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11.发明公开MOYEU DE CARTER D'ÉCHAPPEMENT POUR UNE TURBOMACHINE 有权MOYEU DE CARTER D'ÉCHAPPEMENTPOUR UNE TURBOMACHINE
公开(公告)号：EP2914818A1
公开(公告)日：2015-09-09
申请号：EP13795819.5
申请日：2013-10-22
CPC分类号： F01D25/162 , F01D9/04 , F01D25/243 , F01D25/28
摘要： The invention relates to an exhaust (1) housing (1)hub (2) of a turbomachine, comprising a connecting wall (22) and an inner channel wall (20), the connecting wall (22) connecting the inner channel wall (20) to inner attachment flanges (24), wherein a radial section of the connecting wall (22) is curved and can be formed, as required, as a single component with the inner channel wall (20), the hub also comprising a series of ribs (28) extending radially between the connecting wall (22) and the inner channel wall (20).
摘要翻译： 本发明涉及包括连接壁（22）和内部通道壁（20）的涡轮机的排气（1）外壳（1）轮毂（2），连接壁（22）连接内部通道壁（20） ）连接到内部连接凸缘（24），其中连接壁（22）的径向部分是弯曲的并且可根据需要形成为具有内部通道壁（20）的单个部件，所述毂还包括一系列 在连接壁（22）和内部通道壁（20）之间径向延伸的肋（28）。
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12.发明公开PROCÉDÉ DE RÉALISATION D'UNE BARRIÈRE THERMIQUE DANS UN SYSTÈME MULTICOUCHE DE PROTECTION DE PIÈCE MÉTALLIQUE ET PIÈCE MUNIE D'UN TEL SYSTÈME DE PROTECTION 审中-公开方法用于在多层系统中的热障用于保护金属部分和第二部分与该保护系统
公开(公告)号：EP2683847A1
公开(公告)日：2014-01-15
申请号：EP12712339.6
申请日：2012-03-07
申请人： Snecma Société Anonyme , Centre National de la Recherche Scientifique CNRS , Institut National Polytechnique De Toulouse , Universite Paul Sabatier Toulouse III - Upst III
CPC分类号： F01D25/08 , B05D3/068 , C23C24/082 , C23C28/321 , C23C28/3455 , C23C28/36 , F01D5/288 , Y02T50/67 , Y10T428/12458 , Y10T428/12549
摘要： The present invention aims to produce a metal part equipped with a protective system, in particular for an aircraft engine turbine blade, having an improved thermal barrier in terms of thermal properties, adhesion to the part and resistance to oxidation/corrosion. In order to do this, the process of the invention produces, from particular ceramics, coating layers according to SPS technology in a single step. According to one embodiment, a metal part is produced according to an SPS flash sintering process and comprises a superalloy substrate (22), a metal sublayer (21), a TGO oxide layer (25), and the thermal barrier (23) formed by said process from at least two layers made of ceramic (2a, 2b), which are chemically and thermally compatible. A first ceramic (2a) referred to as an inner ceramic, is capable of having a substantially higher expansion coefficient. The outer ceramic (2b) is capable of having at least a lower thermal conductivity, a substantially higher sintering temperature and/or maximum operating temperature. The thermal barrier (23) has a gradient of composition, of porosity (3) from the metal sublayer (21) to the outer ceramic (2b).
摘要翻译： 一种用于通过在叠加在外壳内的金属部分来PLC机层生产通过快速烧结的保护材料的热处理在生产用于保护由超合金的金属部分的多层系统的热障方法。 该层含有，在一个超合金基材，基于锆的耐火陶瓷中的至少两个层。 的金属部分中产生雅丁到PLC闪光烧结法，包含一个超合金基材，金属子层，TGO氧化物层以及由该方法形成的热屏障。 第一陶瓷是一个内陶瓷设计为具有显着更高的膨胀系数。 外陶瓷被设计成具有至少更低的导热性，和烧结温度或最高工作温度中的至少一个也基本上是较高的。 热障具有从金属子层的外陶瓷的组合物和孔隙率梯度。
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13.发明公开
公开(公告)号：EP2678543A1
公开(公告)日：2014-01-01
申请号：EP12709936.4
申请日：2012-02-17
CPC分类号： B60K25/06 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2220/50
摘要： The invention relates to, in particular, a multi-flow turbojet engine, including an intermediate casing having radial arms and a driveshaft for the gearbox of auxiliary machines of the turbojet engine, said drive shaft being mounted in a radial arm of the intermediate casing, said radial arm of the intermediate casing including an intermediate bearing (110) for supporting the driveshaft, said intermediate bearing (110) including a plurality of bearings (115) for supporting the driveshaft, the driveshaft including a first shaft element (101), which is connected, at one end thereof, to a means for providing mechanical transmission to the turbojet engine, and a second shaft element (102), which is connected, at one end thereof, to a means for providing mechanical transmission to said housing, the first shaft element (101) and the second shaft element (102) being linked by a linkage (105) including a plurality of grooves (107), the turbojet engine being characterized in that a single plane transversely passes through the plurality of grooves (107) and the plurality of bearings (115).
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14.发明授权COMPRESSEUR DE TURBOMACHINE, EN PARTICULIER DE TURBOPROPULSEUR OU DE TURBORÉACTEUR D'AVION 有权涡轮机压缩机，特别是飞机涡轮或飞机涡轮发动机
公开(公告)号：EP3084141B1
公开(公告)日：2018-02-07
申请号：EP14827799.9
申请日：2014-12-04
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/3216 , F05D2220/323 , F05D2240/12
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15.发明公开DISPOSITIF DE PRESSURISATION AUTOGÈNE D'UN RÉSERVOIR 有权DRUCKBEAUFSCHLAGUNGSVORRICHTUNGFÜREIN TREIBSTOFF-RESERVOIR
公开(公告)号：EP3052797A1
公开(公告)日：2016-08-10
申请号：EP14795850.8
申请日：2014-09-18
发明人： ROZ, Gérard , HAYOUN, David , RAVIER, Nicolas
摘要： The invention relates to a propulsion assembly (1, 201) for a rocket, comprising a reservoir (2) configured to contain a propellant, an engine comprising a combustion chamber (9), a propellant supply line (11) that extends between the reservoir (2) and the combustion chamber (9) and on which a sectional valve (24) is positioned, and a heater (15) whereof an inlet is connected to the supply line (11) and an outlet is connected to the reservoir (2). The inlet of the heater comprises an inlet line (13a) connected to the supply line (11) downstream from the sectional valve (24) on the one hand and to a neutral fluid intake (31) on the other hand.
摘要翻译： 一种用于火箭的推进组件（1,201），包括构造成容纳推进剂的罐（2），具有燃烧室（9）的发动机，在所述罐（2）和所述燃烧室之间延伸的推进剂供给管 燃烧室（9）并且具有布置在其中的隔离阀（24），以及具有连接到进料管（11）的入口和连接到罐（2）的出口的加热器（15）。 加热器的入口包括入口管（13a），其首先连接到隔离阀（24）下游的进料管（11），其次连接到中性流体进料（31）。
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公开(公告)号：EP3033495A1
公开(公告)日：2016-06-22
申请号：EP14786954.9
申请日：2014-08-11
CPC分类号： F01D25/246 , F01D9/042 , F05D2220/32 , F05D2230/64 , F05D2240/128 , F05D2240/80 , F05D2260/30 , F05D2260/36
摘要： The invention relates to an assembly which includes: two rotationally symmetrical components (10, 20) for supporting the blades of a turbine engine, arranged one inside the other concentrically about a turbine engine axis, and a system (30) for locking the components (10, 20) such as to prevent the relative translation of same in the axial and radial directions relative to said axis, the system including a slotted ring (40) comprising a U-shaped cross-section suitable for receiving one end of the components (10, 20), the assembly being characterised in that the ring (40) and one of the components (10, 20) are shaped such as to allow the ring to be interlocked on the component, and in that the locking system (30) also includes a member for stopping the rotation of the ring relative to the component with which the latter is interlocked. The invention further relates to a method for assembling such an assembly.
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17.发明公开
公开(公告)号：EP2823150A1
公开(公告)日：2015-01-14
申请号：EP13715272.4
申请日：2013-03-06
发明人： MARIN, Sébastien
CPC分类号： F01D5/20 , F01D5/147 , F01D5/286 , F04D29/324 , F05D2240/303 , F05D2300/133 , Y02T50/672 , Y02T50/673
摘要： The invention proposes a turbomachine rotor blade (10) which comprises a body (12) extending radially and an insert (26) covering the tip (16) of the body (12), the insert (26) being made up of a first portion (28) radially covering the tip (16) of the blade (10) and of a second portion (30) partially covering the pressure face (22) of the blade (10), characterized in that the cross section of the insert (26) on a plane that is radial with respect to the axis of the rotor is in the shape of an angle bracket with the first portion (28) of the insert (26) running tangentially with respect to the main axis of the rotor and the second portion (30) running radially overall with respect to the main axis of the rotor.
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18.发明授权
公开(公告)号：EP2914818B1
公开(公告)日：2017-06-21
申请号：EP13795819
申请日：2013-10-22
CPC分类号： F01D25/162 , F01D9/04 , F01D25/243 , F01D25/28
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19.发明公开COMPRESSEUR DE TURBOMACHINE, EN PARTICULIER DE TURBOPROPULSEUR OU DE TURBORÉACTEUR D'AVION 有权涡轮发动机压气机，特别是飞机涡轮增压发动机或大衣动力发动机
公开(公告)号：EP3084141A1
公开(公告)日：2016-10-26
申请号：EP14827799.9
申请日：2014-12-04
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/3216 , F05D2220/323 , F05D2240/12
摘要： The invention relates to a turbine engine compressor, in particular of an aeroplane turboprop or turbofan, including a stator comprising an annular casing and at least one annular row of variable-pitch vanes, each vane comprising a radially external end including a pivot mounted in an opening of the casing and connected by a linking member to a control ring (38) capable of pivoting axially relative to the casing, the linking member comprising a first end attached to the pivot of the vane and a second end comprising a pin inserted in a hole (52, 58) of the control ring (38), characterised in that at least one (58) of the holes (52, 58) of the control ring (38), which is used for inserting the pins of the linking members, has an oblong shape and extends in the circumferential direction such as to enable the pin to move into said oblong hole (58), during the rotation of the control ring (38).
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公开(公告)号：EP3004864A1
公开(公告)日：2016-04-13
申请号：EP14731705.1
申请日：2014-05-22
CPC分类号： G01H1/003 , G01N29/11 , G01N29/44 , G01N29/4463 , G01N2291/0231 , G01N2291/0289 , G01N2291/044 , G01N2291/048
摘要： The invention relates to a method for inspecting an object by means of ultrasound transmission, comprising the steps consisting in: sweeping an ultrasound beam over a reference part that has the same geometry as the object to be inspected, and measuring the amplitude (1100) transmitted through the part in order to obtain (1200) a mapping thereof, the ultrasound beam being amplified with a reference gain; determining (1300) gain corrections to be added to the reference gain at certain points during the sweeping of the reference part in order to obtain an ultrasound beam amplitude transmitted through the part which is constant at each point of the mapping; and sweeping an ultrasound beam over the object to be inspected and measuring the transmitted amplitude (2100), the gain applied to the various points during the sweeping corresponding to the reference gain corrected on the basis of said corrections.
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