scoop
US9168716B2 (en) * 2012-09-14 2015-10-27 The Boeing Company Metallic sandwich structure having small bend radius

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2352790A (en) * 1941-03-29 1944-07-04 United Aircraft Corp Air intake scoop
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US6050527A (en) * 1997-12-19 2000-04-18 The Boeing Company Flow control device to eliminate cavity resonance
FR2879564A1 (fr) * 2004-12-20 2006-06-23 Airbus France Sas Agencement d'entree d'air de ventilation a element d'obturation mobile
CN101084367A (zh) * 2004-12-20 2007-12-05 法国空中巴士公司 通风进气装置
CN101687552A (zh) * 2007-04-24 2010-03-31 空中巴士营运公司 用于交通工具特别是飞行器的空气吸入设备
CN101842628A (zh) * 2007-08-20 2010-09-22 埃尔塞乐公司 具有整体式配合表面的密封接头
CN102216159A (zh) * 2008-10-07 2011-10-12 空中客车运营简化股份公司 飞行器用的进气设备

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106995049A (zh) * 2017-03-23 2017-08-01 西安飞机工业（集团）有限责任公司 一种飞机匣体结构
CN110863909A (zh) * 2018-08-27 2020-03-06 赛峰短舱公司 用于飞行器的进气口
CN110863909B (zh) * 2018-08-27 2022-08-02 赛峰短舱公司 用于飞行器的进气口

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