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21 条记录 (耗时 0.015 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。

    ENSEMBLE PROPULSIF ET PROCEDE D'ALIMENTATION EN ERGOLS
    8.
    发明公开
    ENSEMBLE PROPULSIF ET PROCEDE D'ALIMENTATION EN ERGOLS 审中-公开
    驱动装置和方法供应发泡剂

    公开(公告)号：EP3066330A1

    公开(公告)日：2016-09-14

    申请号：EP14809465.9

    申请日：2014-11-05

    申请人： Snecma Société Anonyme

    发明人： DANGUY, François ,  HAYOUN, David ,  SANNINO, Jean Michel

    IPC分类号： F02K9/48 ,  F02K9/50 ,  F02K9/64 ,  F02K9/97

    CPC分类号： F02K9/425 ,  F02K9/48 ,  F02K9/50 ,  F02K9/64 ,  F02K9/972

    摘要： The invention relates to the field of rocket engines, and specifically to a propulsion assembly (10) including a first tank (11), for a first liquid propellant, a second tank (12), for a second liquid propellant, a pressurisation device (60) configured to maintain a substantially higher pressure in the second tank (12) than in the first tank (11), and a single-shaft turbopump (30), including a turbine (33), a first pump (31) and a second pump (32). The turbine (33) is actuated by the expansion of the first propellant after passing through a regenerative heat exchanger (44), and in turn actuates, via the single rotary shaft (34) of the turbopump (30), said first and second pumps (31, 32), pumping said first and second propellants, respectively, in order to supply a thrust chamber (40).