会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 1. 发明授权
    • Aircraft propulsion system
    • 飞机推进系统
    • US08720815B2
    • 2014-05-13
    • US12768585
    • 2010-04-27
    • Daniel Kent VettersRobert Wayne CedozDavid Eames
    • Daniel Kent VettersRobert Wayne CedozDavid Eames
    • B64D27/00
    • B64D27/10B64D27/26B64D2027/005B64D2027/026Y02T50/44Y02T50/64Y02T50/66
    • An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.
    • 这里公开了一种飞机推进系统。 飞行器推进系统包括具有进气口的核心发动机,压缩机部分,燃烧器部分和沿中心轴线布置的涡轮部分。 飞机推进系统还包括围绕核心发动机的机舱。 飞行器推进系统还包括至少一个自由动力涡轮机,该自由动力涡轮机被排出涡轮部分的废气驱动旋转。 飞行器推进系统还包括至少一个被至少一个自由动力涡轮机驱动旋转的转子模块。 飞机推进系统还包括从机舱延伸的第一和第二塔架,并且可操作地将核心发动机安装到飞机上。 第一和第二塔在包含中心线轴线的至少一个平面的相对侧上彼此间隔开,并且跨越至少一个平面相互镜像。
    • 4. 发明授权
    • Integrated bypass engine structure
    • 集成旁路引擎结构
    • US08438859B2
    • 2013-05-14
    • US12006980
    • 2008-01-08
    • Daniel Kent Vetters
    • Daniel Kent Vetters
    • F02C7/20
    • F04D29/52F01D25/24F02K3/04
    • One form of the present invention contemplates an apparatus including a gas turbine engine core, wherein a gearbox accessory is mounted to the engine core and is substantially enclosed by an inner fairing. The apparatus can further include a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing. The apparatus can further include a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels. In additional and/or alternative forms a number of frame rods can also be used internal to the nacelle or nacelle panel. In some forms the frame rods can be connected between a front and rear frame.
    • 本发明的一种形式涉及一种包括燃气涡轮发动机芯的装置,其中齿轮箱附件安装在发动机芯上并且基本上由内部整流罩包围。 该装置还可以包括具有多个面板的机舱,其中,所述机舱面板基本上包围并与所述内部整流罩的至少一部分重叠。 该装置还可以包括限定在内部整流罩的外表面与至少一些机舱面板的内表面之间的旁路管道。 在附加和/或替代形式中,许多框架杆也可以在机舱或机舱面板内部使用。 在一些形式中,框架杆可以连接在前框架和后框架之间。