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1. 发明授权

US3965699A Spring compensated radially flexible power takeoff shaft 失效
标题翻译：弹簧补偿径向柔性动力输出轴
公开(公告)号：US3965699A
公开(公告)日：1976-06-29
申请号：US518678
申请日：1974-10-29
申请人： Joseph W. Bracken, Jr.
发明人： Joseph W. Bracken, Jr.
IPC分类号： F16H1/26 , F02C7/36 , F16H57/02 , F16H57/022 , F16H57/028 , F16C1/00
CPC分类号： F16H57/028 , F02C7/36 , F16H2057/02043 , F16H2057/0222 , F16H2057/0225 , Y10T464/50 , Y10T74/19623
摘要： A single shaft gas turbine engine of the type having a shaft assembly including, in axial alignment, a radial turbine element, a central slinger ring element, a radial compressor element, and a geared power takeoff element. The elements of the shaft assembly are interconnected by a tie bolt. An annular combustor liner defines a combustion chamber that encircles the central slinger ring. The shaft assembly is journaled by two bearings which are respectively located outboard of the turbine and on the geared power takeoff element. Each bearing is carried by a tubular support. Each tubular support has a free end carrying the respective bearing and another end secured to the bearing. The ends are spaced and interconnected by circumferentially spaced ribs to provide a flexible support for the prospective bearing. The gear on the power takeoff element drives a larger gear to withdraw power from the engine. A coil spring has one end seated on the housing and another end in contact with the free end of the tubular support carrying the bearing on the geared power takeoff element. The coil spring urges the geared power takeoff element in a radial direction that is opposite to the direction of the operational force exerted by the larger gear on the power takeoff gear. The coil spring is preloaded to exert a force equal to one half of the maximum force exertable by the larger gear on the power takeoff gear and has a spring rate that is relatively small when compared to the spring rate of the tubular support.
摘要翻译：一种单轴燃气涡轮发动机，其具有轴组件，轴组件包括径向涡轮机元件，中心抛油环元件，径向压缩机元件和齿轮传动动力输出元件。轴组件的元件通过连接螺栓相互连接。环形燃烧器衬套限定围绕中央抛油环的燃烧室。轴组件由分别位于涡轮机外侧和齿轮传动动力输出元件上的两个轴承支承。每个轴承由管状支撑件承载。每个管状支撑件具有承载相应轴承的自由端和固定到轴承的另一端。端部通过周向隔开的肋间隔开并互相连接，为预期轴承提供柔性支撑。动力输出元件上的齿轮驱动较大的齿轮以从发动机中撤出动力。螺旋弹簧的一端位于壳体上，另一端与承载轴承的管状支撑件的自由端接触在齿轮传动动力输出元件上。螺旋弹簧在径向方向上推动齿轮传动动力输出元件，该径向方向与由较大齿轮施加在动力输出齿轮上的操作力的方向相反。螺旋弹簧被预加载以施加等于功率输出齿轮上较大齿轮所能施加的最大力的一半的力并且具有与管状支撑件的弹簧刚度相比较小的弹簧刚度。

2. 发明授权

US4318372A Engine intake manifold 失效
标题翻译：发动机进气歧管
公开(公告)号：US4318372A
公开(公告)日：1982-03-09
申请号：US86729
申请日：1979-10-22
申请人： Joseph W. Bracken, Jr. , Edward E. Rahbe
发明人： Joseph W. Bracken, Jr. , Edward E. Rahbe
IPC分类号： F02B3/06 , F02B31/00 , F02M35/10 , F02B75/18
CPC分类号： F02M35/10124 , F02B31/00 , F02M35/10262 , F02M35/112 , F02B3/06 , Y02T10/146
摘要： In a preferred embodiment, a log-type intake manifold for a diesel engine has a longitudinal passage with four equally spaced lateral outlet openings on one side and a centrally disposed inlet opening on the other side of the passage. Similar outlet flow conditions are created in the outlet passages by the addition of at least one flow directing vane at an outlet toward one end of the passage from the inlet to redirect the outlet gas flow into a pattern similar to that of the naturally occurring gas flow patterns at the outlet openings located toward the other end of the passage from the inlet.
摘要翻译：在优选实施例中，用于柴油发动机的对数型进气歧管具有纵向通道，在一侧具有四个等间距的侧向出口和位于通道另一侧的中心设置的入口。在出口通道中产生类似的出口流动条件，其中在出口处从入口向出口的一端添加至少一个导流叶片，以将出口气流重定向成与天然气流相似的图案出口处的图案从入口朝向通道的另一端。

3. 发明授权

US3983694A Cup-shaped fuel slinger 失效
标题翻译：杯形燃油抛油布
公开(公告)号：US3983694A
公开(公告)日：1976-10-05
申请号：US518303
申请日：1974-10-29
申请人： Joseph W. Bracken, Jr.
发明人： Joseph W. Bracken, Jr.
IPC分类号： F02C3/14 , F23D11/06 , F23R3/28 , F23R3/38
CPC分类号： F23D11/06 , F23R3/38
摘要： A generally cup-shaped fuel slinger concentrically secured by its base portion to a rotatable shaft located in a combustion chamber and having a radially inwardly extending lip at its open end provided with a plurality of circumferentially spaced notches opening toward the shaft and spaced at their bottommost portion from the inner annular surface of the slinger side wall. Fuel is delivered by a single tube through the open end of the slinger and is centrifuged outwardly against the inner annular surface of the slinger side wall, and thereafter delivered from the slinger to the combustion chamber through the notches. The slinger is located between a radial turbine and a compressor of a gas turbine engine. The fuel supply tube projects axially through a vane in the diffuser, radially along the diffuser, and then axially into the fuel slinger between the lip and the outer periphery of the adjacent shaft portion. In the disclosed embodiment the notches are generally V-shaped.
摘要翻译：通常其杯形燃料抛油环通过其基部同心地固定到位于燃烧室中的可旋转轴，并且在其开口端具有径向向内延伸的唇缘，其设有多个周向间隔开的开口朝向轴并且在其最底部部分从抛油环侧壁的内环形表面。燃料通过单个管通过抛油环的开口端输送，并且抵靠抛油环侧壁的内环表面向外离心，然后通过凹口从抛油环输送到燃烧室。抛油环位于燃气涡轮发动机的径向涡轮机和压缩机之间。燃料供应管沿着扩散器径向地沿扩散器中的叶片轴向延伸，然后在唇缘和相邻轴部分的外周边之间轴向地进入燃料抛油环。在所公开的实施例中，凹口通常为V形。

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