CN102124197B - 涡轮机机舱的内壁 - Google Patents
涡轮机机舱的内壁 Download PDFInfo
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
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- 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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- F05B2260/00—Function
- F05B2260/30—Retaining components in desired mutual position
- F05B2260/301—Retaining bolts or nuts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
一种用于涡轮机机舱的内壁,所述内壁包括:包围风扇叶片的外环形风扇壳体(126),所述风扇壳体(126)在其上游端处包括法兰(130)用以紧固与其沿轴向对准的环(134);和从所述风扇叶片向上游延伸的内环形隔音结构(142),所述风扇壳体(126)大致延伸至所述隔音结构(142)的上游端,使得所述风扇壳体的上游法兰邻近于所述隔音结构的上游端就位。
Description
技术领域
本发明涉及涡轮机机舱的内壁,其中所述涡轮机例如为飞机涡轮螺旋桨发动机或涡轮喷气发动机。
背景技术
通常,任何机舱内壁均包括外环形风扇壳体,该风扇壳体包围涡轮机风扇叶片并适于在其中紧固有包围风扇叶片的环形的耐磨材料层。风扇壳体在其下游端具有紧固到涡轮机中间壳体的环形法兰,并在其上游端具有紧固到环下游端的环形法兰,其中环的上游端连接到用于将机舱内外壁连接到一起的横向环形分隔部。特别地,横向分隔部可用于强化机舱并提供阻燃功能。
内环形隔音结构布置在风扇叶片上游以减少叶片在操作中所产生声波的传播。隔音结构位于风扇壳体耐磨层的上游并从耐磨层沿轴向延伸。
在现有技术中,为了安装单件隔音结构,所述结构在其下游端附近紧固到前述的环上,并在其上游端紧固到机舱的空气吸入唇。
已经提出通过将多个结构声学板组装到一起而形成环形结构的建议。然而,在板之间的连接区域构成存在声阻突变的区域,由此使该结构的隔音性能显著恶化。这样,隔音结构优选地由单一的大致柱形板制成,其从风扇壳体的耐磨层沿轴向延伸到机舱的空气吸入唇。
然而,此技术存在许多缺点。为了维护目的,有必要移除柱形板以移除空气吸入唇,而且花费相对较长时间。而且,板是结构性的,适于在空气吸入唇与中间壳体之间传力,结果其相对较重。而且其昂贵并制作复杂。最后,将风扇壳体连接到环的法兰就位在与风扇叶片分开一短的轴向距离之处,且他们在风扇叶片破损的情况下可能暴露于强力冲击和高程度机械应力。
发明内容
本发明的具体目的在于,针对这些缺点中的至少一些提供简单、有效、和便宜的解决方案。
为此,本发明提供一种用于涡轮机机舱的内壁,所述内壁包括:用于包围风扇叶片的外环形风扇壳体,所述风扇壳体在其上游端处包括一法兰用以紧固到与其共轴对准的环上;和用于从所述风扇叶片向上游延伸的内环形隔音结构,所述内壁的特征在于:所述风扇壳体大致延伸至所述隔音结构的上游端,所述风扇壳体的上游法兰邻近于所述隔音结构的上游端就位。
根据本发明,将内壳体连接到环的法兰与隔音结构的上游端错开。法兰与风扇叶片的轴向距离因而相对较大,由此限制法兰在风扇叶片破损情况下破裂的风险。由于此法兰不暴露于在叶片破损情况下的过度的冲击或应力,因而其可具有小于现有技术中的尺寸和重量。而且,用于将法兰紧固到环的装置可更轻、更简单,并沿圆周具有更少数量这可通过使风扇壳体沿轴向伸长而实现,此时风扇壳体从中间壳体延伸至空气吸入唇此壳体因而用于强化机舱内壁且本身足以在空气吸入唇与中间壳体之间传力。由此,可使用隔音结构,其为非结构性的并由此更便宜且制作更简单。还可削减或实际上省略现有技术的横向分隔部,这是由于通过风扇壳体提供的额外强化所致。风扇壳体优选地为单一件,并由诸如复合材料这样的高强轻质材料制成。
所述隔音结构可通过例如粘接、熔焊、硬焊、铆接或螺纹紧固而紧固到所述风扇壳体上。可选地,隔音结构可被可松脱地紧固到风扇壳体上以更易于在损坏情况下将其更换。
所述环优选在其上游端通过例如铆接紧固到所述机舱的空气吸入唇上。本发明使得更易于拆卸空气吸入唇,因为不必在执行此操作时移除隔音结构。
所述风扇壳体的法兰紧固到所述环的下游法兰上,这些法兰优选相对于所述涡轮机的纵轴大致沿径向或沿轴向延伸。
当这些法兰沿径向时,他们的接合面可与所述隔音结构的上游端大致对准。在一变例中,此接合面就位在与从所述隔音结构的上游端的上游或下游与所述上游端分开一距离之处。
所述隔音结构从所述风扇壳体的上游端沿轴向延伸经过所述壳体的轴向尺寸的仅一部分。
所述隔音结构可通过单件的或分段的声学环形板形成。
本发明还提供一种涡轮机,例如飞机涡轮螺旋桨发动机或涡轮喷气发动机,其包括机舱,所述机舱具有如前具体所述类型的内壁。
附图说明
通过阅读以下利用非限制性示例方式并参照附图进行的描述,本发明可被更好地理解,且本发明的其他细节、特征和优点将变得更加清楚,其中:
图1是用于安装单件声学结构的现有技术涡轮机的空气吸入口和风扇的局部示意性轴向截面半视图;
图2是本发明的涡轮机的空气吸入口和风扇的局部示意性轴向截面图;
图3是用于将风扇壳体紧固到本发明机舱内壁环的装置的局部示意性轴向截面图;
图4至6是对应于图3的图,它们显示出用于将壳体紧固到环的装置的各变化实施例。
具体实施方式
首先参见图1,其为飞机引擎的局部示意性轴向截面半视图,其中飞机引擎包括包围涡轮喷气发动机12的机舱10,涡轮喷气发动机12在其上游端包括风扇14,风扇14在机舱10内旋转,并产生流动于机舱与涡轮喷气发动机之间所形成的环形管道16中的次级流,且传输由引擎产生的一部分冲力。
涡轮喷气发动机12还包括在风扇14下游的压缩机18,接合机舱10的一部分空气穿过压缩机18并被称为主流。
机舱10包括两个环形壁20、22,这两个环形壁20、22大致为柱形,并相互叠套地延伸,且在它们上游端通过环形空气吸入唇24被连接到一起,环形空气吸入唇24的截面为圆滑或曲形构形并沿上游方向凸出。
机舱内壁20包括大致柱形的外风扇壳体26,风扇壳体26包围风扇14并在其纵向端处包括环形紧固法兰28、30。风扇壳体26的下游法兰28通过螺母-螺栓类型的装置紧固到包围涡轮机压缩机18的中间壳体32的上游环形法兰,风扇壳体26的上游法兰30通过螺母-螺栓类型的装置紧固到轴向尺寸小于风扇壳体轴向尺寸的环34的下游环形法兰。此环34的上游端被连接到增强和传力横向环形分隔部36的内周边,增强和传力横向环形分隔部36在其外周边连接到机舱的外壁22上。
环形耐磨材料层38紧固到风扇壳体26的内柱形表面并包围风扇叶片。此层在壳体26的中间或中部部分上沿轴向延伸。此层38的轴向尺寸基本上等于风扇叶片14的最大轴向尺寸。隔音板40、42也紧固到风扇壳体26并紧固到环34,且处于耐磨层38的上游和下游。
下游隔音板40通过其下游端部分紧固到风扇壳体26的内柱形表面上。它们位于耐磨层38的下游沿轴向延伸处。
单件的柱形上游隔音板42在其上游端紧固到空气吸入唇24,并且在其下游端邻近处紧固到环34的内柱形表面。此板42是结构性的,其将唇24刚性地连接到环34上。此板的下游端部分接合于风扇壳体26的上游端中,并且从其耐磨层38沿轴向延伸。
在此构造中,风扇壳体26具有的轴向尺寸小于上游板42的轴向尺寸,例如,其等于大约风扇叶片轴向尺寸的两倍或三倍。此技术存在多个如前所述的缺点。
本发明通过使风扇壳体向上游沿轴向伸长并与由此使将所述风扇壳体连接到环的法兰沿上游方向错开而使这些问题至少部分地得以解决。
在图2中所示实施例中,风扇壳体126大致延伸到上游板142的上游端,并由此呈现出其轴向尺寸大于所述板的轴向尺寸。在一示例中,此轴向尺寸等于风扇叶片114轴向尺寸的五倍或六倍,因而约为现有技术的两倍长。
风扇壳体126优选地形成为单一件,且其可由复合材料制成。通过举例,其为在申请FR 07/53449中所述的类型。壳体126优选地呈现出局部包围风扇叶片114的额外厚度143,以在此区域中增强壳体。
如现有技术中那样,壳体126的下游端包括法兰128,用于紧固到中间壳体132上。壳体126在其上游端还包括环形法兰130,用于紧固到环134的下游环形法兰144上,环134的上游端利用例如铆钉紧固到空气吸入唇124的内周边。
风扇壳体126因而用于将力从空气吸入唇124传到中间壳体132。
现有技术的横向分隔部36不再必要,可以省略。
上游隔音板142与现有技术的不同之处在于,其为非结构性的,因而重量较轻。不再需要将其紧固到环上。上游隔音板142通过例如熔焊、硬焊、粘接、铆接、螺纹紧固等方式紧固到风扇壳体126的内表面。板142可形成为单一件,或者其可以是分段的。
下游板140和耐磨层138与现有技术中大致相同。在所述示例中,环134包括:大致柱形的紧固到空气吸入唇124的上游端部分,和向下游展开的大致截锥形的下游端部分,且下游端部分在其下游端包括用于紧固到风扇壳体126上的法兰144。板142的上游端接合于环134的截锥形部分中,并与所述部分形状互补。板142的内柱形表面与由环134的上游柱形部分限定的内柱形表面对准。风扇壳体126和环134的法兰130、144相对于引擎纵轴A大致沿径向延伸。
图3至6显示出用于将风扇壳体上游端紧固到连接到空气吸入唇的环的装置的其他变化实施例。
在图3中,环234为柱形,并在其上游端具有法兰244,用于紧固到风扇壳体226的法兰230上。在各法兰之间的接合面与隔音板242的上游端对准,此板的内表面与环的内表面沿轴向对准。
在图4的变例中,环与图3的环大致相同。风扇壳体326包括大致截锥形的上游端部分,其向上游朝向涡轮机轴线会聚;并在其上游端承载用于紧固到环334的法兰344上的法兰330。板342在其上游端呈现出与壳体形状互补的形状,且其内柱形表面与风扇壳体326的上游端部分的内周边对准。
图5中所示的变例与图2的紧固装置的不同之处在于,风扇壳体426的法兰430与环434的法兰444的接合面从隔音板442的上游端沿轴向进一步向下游伸展。
在图6中所示变化实施例中,用于在风扇壳体526与环534之间紧固的法兰530、544相对于涡轮机纵轴大致沿轴向且非径向延伸。环534大致为柱形形状,并在其下游端被风扇壳体526的上游轴向法兰530覆盖。板542的内柱形表面与环534的内表面对准。
Claims (11)
1.一种用于涡轮机(112)的机舱(110)的内壁(120),所述内壁包括:用于包围风扇叶片(114)的外环形风扇壳体(126),所述风扇壳体(126)在其上游端处包括法兰(130)用以紧固与其共轴对准的环(134);和用于从所述风扇叶片向上游延伸的内环形隔音结构(142),其特征在于:
-所述风扇壳体(126)大致延伸至所述隔音结构(142)的上游端,
-所述风扇壳体的上游法兰邻近于所述隔音结构的上游端就位,
-所述环(134)的上游端紧固到所述机舱的空气吸入唇(124)上,以及
-一耐磨材料的环形层(138)紧固到所述风扇壳体(126)的内柱形表面上,并围绕所述风扇叶片。
2.如权利要求1所述的内壁,其特征在于,所述隔音结构(142)通过粘接、熔焊、硬焊、铆接或螺纹紧固而紧固到所述风扇壳体(126)上。
3.如权利要求1所述的内壁,其特征在于,所述环(134)未固定到所述机舱(110)的一外壁上。
4.如权利要求1,2或3所述的内壁,其特征在于,所述风扇壳体(126)的法兰(130)紧固到所述环(134)的法兰上,这些法兰相对于所述涡轮机的纵轴大致沿径向或轴向延伸。
5.如权利要求4所述的内壁,其特征在于,所述法兰(130)的接合面与所述隔音结构(142)的上游端大致沿径向对准。
6.如权利要求4所述的内壁,其特征在于,所述法兰(130)的接合面就位在从所述隔音结构(142)的上游端的上游或下游与所述上游端相距一定距离之处。
7.如权利要求1,2或3所述的内壁,其特征在于,所述隔音结构(142)从所述风扇壳体(126)的上游端沿轴向延伸经过所述壳体的轴向尺寸的仅一部分。
8.如权利要求1,2或3所述的内壁,其特征在于,所述隔音结构(142)由单件的或分段的声学环形板形成。
9.如权利要求1,2或3所述的内壁,其特征在于,所述风扇壳体(126)由复合材料制成。
10.如权利要求1,2或3所述的内壁,其特征在于,在所述耐磨材料的环形层(138)的上游,所述内环形隔音结构限定一上游板(142),该上游板具有平行于所述涡轮机纵轴的轴向尺寸,该轴向尺寸等于所述风扇叶片(114)的轴向尺寸的5或6倍。
11.一种涡轮机(112),其特征在于,其包括机舱(110),所述机舱具有如前述权利要求中任何一项所述的内壁(120)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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FR0804585A FR2935017B1 (fr) | 2008-08-13 | 2008-08-13 | Paroi interne d'une nacelle de turbomachine |
FR08/04585 | 2008-08-13 | ||
PCT/FR2009/000867 WO2010018314A1 (fr) | 2008-08-13 | 2009-07-15 | Paroi interne d'une nacelle de turbomachine |
Publications (2)
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CN102124197A CN102124197A (zh) | 2011-07-13 |
CN102124197B true CN102124197B (zh) | 2014-04-16 |
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CN200980131737.4A Active CN102124197B (zh) | 2008-08-13 | 2009-07-15 | 涡轮机机舱的内壁 |
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US (1) | US8876467B2 (zh) |
EP (1) | EP2318679B1 (zh) |
JP (1) | JP5425908B2 (zh) |
CN (1) | CN102124197B (zh) |
BR (1) | BRPI0917460B1 (zh) |
CA (1) | CA2733094A1 (zh) |
FR (1) | FR2935017B1 (zh) |
RU (1) | RU2011109214A (zh) |
WO (1) | WO2010018314A1 (zh) |
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US9938852B2 (en) | 2014-04-30 | 2018-04-10 | The Boeing Company | Noise attenuating lipskin assembly and methods of assembling the same |
US9708072B2 (en) | 2014-04-30 | 2017-07-18 | The Boeing Company | Aircraft engine nacelle bulkheads and methods of assembling the same |
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FR3033839B1 (fr) * | 2015-03-16 | 2018-09-28 | Safran Aircraft Engines | Ensemble pour turbomachine d'aeronef comprenant un carter de soufflante equipe d'un revetement acoustique integrant un raidisseur de carter de soufflante |
US10830136B2 (en) * | 2015-11-19 | 2020-11-10 | General Electric Company | Fan case for use in a turbofan engine, and method of assembling a turbofan engine |
DE102016105957A1 (de) * | 2016-04-01 | 2017-10-05 | Rolls-Royce Deutschland Ltd & Co Kg | Fangehäuse und Triebwerksbaugruppe mit Fangehäuse |
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US10662813B2 (en) * | 2017-04-13 | 2020-05-26 | General Electric Company | Turbine engine and containment assembly for use in a turbine engine |
GB201809822D0 (en) * | 2018-06-15 | 2018-08-01 | Rolls Royce Plc | Gas turbine engine |
FR3085447B1 (fr) * | 2018-09-04 | 2020-09-11 | Safran Aircraft Engines | Carter de soufflante pour une turbomachine d'aeronef integrant directement des portions abradable et ayant des proprietes acoustiques |
FR3086338B1 (fr) * | 2018-09-20 | 2020-12-25 | Safran Aircraft Engines | Procede de preparation d'un support et de gestion acoustique, sur une turbomachine ou une nacelle |
FR3100834B1 (fr) | 2019-09-12 | 2023-07-07 | Safran Aircraft Engines | Virole annulaire acoustique de turbomachine et procede de fabrication associe |
JPWO2022091542A1 (zh) | 2020-10-30 | 2022-05-05 | ||
FR3128444A1 (fr) * | 2021-10-26 | 2023-04-28 | Airbus Operations (S.A.S.) | Nacelle d’aéronef comprenant une liaison entre des conduits comportant des collerettes orientées vers l’intérieur et aéronef comprenant au moins une telle nacelle |
US20230193827A1 (en) * | 2021-12-21 | 2023-06-22 | Rolls-Royce Deutschland Ltd & Co Kg | Fan case assembly for a gas turbine engine |
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- 2009-07-15 WO PCT/FR2009/000867 patent/WO2010018314A1/fr active Application Filing
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Also Published As
Publication number | Publication date |
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EP2318679B1 (fr) | 2020-09-02 |
JP5425908B2 (ja) | 2014-02-26 |
US20110142615A1 (en) | 2011-06-16 |
EP2318679A1 (fr) | 2011-05-11 |
JP2011530675A (ja) | 2011-12-22 |
WO2010018314A8 (fr) | 2011-02-03 |
US8876467B2 (en) | 2014-11-04 |
BRPI0917460A2 (pt) | 2015-12-01 |
CN102124197A (zh) | 2011-07-13 |
FR2935017B1 (fr) | 2012-11-02 |
CA2733094A1 (fr) | 2010-02-18 |
FR2935017A1 (fr) | 2010-02-19 |
RU2011109214A (ru) | 2012-09-20 |
BRPI0917460B1 (pt) | 2020-03-31 |
WO2010018314A1 (fr) | 2010-02-18 |
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