公开(公告)号：US06457306B1

公开(公告)日：2002-10-01

申请号：US09712778

申请日：2000-11-13

申请人： Terry M. Abel ,  Thomas A. Velez

发明人： Terry M. Abel ,  Thomas A. Velez

IPC分类号： F02K946

CPC分类号： F02K9/46 ,  B64G1/002 ,  B64G1/401 ,  B64G1/402

摘要： A liquid propellant supply system (10) according to the invention is electrical in nature and avoids the need for a gas generator and a turbine assembly. In particular, the system (10) includes an electrical power source (12), a controller (14) and a motor (18) for driving the pump (20). The electrical power source (12) provides electrical power sufficient for high power, limited duration applications such as for launch vehicle applications. For launch vehicle applications, the power source (12) is preferably capable of providing very high power for at least 60 seconds. A number of different types of electrical power sources may be employed in this regard. For example, the power source (12) may include high energy density batteries, supercapacitors, or counter rotating flywheels. Multiple counter rotating motors may be employed in order to minimize precessional forces. The invention thereby eliminates problematic high pressure plumbing, reduces overall mass and allows for convenient mass flow rate throttling, as well as safe abort options.

摘要翻译： 根据本发明的液体推进剂供应系统（10）本质上是电气的，并且避免了对气体发生器和涡轮机组件的需要。 特别地，系统（10）包括用于驱动泵（20）的电源（12），控制器（14）和马达（18）。 电源（12）提供足够用于高功率，有限持续时间的应用的电力，例如用于运载火箭应用。 对于运载火箭应用，电源（12）优选能够提供非常高的功率至少60秒。 在这方面可以采用多种不同类型的电源。 例如，电源（12）可以包括高能量密度电池，超级电容器或反向旋转飞轮。 可以采用多个反转电动机，以便最小化进动力。 因此，本发明消除了有问题的高压管道，降低了整体质量并且允许方便的质量流量节流以及安全的中止选项。

公开(公告)号：US06834493B2

公开(公告)日：2004-12-28

申请号：US10196055

申请日：2002-07-17

申请人： Tomoyuki Hashimoto ,  Mitsuo Watanabe ,  Takeshi Kanda ,  Satoshi Hasegawa ,  Kenji Kudo ,  Athuo Murakami ,  Kouichiro Tani

发明人： Tomoyuki Hashimoto ,  Mitsuo Watanabe ,  Takeshi Kanda ,  Satoshi Hasegawa ,  Kenji Kudo ,  Athuo Murakami ,  Kouichiro Tani

IPC分类号： F02K946

CPC分类号： F04D29/669 ,  F02K9/46

摘要： Cavitation is reduced in a rotary pump while the pump performance is maintained by utilizing a low-temperature fluid source already present in the pump system. The fluid from the low-temperature fluid source receives heat from the fluid flowing to the pump, thereby lowering its temperature and the saturated vapor pressure, which increases the allowable margin for a decrease in fluid pressure and reduces the occurrence of cavitation. The pump system may be used for a liquid rocket engine. The fluid velocity of the fluid directed to the pump is low before releasing heat, so there is only a slight pressure loss at the pump. Accordingly, the temperature is lowered and the occurrence of cavitation is reduced within the pump.

摘要翻译： 通过利用已经存在于泵系统中的低温流体源来维持泵性能，旋转泵中的气蚀减小。 来自低温流体源的流体从流动到泵的流体接收热量，从而降低其温度和饱和蒸气压，这增加了流体压力降低的允许余量并减少了空化现象。 泵系统可用于液体火箭发动机。 在释放热量之前，引导到泵的流体的流体速度低，因此在泵处仅有轻微的压力损失。 因此，降低了温度，并且在泵内发生了气穴。

公开(公告)号：US06499288B1

公开(公告)日：2002-12-31

申请号：US09878293

申请日：2001-06-12

申请人： Andrew F. Knight

发明人： Andrew F. Knight

IPC分类号： F02K946

CPC分类号： F02K9/56 ,  F02K9/50

摘要： The present invention provides for a pressurizer for pressurizing a fluid, comprising a pressurant entrance for the introduction of a pressurant, a fluid entrance for the fluid, a fluid exit for the fluid, and a transfer chamber movable in a cycle with respect to the fluid exit, where for a portion of a cycle the pressurant exerts a force on the fluid inside the transfer chamber. In a preferred aspect of the present invention, the pressurizer further comprises a spindle housing more than one transfer chamber, rotatable about an axis between the fluid entrance and the fluid exit. In another preferred aspect, the transfer chamber comprises either a flexible membrane or a movable piston to separate the pressurant and the fluid.

摘要翻译： 本发明提供了一种用于加压流体的加压器，包括用于引入加压剂的加压入口，用于流体的流体入口，用于流体的流体出口以及可相对于流体循环移动的传送室 出口，其中对于循环的一部分，压力对传送室内的流体施加力。 在本发明的优选方面，加压器还包括主轴，其容纳多于一个传送室，可围绕流体入口和流体出口之间的轴线旋转。 在另一个优选的方面，传送室包括柔性膜或可移动活塞以分离压力和流体。