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    • 24. 发明授权
    • Skin penetration apparatus including multiple needle configuration
    • 皮肤穿透装置,包括多针配置
    • US6030404A
    • 2000-02-29
    • US178188
    • 1998-10-23
    • Alexis A. LawsonMichael Lawson
    • Alexis A. LawsonMichael Lawson
    • A61M37/00A61B17/34
    • A61M37/0076
    • An array of elongated needles for penetrating skin is assembled in single or multiple tiers with the tips or points thereof substantially aligned along an axis or plane that is skewed in non-perpendicular orientation relative to the axes of elongation of the needles. The needles are rigidly confined in the assembly within a common base portion that extends to a boundary limit remote from the tips which is oriented along an axis or plane that is skewed in non-perpendicular orientation relative to axes of elongation of the needles. The axis or plane of the needle tips may be substantially parallel or non-parallel to the axis or plane of the boundary limit to promote selected resilient flexure characteristics of the needles in the portions thereof between the boundary limit of the base and the needle tips.
    • 用于穿透皮肤的细长针阵列组装成单层或多层,其顶端或点基本上沿着相对于针的伸长轴以非垂直取向偏斜的轴线或平面对齐。 这些针被牢固地限制在组件内,公共基部部分中延伸到远离尖端的边界极限,该尖端沿着相对于针的延伸轴线以非垂直取向偏斜的轴线或平面定向。 针尖的轴线或平面可以基本上平行于或不平行于边界极限的轴线或平面,以促进针在基部的边界极限和针尖之间的部分中的针的弹性弯曲特性。
    • 26. 发明申请
    • Gas turbine engine blade containment assembly
    • 燃气轮机发动机叶片安全壳组件
    • US20070110557A1
    • 2007-05-17
    • US11647257
    • 2006-12-29
    • Michael LawsonSivasubramaniam Sathianathan
    • Michael LawsonSivasubramaniam Sathianathan
    • F01D21/00
    • F01D21/045F05D2300/121F05D2300/133F05D2300/171Y02T50/672
    • A gas turbine engine rotor blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The metal casing (40) has at least one arched portion (62,64,66) and each arched portion (62,64,66) extends circumferentially around the metal casing (40). Each arched portion (62,64,66) comprises a radially inwardly extending arch (68) in which the trough (74) of the arch (68) is radially inwardly of a straight line (76) interconnecting the axial ends (70,72) of the arch (68). The trough (74) of the arch (68) is radially inwardly of the at least one of the axial ends (70,72) of the at least one arch (68). The arched portions (62,64,66) introduce compressive stresses into the metal casing (40) during a fan blade 34 impact and enable the metal casing (40) to withstand the impact. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).
    • 燃气涡轮发动机转子叶片容纳组件(38)包括大致圆柱形或截头圆锥形的金属壳体(40)。 金属外壳(40)具有至少一个拱形部分(62,66,66),并且每个拱形部分(62,66,66)围绕金属外壳(40)周向延伸。 每个拱形部分(62,66,66)包括径向向内延伸的拱形部分(68),拱形部分(68)的槽(74)在其中径向向内延伸直线(76),该直线(76)将轴向端部(70,72 )(68)。 拱形物(68)的槽(74)在至少一个拱形件(68)的轴向端部(70,72)中的径向内侧。 拱形部分(62,66,66)在风扇叶片34冲击期间将压缩应力引入金属壳体(40)中,并且使金属壳体(40)能够承受冲击。 对于大直径涡轮风扇燃气涡轮发动机(10),风扇叶片容纳组件(38)较轻。
    • 29. 发明申请
    • Gas turbine engine blade containment assembly
    • 燃气轮机发动机叶片安全壳组件
    • US20050238484A1
    • 2005-10-27
    • US11046246
    • 2005-01-31
    • Michael LawsonSivasubramaniam Sathianathan
    • Michael LawsonSivasubramaniam Sathianathan
    • F01D25/24F01D21/04F02C7/04F04D29/52F01D21/00
    • F01D21/045F05D2300/121F05D2300/133F05D2300/171Y02T50/672
    • A gas turbine engine rotor blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The metal casing (40) has at least one arched portion (62, 64, 66) and each arched portion (62, 64, 66) extends circumferentially around the metal casing (40). Each arched portion (62, 64, 66) comprises a radially inwardly extending arch (68) in which the trough (74) of the arch (68) is radially inwardly of a straight line (76) interconnecting the axial ends (70, 72) of the arch (68). The trough (74) of the arch (68) is radially inwardly of the at least one of the axial ends (70, 72) of the at least one arch (68). The arched portions (62, 64, 66) introduce compressive stresses into the metal casing (40) during a fan blade 34 impact and enable the metal casing (40) to withstand the impact. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).
    • 燃气涡轮发动机转子叶片容纳组件(38)包括大致圆柱形或截头圆锥形的金属壳体(40)。 金属外壳(40)具有至少一个拱形部分(62,64,66),并且每个拱形部分(62,64,66)围绕金属外壳(40)周向延伸。 每个拱形部分(62,64,66)包括径向向内延伸的拱形部分(68),拱形部分(68)的槽(74)在其中径向向内延伸出直线(76),该直线将直线(70,72) )(68)。 拱形物(68)的槽(74)在至少一个拱形部(68)的轴向端部(70,72)中的径向内侧。 拱形部分(62,64,66)在风扇叶片34冲击期间将压缩应力引入金属壳体(40)中,并且使得金属壳体(40)能够承受冲击。 对于大直径涡轮风扇燃气涡轮发动机(10),风扇叶片容纳组件(38)较轻。