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    • 2. 发明授权
    • Engine for aeronautical applications
    • 发动机用于航空应用
    • US06789522B2
    • 2004-09-14
    • US10201814
    • 2002-07-23
    • John Seymour
    • John Seymour
    • F02B7700
    • F02B61/04F01M2011/0058F02B67/04F02B75/22Y10T74/2122
    • The present invention provides an improved engine for aeronautical applications which includes a core engine block having a drive shaft rotatably mounted within the core engine block and a motive device for rotating the drive shaft. A propeller speed reduction unit is connected to the drive shaft for transferring power from the drive shaft to a propeller and an accessory drive gearbox is connected to the drive shaft for transferring power from the drive shaft to at least one accessory device. The accessory drive gearbox includes an accessory drive crank gear connected to the drive shaft and a drive gear intermeshing with the crank gear. Finally, at least two inter-module dampers are mounted in the engine, one each of the inter-module dampers positioned between the core engine block and the accessory drive gearbox and the core engine block and the propeller speed reduction unit to dampen and isolate vibrations.
    • 本发明提供了一种用于航空应用的改进的发动机,其包括具有可旋转地安装在所述核心发动机缸体内的驱动轴的核心发动机缸体和用于旋转所述驱动轴的动力装置。 螺旋桨减速单元连接到用于将动力从驱动轴传递到螺旋桨的驱动轴,附件驱动齿轮箱连接到用于将动力从驱动轴传递到至少一个附件装置的驱动轴。 附件驱动齿轮箱包括连接到驱动轴的辅助驱动曲柄齿轮和与曲柄齿轮啮合的驱动齿轮。 最后,至少两个模块间阻尼器安装在发动机中,每个模块间阻尼器位于核心发动机缸体和附件驱动齿轮箱之间,并且核心发动机缸体和螺旋桨减速单元以抑制和隔离振动 。
    • 3. 发明申请
    • Illumination system for a printing press
    • 印刷机照明系统
    • US20050099795A1
    • 2005-05-12
    • US10941489
    • 2004-09-15
    • John Seymour
    • John Seymour
    • B41F31/02B41F33/00B41F33/14G06T1/00F21V33/00
    • B41F33/0036B41F33/0045
    • An illumination system for a web travelling from upstream to downstream in a longitudinal direction in a printing press is described. The illumination system includes a first and a second illuminator for emitting light, each illuminator having a long axis arranged in a lateral direction. Further, the system includes a first and a second reflector, with the second reflector being arranged downstream from the first reflector. Each reflector has a surface for reflecting light from a corresponding illuminator toward the web, wherein a cross-section of each reflecting surface is a portion of a parabola having a focal point, or a portion of an ellipse, having two focal points. An illuminator is located at a corresponding focal point.
    • 描述了一种用于在印刷机中从纵向方向上游到下游的幅材的照明系统。 照明系统包括用于发光的第一和第二照明器,每个照明器具有沿横向布置的长轴。 此外,该系统包括第一反射器和第二反射器,其中第二反射器布置在第一反射器的下游。 每个反射器具有用于将来自相应的照明器的光朝向幅材反射的表面,其中每个反射表面的横截面是抛物线的具有焦点的部分或具有两个焦点的椭圆的一部分。 照明器位于相应的焦点处。
    • 4. 发明申请
    • COOLING CIRCUIT WITHIN A TURBINE NOZZLE AND METHOD OF COOLING A TURBINE NOZZLE
    • 涡轮喷嘴中的冷却电路和冷却涡轮喷嘴的方法
    • US20050031444A1
    • 2005-02-10
    • US10632851
    • 2003-08-04
    • Michael PothierJohn SeymourDavid Leo
    • Michael PothierJohn SeymourDavid Leo
    • F01D9/02F01D9/04F01D9/06F01D25/08
    • F01D9/06F01D9/041F01D25/08
    • A cooling circuit is provided within a turbine nozzle to help increase turbine efficiency. The turbine nozzle includes first, second and third cavities, an outer band, and an inner band. The cooling circuit contains an inlet receiving cooling medium flow, and a first duct insert disposed in the second cavity. The first duct insert receives the cooling medium flow via the inlet and duct flows the cooling medium flow to a bottom of the second cavity. An impingement insert is disposed in the first cavity that receives the cooling medium flow from the first duct insert. A first impingement plate is disposed within the outer band defining an outer band cooling path within the outer band. The outer band cooling path receives the cooling medium flow from the first cavity. A second cavity cooling path is defined between the first duct insert and a second cavity wall, where the second cavity cooling path receives the cooling medium flow from the outer band cooling path. A second impingement plate is disposed within the inner band and defines an inner band cooling path within the inner band. The inner band cooling path receives the cooling medium flow from second cavity cooling path. Finally, a second duct insert is disposed in the third cavity and defines a third cavity cooling path between the second duct insert and a third cavity wall. The third cavity cooling path receives the cooling medium flow from the inner band cooling path.
    • 在涡轮喷嘴内设置冷却回路以帮助提高涡轮效率。 涡轮喷嘴包括第一,第二和第三腔,外带和内带。 冷却回路包括入口接收冷却介质流,以及设置在第二腔中的第一管道插入件。 第一管道插入件通过入口接收冷却介质流,并且管道使冷却介质流流动到第二腔的底部。 冲击插入件设置在第一空腔中,其接收来自第一管道插入件的冷却介质流。 第一冲击板设置在外带内,限定外带内的外带冷却路径。 外带冷却通道接收来自第一腔的冷却介质流。 第二腔体冷却路径限定在第一管道插入件和第二腔壁之间,其中第二腔体冷却路径从外带冷却路径接收冷却介质流。 第二冲击板设置在内带内并且限定内带内的内带冷却路径。 内带冷却通道从第二腔冷却通道接收冷却介质流。 最后,第二管道插入件设置在第三腔中,并且在第二管道插入件和第三腔壁之间限定第三腔体冷却路径。 第三腔冷却通道从内带冷却通道接收冷却介质流。