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    • 1. 发明申请
    • Method and system for layer-3 subscriber login in a cable data network
    • 有线数据网络中第三层用户登录的方法和系统
    • US20110161510A1
    • 2011-06-30
    • US12649318
    • 2009-12-29
    • Erich C. ArnoldThomas J. CloonanJeff Howe
    • Erich C. ArnoldThomas J. CloonanJeff Howe
    • G06F15/16
    • H04L63/10H04L12/2801H04L12/287H04L63/164H04W12/08
    • A subscriber login server is used for managing a subscriber login session. The login server is associated with a DHCP server for configuring a premise equipment device and operator-managed device. A subscriber login client at the premise equipment device securely communicates login username and password identifiers to the subscriber login server without using PPP technology. The login server retrieves matching identifiers from a RADIUS server and authorizes service with messages to the DHCP server and the CMTS.The login client can emulate a PPP login client so that a user's interface is similar to a PPPoE client. However, a layer-3 CMTS can be used instead of a layer-2 CMTS. In addition, subscriber authentication and accounting using RADIUS are preserved, positive network access control at the CMTS is maintained, and native IP traffic is routed or switched for maximum performance and QoS treatment.
    • 用户登录服务器用于管理用户登录会话。 登录服务器与DHCP服务器相关联,用于配置前提设备设备和操作员管理的设备。 住宅设备设备上的用户登录客户端可以安全地将登录用户名和密码标识符传递给用户登录服务器,而无需使用PPP技术。 登录服务器从RADIUS服务器检索匹配的标识符,并向DHCP服务器和CMTS授权服务。 登录客户端可以模拟PPP登录客户端,使用户的界面类似于PPPoE客户端。 然而,可以使用第3层CMTS而不是第2层CMTS。 另外,保留了使用RADIUS的用户认证和计费,保持了CMTS的正确的网络访问控制,本地IP流量被路由或切换,以实现最佳性能和QoS处理。
    • 9. 发明授权
    • Gas turbine engine assemblies with vortex suppression and cooling film replenishment
    • 具有涡流抑制和冷却膜补充的燃气涡轮发动机组件
    • US08167557B2
    • 2012-05-01
    • US12187791
    • 2008-08-07
    • Tom ElliottGreg HeitlandJeff HoweMark C. Morris
    • Tom ElliottGreg HeitlandJeff HoweMark C. Morris
    • F01D5/18
    • F01D5/186F05D2240/127F05D2240/81F05D2260/2212Y02T50/673Y02T50/676
    • A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.
    • 燃气涡轮发动机组件具有流过气体流路的燃烧气体。 燃气涡轮发动机组件包括定子组件,该定子组件包括延伸到气体流路中的定子叶片; 以及在定子组件下游的涡轮机转子组件,并且包括涡轮机平台和从涡轮机平台延伸到主流燃烧气体流动路径中的涡轮机转子叶片。 涡轮转子叶片包括压力侧和与从前缘延伸到后缘的压力侧相对的吸力侧。 燃烧气体在与涡轮机转子叶片的前缘相邻的形成区域形成马蹄形旋涡,并且涡轮机转子组件还包括涡轮机平台中的第一组孔,用于将第一射流引导到马蹄形旋涡的形成区域中。
    • 10. 发明授权
    • Impeller backface shroud for use with a gas turbine engine
    • 用于燃气轮机的叶轮背面护罩
    • US08801364B2
    • 2014-08-12
    • US12794433
    • 2010-06-04
    • Mark C. MorrisAlexander MirzaMoghadamKhosro Molla HosseiniKin PoonJeff HoweAlan G. Tiltman
    • Mark C. MorrisAlexander MirzaMoghadamKhosro Molla HosseiniKin PoonJeff HoweAlan G. Tiltman
    • F01D3/00
    • F01D3/025
    • An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.
    • 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时,叶轮或轴向级压缩机盘的表面和背面形成空腔,该空腔将气流部分引导到涡轮机。 气流部分具有切向速度,并且背面护罩的表面中的凹槽通常横向于切向速度定向,以至少部分地干扰气流部分,从而影响空腔中的静压力。