公开(公告)号：US20130186493A1

公开(公告)日：2013-07-25

申请号：US13357294

申请日：2012-01-24

Applicant: Jim A. Clark ,  Charles W. Whipple, IV

Inventor： Jim A. Clark ,  Charles W. Whipple, IV

IPC: F16K11/00 ,  F16K31/02 ,  F16K1/00 ,  F16L55/00

CPC classification number: F16K47/08 ,  G05D7/0186 ,  Y10T137/86493

Abstract: An apparatus for bi-directionally regulating flow of an actuation fluid includes a conduit and a plurality of baffles. The conduit includes a conduit flow channel that extends longitudinally along a centerline between a first conduit end and a second conduit end. The baffles are sequentially non-coaxially arranged in the conduit. Each of the baffles includes a baffle flow channel that laterally tapers and extends, in a longitudinal direction towards the second conduit end, from a first baffle end to a baffle orifice at a second baffle end. The first baffle end is connected to the conduit, and extends laterally across the conduit flow channel.

Abstract translation: 用于双向调节致动流体的装置包括导管和多个挡板。 导管包括导管流动通道，其沿第一导管端和第二导管端之间的中心线纵向延伸。 挡板顺序地非同轴地布置在导管中。 每个挡板包括挡板流动通道，其在朝向第二管道端部的纵向方向上在第二挡板端处从第一挡板端部到挡板孔口横向渐缩和延伸。 第一挡板端连接到导管，横向延伸穿过导管流动通道。

公开(公告)号：US20130125527A1

公开(公告)日：2013-05-23

申请号：US13300775

申请日：2011-11-21

Applicant: Jim A. Clark ,  Craig W. Irwin ,  Reed A. Kakuska

Inventor： Jim A. Clark ,  Craig W. Irwin ,  Reed A. Kakuska

IPC: F02K9/97

CPC classification number: F02K9/566 ,  F02K9/64 ,  F02K9/972 ,  F15D1/025 ,  F16L55/027 ,  G05D7/0186

Abstract: A rocket engine fluid-flow system includes a pump fluidly interconnecting a fluid source to a combustion chamber. A nozzle is in fluid communication with the combustion chamber and includes coolant tubes fluidly arranged between the pump and the combustion chamber. An orifice has a throat and is fluidly arranged between the pump and the coolant tubes. The orifice has entrance and exit ramps arranged on either side of the throat. The exit ramp has an exit ramp surface with a divergent angle that is less than a right angle. The entrance ramp provides a smooth approach to the orifice throat. In one example, the exit ramp includes an exit ramp surface having a divergent angle of 20-60°. The exit ramp radius is less than twice the throat radius in one example.

Abstract translation: 火箭发动机流体流动系统包括将流体源流体地连接到燃烧室的泵。 喷嘴与燃烧室流体连通，并且包括流体地布置在泵和燃烧室之间的冷却剂管。 孔具有喉部并且流体地布置在泵和冷却剂管之间。 孔口具有设置在喉部两侧的入口和出口斜面。 出口斜坡具有出口斜面，其具有小于直角的发散角。 入口斜坡提供了孔口喉咙平滑的方法。 在一个示例中，出口斜坡包括具有20-60°的发散角的出口斜面。 在一个示例中，出口斜坡半径小于喉部半径的两倍。

公开(公告)号：US06272865B1

公开(公告)日：2001-08-14

申请号：US09303072

申请日：1999-04-30

Applicant: Jim A. Clark ,  Todd M. Neill

Inventor： Jim A. Clark ,  Todd M. Neill

IPC: F02C100

CPC classification number: F23R3/14 ,  F23R3/26 ,  Y02T50/675

Abstract: The effectiveness of a radial inlet air swirler for the fuel nozzle in the combustor of a gas turbine engine is enhanced by reducing the pressure loss associated with compressor discharge air as it enters the combustor cowl. A circumferential uniform feed pressure is created by an aerodynamically contoured projection on the pressure plate supporting the fuel nozzle and a cooperating dynamic swirler scoop at the inlet of the swirler. The increased flow and fuel/air mixing reduces smoke production without adversely affecting combustor or engine performance.

Abstract translation: 通过减少与压缩机排放空气进入燃烧器整流罩相关联的压力损失，燃气轮机的燃烧器中的燃料喷嘴的径向入口空气旋流器的有效性得到提高。 通过在支撑燃料喷嘴的压力板上的空气动力学轮廓投影和在旋流器的入口处配合的动态旋流器勺产生圆周均匀进料压力。 增加的流量和燃料/空气混合减少烟雾产生，而不会对燃烧器或发动机性能产生不利影响。

公开(公告)号：US4991398A

公开(公告)日：1991-02-12

申请号：US296155

申请日：1989-01-12

Applicant: Jim A. Clark ,  James H. Shadowen ,  Thomas L. DuBell

Inventor： Jim A. Clark ,  James H. Shadowen ,  Thomas L. DuBell

IPC: F23R3/28 ,  F23D11/12 ,  F23R3/14 ,  F23R3/16 ,  F23R3/50

CPC classification number: F23R3/14 ,  F23R3/50 ,  Y02T50/675

Abstract: The fuel nozzles in the combustor of a gas turbine engine are concentrically disposed in two tiers about the circumference of the dome and are arranged in a triangular pattern with the air swirl orientation providing an increased intensity of combustion so as to enable a reduction in combustor size and weight while increasing temperature rise and the overall thrust-to-weight ratio of the engine.