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21 条记录 (耗时 0.012 秒)

    ENSEMBLE PROPULSIF POUR AÉRONEF
    1.
    发明公开
    ENSEMBLE PROPULSIF POUR AÉRONEF 审中-公开
    驱动单元一种平面

    公开(公告)号：EP2931607A1

    公开(公告)日：2015-10-21

    申请号：EP13820811.1

    申请日：2013-12-12

    申请人： Aircelle ,  Snecma Société Anonyme

    发明人： BOILEAU, Patrick ,  CARUEL, Pierre ,  ANCUTA, Carmen ,  BEUTIN, Bruno

    IPC分类号： B64D29/08

    摘要： The invention relates to a propulsion unit (1) for an aircraft, including: a turbofan (7); a nacelle (2) surrounding the turbofan (7), including an inner structure (17) surrounding a downstream compartment of the turbofan (7), consisting of two annular half-portions (19a, 19b); and means (27, 29) for moving said half-portions, which include a rail/guide unit and are shaped such as to move the half-portion (19a, 19b) between a working position and a maintenance position. The propulsion unit according to the invention is characterised in that the rail/guide unit (27) is shaped such as to space the half-portion (19a, 19b) radially relative to a longitudinal axis of the nacelle, during a translation movement of the half-portion (19a, 19b) and in that the moving means include at least one connecting rod (29) which is connected to the half-portion (19a, 19b) and to the turbofan (7) and which is shaped such as to rotate the half-portion about said rail (37).

    PALIER A DOUBLE PRECHARGE INTERNE
    3.
    发明公开
    PALIER A DOUBLE PRECHARGE INTERNE 有权
    LAGER MIT DOPPELTER INTERNER VORSPANNUNG

    公开(公告)号：EP2978984A1

    公开(公告)日：2016-02-03

    申请号：EP14717156.5

    申请日：2014-03-18

    申请人： Snecma Société Anonyme

    发明人： BOUFFLERT, Sébastien ,  BOURDIN, Philippe ,  LEMAITRE, Alban ,  TESSIER, Fabien

    IPC分类号： F16C33/60 ,  F16C25/08 ,  F16C19/16 ,  F16C19/52

    CPC分类号： F16C25/083 ,  F16C19/06 ,  F16C19/163 ,  F16C33/60

    摘要： In a bearing for rotary machine comprising an inner ring (102), an outer ring (114A, 114B) and rolling elements (110) between the two, one of these inner and outer rings comprises first (114A) and second (114B) half-rings which can be clamped in the axial direction between a thrust member (118) and a first preload system (120) applying a first predetermined axial force, and a second preload system (126) is provided, this being inserted in the axial direction between the first and second half-rings and applying a second predetermined axial force lower than the first predetermined axial force.

    摘要翻译： 在包括内圈，外圈和它们之间的滚动元件的旋转机械轴承中，内环和外环中的一个包括第一和第二半环，其适于在推力构件和第一预制件之间沿轴向夹紧 并且提供第二预加载系统，所述第二预加载系统在轴向方向上插入在第一和第二半环之间并且施加小于第一预定轴向力的第二预定轴向力。

    DISPOSITIF DE PRESSURISATION AUTOGÈNE D'UN RÉSERVOIR
    8.
    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

    申请人： Snecma Société Anonyme

    发明人： ROZ, Gérard ,  HAYOUN, David ,  RAVIER, Nicolas

    IPC分类号： F02K9/50 ,  F02K9/94

    CPC分类号： F02K9/425 ,  F02K9/44 ,  F02K9/50 ,  F02K9/94

    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）。

    AMELIORATION POUR LE VERROUILLAGE DE PIECES DE SUPPORT D'AUBAGE
    9.
    发明公开
    AMELIORATION POUR LE VERROUILLAGE DE PIECES DE SUPPORT D'AUBAGE 审中-公开
    改进刀片磨损组件的锁定

    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

    申请人： Snecma Société Anonyme

    发明人： ROSSET, Patrice Jean-Marc ,  GUERARD, Coralie ,  CONDAT, Hélène ,  PRESTEL, Sébatien

    IPC分类号： F01D9/04 ,  F01D25/24

    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.

    AUBE DE TURBOMACHINE COMPORTANT UN INSERT DE PROTECTION DE LA TETE DE L'AUBE
    10.
    发明公开
    AUBE DE TURBOMACHINE COMPORTANT UN INSERT DE PROTECTION DE LA TETE DE L'AUBE 有权
    机采用涡轮用来保护瓢勺TOP

    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

    申请人： Snecma Société Anonyme

    发明人： MARIN, Sébastien

    IPC分类号： F01D5/14 ,  F01D5/20 ,  F01D5/28

    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.