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    Vorrichtung zum Öffnen oder Schließen eines Dichtsitzes eines Ventils
    4.
    发明公开
    Vorrichtung zum Öffnen oder Schließen eines Dichtsitzes eines Ventils 有权
    Vorrichtung zumÖffnenoderSchließeneines Dichtsitzes eines Ventils

    公开(公告)号：EP2829476A1

    公开(公告)日：2015-01-28

    申请号：EP14002532.1

    申请日：2014-07-22

    申请人： Astrium GmbH

    发明人： Kraus, Stephan ,  Maier, Thomas ,  Wolf, Markus

    IPC分类号： B64G1/40 ,  F02K9/44 ,  F16K31/02

    CPC分类号： F16K31/025 ,  B64G1/402 ,  F02K9/58 ,  F03G7/065 ,  F05D2220/60 ,  F05D2300/505 ,  F16K11/048

    摘要： Es wird eine Vorrichtung zum Öffnen oder Schließen eines Dichtsitzes eines Ventils (100) beschrieben, das zur Anordnung in einer Rohrleitung für flüssige oder gasförmige Medien vorgesehen ist, wobei zur einmaligen Ansteuerung des Ventils (100) ein Formgedächtnisaktor (6) vorgesehen ist, der beim Erreichen einer von dessen Legierungszusammensetzung abhängigen Umwandlungstemperatur seine äußere Form sprunghaft ändert, und wobei die Umwandlungstemperatur durch eine steuerbare elektrische Heizvorrichtung (8) der Vorrichtung erzeugbar ist.

    摘要翻译： 用于打开或关闭布置在用于液体或气体介质的管中的阀的密封座的装置包括使用形状记忆致动器仅一次启动阀。 当达到取决于其合金组成的转变温度时，形状记忆致动器会突然改变其外部形状。 转换温度可由装置的可控电加热装置产生。

    EINSPRITZELEMENT
    7.
    发明授权
    EINSPRITZELEMENT 有权
    注射元件

    公开(公告)号：EP1689996B1

    公开(公告)日：2011-01-05

    申请号：EP04802667.8

    申请日：2004-11-03

    申请人： Astrium GmbH

    发明人： MAEDING, Chris, Udo

    IPC分类号： F02K9/52 ,  F02K9/44

    CPC分类号： F02M57/00 ,  F02K9/52 ,  F05D2260/202

    摘要： The invention relates to an injection element (10), especially for a rocket drive. Said injection element comprises an inner and an outer element (12, 14), mounted coaxially thereto, for receiving and injecting fuel into a combustion chamber. According to the invention, the outer element (14) is provided with bores (16) for forming a cooling liquid film layer.

    DISPOSITIF CRYOTECHNIQUE DE PROPULSION DANS L'ESPACE ET SON PROCEDE DE COMMANDE
    8.
    发明公开
    DISPOSITIF CRYOTECHNIQUE DE PROPULSION DANS L'ESPACE ET SON PROCEDE DE COMMANDE 有权
    对于空间推进及其控制方法的低温设备

    公开(公告)号：EP2150694A1

    公开(公告)日：2010-02-10

    申请号：EP08805846.6

    申请日：2008-05-23

    申请人： Centre National d'Etudes Spatiales

    发明人： FORTUNIER, Pascal ,  LEUDIERE, Vincent

    IPC分类号： F02K9/42 ,  F02K9/44 ,  B64G1/40

    CPC分类号： B64G1/401 ,  F02K9/46 ,  F02K9/563 ,  F02K9/94 ,  F02K9/95

    摘要： The device, suitable for intermittent operation, comprises first (1) and second (2) main tanks of first and second liquid cryogenic propellants respectively, fuel and oxidizer respectively, first (3) and second (4) means of vaporizing the first and second liquid propellants respectively, and at least one propulsive combustion chamber (19) fed by the vaporized propellants. According to the invention, the first (3) and second (4) vaporization means are in thermal transfer relation with the combustion chamber (19), the first and second vaporized propellants pass into the first (9) and second (10) compression means respectively, and the gases compressed in these first (9) and second (10) compression means are stored in first (15) and second (16) surge tanks respectively, arranged between the compression means (9, 10) and the combustion chamber (19). Applicable to the top stage of a geostationary satellite launch vehicle.

    ROCKET ENGINE
    10.
    发明公开
    ROCKET ENGINE 有权
    火箭发动机

    公开(公告)号：EP1171705A4

    公开(公告)日：2005-01-12

    申请号：EP00946747

    申请日：2000-03-10

    申请人： WILLIAMS INT CO LLC

    发明人： STEPHENS RICHARD D ,  THOMPSON ROBERT S JR ,  DEFEVER GUIDO J ,  JONES JOHN F ,  MUSGRAVE DEAN S ,  WILLIAMS GREGG G

    IPC分类号： F02K9/50 ,  F02K9/48 ,  F02K9/52 ,  F02K9/56 ,  F02K9/60 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/72 ,  F02K9/97 ,  F02K1/00 ,  F02K9/00 ,  F02K9/44

    CPC分类号： F02K9/52 ,  F02K9/48 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/72 ,  F05D2240/40

    摘要： A rocket engine (10) comprises first (76) and second (142) rotary injectors for injecting respective fuel (20) and oxidizer (18) propellant components into a first combustion chamber (34), and the effluent (38) therefrom drives a turbine (40) that rotates the rotary injectors (76, 142). The mixture within the first combustion chamber (34) is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber (36) with additional oxidizer injected by a third rotary injector (182) so as to generate a high temperature effluent (214) suitable for propulsion. The rotary injectors (76, 142, 182) are adapted with associated rotary pressure traps (86, 146, 174) so as to isolate the low pressure propellant supply (22', 24') from the relatively high pressures in the respective combustion chambers (34, 36). A portion of the fuel-rich effluent from the first combustion chamber (34) is directed through an annular passage (198, 204) surrounding the combustion chambers (34, 36) to provide effusion cooling of a surface (218) of the second combustion chamber (36).