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    ENSEMBLE PROPULSIF ET PROCEDE D'ALIMENTATION EN ERGOLS
    1.
    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).

    MOTEUR POUR FUSÉE A ALIMENTATION OPTIMISÉE
    2.
    发明公开
    MOTEUR POUR FUSÉE A ALIMENTATION OPTIMISÉE 有权
    具有改进的燃料供应火箭发动机

    公开(公告)号：EP2805039A1

    公开(公告)日：2014-11-26

    申请号：EP13704160.4

    申请日：2013-01-16

    申请人： Snecma

    发明人： SOULIER, Nicolas ,  HAYOUN, David ,  SANNINO, Jean Michel

    IPC分类号： F02K9/48

    CPC分类号： F02K9/46 ,  F02K9/48 ,  F05D2260/601

    摘要： The invention relates to a rocket engine (100), which includes an antechamber and combustion chamber (14), two supply lines (22A, 22B) for the engine, and two turbopumps (20A, 20B). The engine is a staged-combustion engine. A jet pump (102A, 102B) is arranged in at least a first supply line (12A, 12B). After being pressurized, a portion of the fluid circulating in the first supply line is directed towards the jet pump, so as to enable said pump to convey the fluid circulating in said first supply line to the intake of said first pump, thereby increasing the pressure at the supply port of the pump.

    DISPOSITIF DE PRESSURISATION AUTOGÈNE D'UN RÉSERVOIR
    6.
    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）。

    DISPOSITIF DE PRESSURISATION D'UN RESERVOIR D'ERGOL D'UN MOTEUR DE FUSEE
    7.
    发明公开
    DISPOSITIF DE PRESSURISATION D'UN RESERVOIR D'ERGOL D'UN MOTEUR DE FUSEE 有权
    VORRICHTUNG ZUR DRUCKBEAUFSCHLAGUNG EINESTREIBMITTELBEHÄLTERSEINES RAKETENTRIEBWERKS

    公开(公告)号：EP3030776A1

    公开(公告)日：2016-06-15

    申请号：EP14755877.9

    申请日：2014-07-25

    申请人： Snecma

    发明人： ROZ, Gérard ,  HAYOUN, David ,  VUILLAMY, Didier ,  LASSOUDIERE, François

    IPC分类号： F02K9/50

    CPC分类号： F02K9/44 ,  F02K9/425 ,  F02K9/50 ,  F02K9/605 ,  F05D2220/80 ,  F05D2260/20

    摘要： The device comprises a primary heater (58) able to heat the propellant coming from the reservoir (16) before its reintroduction into its reservoir. The primary heater uses the combustion heat of the engine (10) and the device additionally comprises a secondary heater (66) of which the heat source is independent of the operation of the engine, the secondary heater being arranged downstream of the primary heater (58) to heat the propellant between its exit from the primary heater and its reintroduction into the reservoir. The device also comprises means (62) for pressurizing the propellant between the supply of the primary heater (58) and the return of the propellant to the reservoir.

    摘要翻译： 该装置包括适于加热来自罐（16）的推进剂在其再次引入其罐之前的主加热器（58）。 主加热器使用来自发动机（10）的燃烧热，并且该装置还包括具有独立于发动机操作的其热源的次级加热器（66），二次加热器布置在主加热器（58）的下游 ），以便将推进剂在其来自主加热器的出口之间加热并且被重新引入到罐中。 该装置还具有在进给到主加热器（58）的进料和将推进剂返回到罐之间以将推进剂置于压力下的装置（62）。

    DISPOSITIF ET PROCEDE D'ALIMENTATION D'UN MOTEUR-FUSEE
    9.
    发明公开
    DISPOSITIF ET PROCEDE D'ALIMENTATION D'UN MOTEUR-FUSEE 有权
    VERFAHREN UND VORRICHTUNG ZUM ANTREIBEN EINES RAKETENMOTORS

    公开(公告)号：EP2917547A1

    公开(公告)日：2015-09-16

    申请号：EP13803100.0

    申请日：2013-11-04

    申请人： SNECMA

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

    IPC分类号： F02K9/48 ,  F02K9/50

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

    摘要： The invention relates to a device for supplying a propulsion chamber (10) of a rocket motor (100) with a first and a second propellant. According to the invention, a first propulsion chamber (10) supply circuit (16) comprises a turbopump (22) with at least one pump (22a) for pumping the first propellant from a first tank (12) and a turbine (22b) mechanically coupled to said pump (22a). This first supply circuit connects an outlet of the pump to an inlet of the turbine through a heat exchanger (24) that is configured to heat the first propellant using heat generated by the propulsion chamber to drive the turbine. According to the invention, a second supply circuit (18) is configured to supply the propulsion chamber with a second propellant from a second tank (14) which is configured to be pressurized. The invention also relates to a method for supplying a rocket motor propulsion chamber with a first and a second propellant.

    摘要翻译： 本发明涉及一种用于向第一和第二推进剂供给火箭发动机（100）的推力室（10）的进料装置。 根据本发明，推力室（10）的第一进料回路（16）包括涡轮泵（22），其具有至少一个用于从第一罐（12）泵送第一推进剂的泵（22a）和涡轮（ 22b），其机械地联接到所述泵（22a）。 第一进料回路通过热交换器（24）将泵的出口连接到涡轮机的入口，热交换器（24）构造成通过由推力室产生的热量来加热第一推进剂，以便致动涡轮机。 根据本发明，第二进料回路（18）构造成从第二罐（14）向推进室供给第二推进剂，第二罐被构造成被加压。 本发明还提供了一种用第一和第二推进剂进给火箭发动机推进室的方法。