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    • 38. 发明申请
    • Flow trim for vane-axial fans
    • 叶片轴流风机流量调整
    • US20110038724A1
    • 2011-02-17
    • US12583024
    • 2009-08-12
    • John J. DeckerChellappa BalanPatrick B. Lawless
    • John J. DeckerChellappa BalanPatrick B. Lawless
    • F04D29/54
    • F04D29/526F04D29/541
    • A fan comprises a fan housing which includes a fan inlet, a motor which is connected to the fan housing, and an impeller which is removably connected to the motor. The impeller includes an impeller hub, a number of impeller blades which extend radially outwardly from the impeller hub, an impeller leading edge, an impeller trailing edge and an impeller tip. The fan housing includes an inlet shroud which is positioned over the impeller. The inlet shroud comprises an upstream end portion within which the fan inlet is formed and a downstream end portion which is removably connected to a separate portion of the fan housing. The inlet shroud further includes a first section which extends axially from the upstream end portion to approximately the impeller leading edge, a second section which extends axially from the first section to approximately the impeller trailing edge, and a third section which extends axially from the second section to approximately the downstream end portion. The second section comprises a configuration which conforms to the configuration of the impeller tip, and the third section comprises a radius which increases from approximately the upstream end of the third section to approximately the downstream end of the third section.
    • 风扇包括风扇壳体,其包括风扇入口,连接到风扇壳体的电动机和可移除地连接到电动机的叶轮。 叶轮包括叶轮毂,从叶轮毂径向向外延伸的多个叶轮叶片,叶轮前缘,叶轮后缘和叶轮尖端。 风扇壳体包括位于叶轮上方的入口罩。 入口护罩包括形成风扇入口的上游端部分和可移除地连接到风扇壳体的分离部分的下游端部分。 入口罩还包括第一部分,其从上游端部分轴向延伸到大致叶轮前缘;第二部分,其从第一部分轴向延伸到大约叶轮后缘;以及第三部分,其从第二部分轴向延伸, 截面到大致下游端部。 第二部分包括符合叶轮尖端的构造的构造,第三部分包括从第三部分的大致上游端到第三部分的下游端的大致半径。
    • 39. 发明授权
    • Aircraft auxiliary gas turbine engine and method for operating
    • 飞机辅助燃气轮机及其操作方法
    • US07721554B2
    • 2010-05-25
    • US11345950
    • 2006-02-02
    • Chellappa BalanKarl Edward Sheldon
    • Chellappa BalanKarl Edward Sheldon
    • F02C6/04
    • B64D41/00B64D2013/0611B64D2041/002F02C7/32F05D2220/50
    • A non-aircraft-propelling auxiliary gas turbine engine installable in an aircraft having a cabin adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor having an inlet, wherein the inlet is adapted to receive pressurized air from the cabin. A method for operating a non-aircraft-propelling auxiliary gas turbine engine of an aircraft includes providing pressurized air from the cabin of the aircraft to an inlet of a compressor of the auxiliary gas turbine engine. The method includes providing compressed air from the compressor to a combustor of the auxiliary gas turbine engine and includes providing combustion gases from the combustor to a turbine of the auxiliary gas turbine engine, wherein the turbine is mechanically coupled to the compressor.
    • 可安装在具有适于加压的舱室的飞行器中的非飞机推进辅助燃气涡轮发动机。 辅助燃气涡轮发动机包括具有入口的辅助燃气涡轮发动机压缩机,其中入口适于从舱室接收加压空气。 用于操作飞行器的非飞机推进辅助燃气涡轮发动机的方法包括将来自飞机的舱室的加压空气提供给辅助燃气涡轮发动机的压缩机的入口。 该方法包括将压缩空气从压缩机提供给辅助燃气涡轮发动机的燃烧器,并且包括将来自燃烧器的燃烧气体提供给辅助燃气涡轮发动机的涡轮机,其中涡轮机械地联接到压缩机。