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31. 发明公开

EP2715100A1 SYSTÈME DE RÉDUCTION DE LA DYNAMIQUE DU SEGMENT MOBILE D'UNE TUYÈRE DÉPLOYABLE POUR MOTEUR DE FUSÉE 有权转让
标题翻译：系统，以减少移动部分的可伸展火箭发动机喷管的动力学
公开(公告)号：EP2715100A1
公开(公告)日：2014-04-09
申请号：EP12728699.5
申请日：2012-05-15
申请人： SNECMA
发明人： DAVID, Noël , PYRE, Alain
IPC分类号： F02K9/97
CPC分类号： F02K9/976 , F05D2260/96 , F05D2300/433 , F05D2300/614
摘要： Deployable nozzle for a rocket motor, comprising at least one fixed divergent segment (12) and one mobile divergent segment (14) coaxial with the fixed divergent segment (12) and able to move along the fixed divergent segment (12) from a withdrawn position to a deployed position, said deployable nozzle being characterized in that it further comprises a transverse stiffener (16) which is tension preloaded and extends transversely to the mobile divergent segment (14), near a downstream end (14b) of the mobile divergent segment (14), between at least two points on the periphery of an interior wall of the mobile divergent segment (14).

32. 发明公开

EP2627809A2 PROCEDE DE FABRICATION D'UNE STRUCTURE FIBREUSE METALLIQUE PAR TISSAGE 有权转让
标题翻译： VERFAHREN ZUR HERSTELLUNG EINER METALLFASERSTRUKTUR DURCH WEBEN
公开(公告)号：EP2627809A2
公开(公告)日：2013-08-21
申请号：EP11832091.0
申请日：2011-10-10
申请人： Snecma
发明人： GODON, Thierry , DAMBRINE, Bruno , PERROUX, Alain
IPC分类号： D03D13/00 , D03D15/02 , D03D23/00 , D03D25/00 , B64C11/20 , F04D29/38 , B64C11/26 , F04D29/32
CPC分类号： D03D15/02 , B21F27/128 , B64C11/26 , D03D13/00 , D03D23/00 , D03D25/005 , D10B2101/20 , D10B2505/02 , F01D5/147 , F04D29/023 , F04D29/324 , F05D2240/303 , F05D2300/133 , F05D2300/2261 , F05D2300/614 , Y02T50/66 , Y10T29/49321
摘要： The invention relates to a method (200) for the production of a fibrous metal structure (100) by means of weaving with metal weft yarns and metal warp yarns. The invention is characterised in that it includes a step comprising the weaving of the fibrous structure (100) by means of the successive weaving of metal clasps (301') that are used as weft yarns. For the purpose of weaving, each of the arms (302, 303) of each of the metal clasps (301') is introduced into at least one shed, each shed being formed by two warp yarns.
摘要翻译：一种用金属纬纱和金属经纱编织生产纤维金属结构的方法。该方法包括通过连续编织用作纬纱的金属扣来编织纤维结构。为了编织的目的，每个金属扣的每个臂被引入至少一个棚，每个棚由两根经纱形成。

33. 发明授权

EP2387497B1 PROCEDE DE FABRICATION D'UNE AUBE DE TURBOMACHINE 有权转让
标题翻译：制造方法涡轮叶片
公开(公告)号：EP2387497B1
公开(公告)日：2013-06-26
申请号：EP09805732.6
申请日：2009-12-17
申请人： Snecma
发明人： MAHIEU, Jean, Noël , ROMERO, Jean-Louis
IPC分类号： B29C70/54 , B29C70/24 , B29B11/16 , F01D5/28 , B29L31/08 , D03D25/00
CPC分类号： B29C70/24 , B29B11/16 , B29C70/48 , B29C70/545 , B29L2031/08 , D03D25/005 , F01D5/282 , F05D2300/44 , F05D2300/614

34. 发明公开

EP2284362A3 Triebwerkswelle in hybrider Bauweise 审中-公开
标题翻译：在混合设计发动机轴
公开(公告)号：EP2284362A3
公开(公告)日：2013-03-06
申请号：EP10007922.7
申请日：2010-07-29
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Schreiber, Karl
IPC分类号： F01D5/02 , F01D5/28
CPC分类号： F01D5/02 , F01D5/282 , F05D2230/239 , F05D2300/224 , F05D2300/603 , F05D2300/614 , F16C3/026 , F16C2360/23 , Y02T50/672 , Y10T403/65
摘要： Bei einer Triebwerkswelle in hybrider Bauweise mit an den Enden eines Faserverbundkunststoffrohres (2) befestigtem, außen verzahnten Kraftübertragungselement (3) ist das Kraftübertragungselement zweiteilig ausgebildet und umfasst ein aus einem Stahl bestimmter Härte bestehendes Verzahnungsteil (5) sowie ein stirnseitig mit diesem verschweißtes, sich verjüngendes und zur Ausbildung einer geschäfteten Verbindung von dem Faserverbundmaterial umschlossenes Adapterteil (7), dessen Wärmeausdehnung etwa gleich dem Ausdehnungsverhalten des Faserverbundmaterials ist. Dadurch ist auch bei hohen Temperaturen eine feste Verbindung zwischen dem Faserverbundmaterial und dem Kraftübertragungselement und eine Übertragung hoher Kräfte möglich. (Fig.)

35. 发明授权

EP1674245B1 Method for fabricating reinforced composite materials with low porosity 有权
标题翻译：一种用于生产强化复合材料具有低Pörosität过程
公开(公告)号：EP1674245B1
公开(公告)日：2012-11-28
申请号：EP05257696.4
申请日：2005-12-15
申请人： GENERAL ELECTRIC COMPANY
发明人： Blanton, Lee Alan , Fairbanks, Robert Paul , Price, Richard Thomas , Ronk, Warren Rosal , Meibers, Gregory Joseph , Whiteker, Stephen Mark , Buczek, Matthew Bernard
IPC分类号： B29C70/46 , B29C70/44 , B29C70/54 , F01D21/04
CPC分类号： B29C70/546 , B29C70/44 , B29C70/465 , B29L2031/7504 , F01D21/045 , F05D2300/614 , F05D2300/702 , Y02T50/672 , Y10T428/249928 , Y10T428/249933 , Y10T428/24994 , Y10T428/249944

36. 发明公开

EP2489837A1 Drosseleinsatz für Turbinenschaufel und zugehörige Turbinenschaufel 审中-公开
标题翻译： DurbseleinsatzfürTurbinenschaufel undzugehörigeTurbinenschaufel
公开(公告)号：EP2489837A1
公开(公告)日：2012-08-22
申请号：EP11154936.6
申请日：2011-02-18
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Ahmad, Fathi , Eßer, Winfried , Gaio, Giuseppe , Heckel, Waldemar , Küperkoch, Rudolf , Lüsebrink, Oliver , Mattheis, Thorsten , Milazar, Mirko , Mol, Artur , Paul, Uwe , Ricken, Oliver , Schneider, Oliver
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2240/122 , F05D2240/304 , F05D2300/614
摘要： Die Erfindung betrifft einen Drosseleinsatz zum Unterteilen eines kühlmitteldurchströmten Hohlraums einer Turbinenschaufel in zwei Teilräume, wobei der Hohlraum durch Schaufelwandungen der Turbinenschaufel begrenzt ist, und wobei der Drosseleinsatz ein Drosselblech mit Durchführungen aufweist, deren Gesamtgröße eine Drosselleistung des Kühlmittelstroms zwischen den Teilräumen bestimmt. Erfindungsgemäß sind an Randbereichen des Drosselblechs flexible Dichtelemente zum Abdichten angebracht.
摘要翻译：插入件具有节流板（B），其具有通道（D），其尺寸确定隔室之间的冷却剂流的节流性能。柔性密封元件设计为可密封地连接在节流板边缘区域的金属棉（A）。翼型叶片壁（W1，W2）形成用于引导冷却剂流的中空室，其中中空室由涡轮叶片的叶片壁结合。引导元件（S1，S2）以使得插入件通过柔性密封元件紧密附接的方式设计。还包括用于燃气轮机的涡轮叶片的独立权利要求。

37. 发明公开

EP2447476A2 Annulus filler for a rotor disk of a gas turbine 无效转让
标题翻译： RingförmigesZwischenstückfüreine Rotorscheibe einer Gurburbine
公开(公告)号：EP2447476A2
公开(公告)日：2012-05-02
申请号：EP11184582.2
申请日：2011-10-11
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F01D11/00
CPC分类号： F02C7/05 , F01D11/008 , F05D2220/36 , F05D2250/75 , F05D2260/30 , F05D2300/173 , F05D2300/603 , F05D2300/614 , Y02T50/672
摘要： An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion which defines an airflow surface for air being drawn through the engine. The annulus filler further has a front attachment formation which connects a forward end of the body portion to the rotor disc and which allows rotational movement of the body portion thereabout. The annulus filler further has a rear attachment formation which connects a rearward end of the body portion to the rotor disc. The rear attachment formation comprises a spring element which extends between the body portion and the rotor disc. The spring element expands under operational centrifugal loading such that the rearward end of the body portion moves radially outwardly with the body portion rotating about the front attachment formation.
摘要翻译：提供了一种环形填料，用于安装到燃气涡轮发动机的转子盘，并用于桥接附接到转子盘的两个相邻叶片之间的间隙。环形填料具有主体部分，其限定用于空气被吸入发动机的气流表面。环形填料还具有将本体部分的前端与转子盘连接并允许主体部分在其周围的旋转运动的前附接结构。环形填料还具有将主体部分的后端连接到转子盘的后连接结构。后附接结构包括在主体部分和转子盘之间延伸的弹簧元件。弹簧元件在操作的离心载荷下膨胀，使得主体部分的后端径向向外移动，主体部分围绕前附接结构旋转。

38. 发明公开

EP2439394A1 Improved thermal insulation of rocket engines 审中-公开
标题翻译： VerbesserteWärmedämmungvon Raketentriebwerken
公开(公告)号：EP2439394A1
公开(公告)日：2012-04-11
申请号：EP10187147.3
申请日：2010-10-11
申请人： Nammo Raufoss AS
发明人： Ørbekk, Erland
IPC分类号： F02K9/34 , F02K9/62 , F02K9/97
CPC分类号： F02K1/822 , F02K9/346 , F02K9/62 , F02K9/974 , F05D2300/603 , F05D2300/614
摘要： The present invention is related to an improved thermal insulation of an exhaust tube (8) for use in a rocket engine. The thermal insulation is provided for as a layered structure wherein respective layers comprises a composite material, and wherein dominant directions of fibres in respective adjacent layers are different with respect to each other. In addition, a flexible layer might be used to attach the thermal insulation to an inner wall of the exhaust tube (8).
摘要翻译：本发明涉及一种用于火箭发动机的排气管（8）的改进的热绝缘。提供隔热层作为分层结构，其中各层包括复合材料，并且其中各相邻层中的纤维的主要方向相对于彼此是不同的。此外，可以使用柔性层将隔热件附接到排气管（8）的内壁。

39. 发明公开

EP2387497A1 PROCEDE DE FABRICATION D'UNE AUBE DE TURBOMACHINE 有权转让
标题翻译：制造方法涡轮叶片
公开(公告)号：EP2387497A1
公开(公告)日：2011-11-23
申请号：EP09805732.6
申请日：2009-12-17
申请人： Snecma
发明人： MAHIEU, Jean, Noël , ROMERO, Jean-Louis
IPC分类号： B29C70/54 , B29B11/16 , F01D5/28 , B29L31/08
CPC分类号： B29C70/24 , B29B11/16 , B29C70/48 , B29C70/545 , B29L2031/08 , D03D25/005 , F01D5/282 , F05D2300/44 , F05D2300/614
摘要： The invention relates to the manufacture of a vane by 3D weaving a preform to be impregnated with resin. According to the invention, the visibility of the cut ends of some yarns of the preform (16) is accentuated, for example the warp yarns, to reveal curved lines (20), and the configuration of said curved lines is compared with a reference configuration to ensure correct the shaping of the preform.

40. 发明授权

EP1669547B1 Composite aerofoil 有权
标题翻译：复合刀片
公开(公告)号：EP1669547B1
公开(公告)日：2011-09-28
申请号：EP05256747.6
申请日：2005-11-01
申请人： Rolls-Royce plc
发明人： McMillan, Alison Jane
IPC分类号： F01D5/28 , F01D5/14 , B29C70/02 , B29C70/08 , B29C70/30 , B29C70/34 , B64C3/24 , B64C27/473 , F03D1/06
CPC分类号： B29C70/222 , B29C70/865 , B29D99/0028 , B29L2031/08 , D03D25/005 , F01D5/147 , F01D5/282 , F05C2201/025 , F05D2230/60 , F05D2240/301 , F05D2250/20 , F05D2250/293 , F05D2300/2261 , F05D2300/2283 , F05D2300/44 , F05D2300/603 , F05D2300/612 , F05D2300/614 , Y02E10/721 , Y02T50/43 , Y02T50/672 , Y02T50/673 , Y10T442/20 , Y10T442/2975 , Y10T442/3195
摘要： A composite blade (26) comprises a three-dimensional arrangement of reinforcing fibres (58) and a matrix material (60) infiltrated around the three-dimensional arrangement of woven reinforcing fibres (60). The three-dimensional arrangement of woven reinforcing fibres (58) defines a plurality of cavities (56) within the aerofoil (28). The composite blade (26) comprises an aerofoil portion (38) and a root portion (36). The aerofoil portion (38) comprises a leading edge (44), a trailing edge (46), a concave pressure surface wall (50), a convex suction surface wall (52) and a tip (48). The aerofoil portion (36) comprises a plurality of webs (54) extending between, and being secured to, the concave pressure surface wall (50) and the convex suction surface wall (52) to produce a Warren girder structure. The three-dimensional arrangement of woven reinforcing fibres (58) are arranged to produce the concave pressure surface wall (50), the convex suction surface wall (52) and the plurality of webs (54). The matrix material (60) is an organic resin and the reinforcing fibres (58) comprise carbon fibres.

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