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    • 6. 发明授权
    • Method and apparatus for determining flow characteristics within a well
    • 用于确定井内流量特性的方法和装置
    • US4507552A
    • 1985-03-26
    • US410276
    • 1982-08-23
    • Raymond E. RoesnerMark L. Sloan
    • Raymond E. RoesnerMark L. Sloan
    • E21B47/10G01V5/00
    • E21B47/1015
    • In the representative embodiments of the new and improved methods and apparatus disclosed herein, a well logging instrument includes an elongated body member having a funnel configuration fluid collector mounted thereon. An aperture in the body member, proximate the apex of the collector, allows discharge of the fluid through a passage in the body member, past a pair of radiation detectors, thereafter returning into the well. A tracer ejector valve assembly is mounted proximate the apex of the funnel and the aperture therein for selectively injecting a quantity of radioactive tracer element into the fluid flow. The tracer element is detected by the pair of detectors with the signals provided therefrom used to determine flow characteristics of the fluids within the well.
    • 在本文公开的新的和改进的方法和装置的代表性实施例中,测井仪器包括细长的主体构件,其具有安装在其上的漏斗形流体收集器。 身体构件中的靠近收集器顶点的孔允许流体通过身体构件中的通道排出,经过一对辐射检测器,然后返回到井中。 示踪剂排出阀组件安装在漏斗的顶点附近,并且其中的孔用于选择性地将一定量的放射性示踪元件注入到流体流中。 示踪元件由一对检测器检测,其中提供的信号用于确定井内的流体的流动特性。
    • 9. 发明授权
    • Payload chamber cooling system
    • 有效载荷室冷却系统
    • US6027072A
    • 2000-02-22
    • US129594
    • 1998-08-05
    • Richard A. BlackMark L. SloanSteven R. Overton
    • Richard A. BlackMark L. SloanSteven R. Overton
    • B64G1/00F28F3/12F28F13/02B64D11/00B64C1/00F28F1/00
    • F28F9/0265B64G1/002F28F13/02F28F3/12
    • A cooling system (18) for supplying an even distribution of cooling air within a payload chamber (14) of a launch vehicle is disclosed. The cooling system (18) includes an elongate duct (20), a diverter (22), and a plurality of partitions (24a, 24b, 24c . . . ). The diverter (22) is attached to a distal end (21) of the elongate duct (20) by the plurality of partitions (24a, 24b, 24c . . . ). A turning vane (26) integral with two of the plurality of partitions (24a, 24b, 24c . . . ) extends into the elongate duct (20) dividing part of the elongate duct (20) into two separate halves. Cooling air passes through the elongate duct (20) and strikes the diverter (22) which evenly distributes the cooling air within the payload chamber (14) of the launch vehicle.
    • 公开了一种用于在运载火箭的有效载荷室(14)内提供均匀分布的冷却空气的冷却系统(18)。 冷却系统(18)包括细长管道(20),转向器(22)和多个隔板(24a,24b,24c ...)。 分流器(22)通过多个隔板(24a,24b,24c ...)附接到细长导管(20)的远端(21)。 与多个隔板中的两个(24a,24b,24c ...)成一体的转动叶片(26)延伸到细长管道(20)中,将细长管道(20)的一部分分成两个分开的两半。 冷却空气通过细长管道(20)并撞击分配器(22),该分配器将冷却空气均匀地分布在运载火箭的有效载荷室(14)内。