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    • 8. 发明申请
    • Gas turbine engine blade tip clearance apparatus and method
    • 燃气轮机发动机叶片间隙装置及方法
    • US20060140755A1
    • 2006-06-29
    • US11025435
    • 2004-12-29
    • Frederick SchwarzRobert PerkinsonJesse Smith
    • Frederick SchwarzRobert PerkinsonJesse Smith
    • F01D11/08
    • F01D11/22F01D11/122F04D29/052F05D2260/403F16C23/06F16C2360/23
    • A gas turbine engine is provided that includes one or more rotor assemblies, one or more shroud segments, and an actuator. The rotor assemblies are rotatable around an axially extending rotational axis, and each rotor assembly has a plurality of blades. Each blade has a blade tip. The one or more shroud segments each has a blade seal surface disposed radially outside of the one or more rotor assemblies. The blade tips and blade seal surfaces (collectively referred to as the blade seal surface) have mating conical geometries and a clearance distance extending between the blade tips and blade seal surface. The blade tips and blade seal surface are disposed at an angle relative to the axial centerline of the engine, which angle is greater than zero. The actuator is selectively operable to axially move one or both of the shroud segments and rotor assemblies relative to the other of the shroud segments and rotor assemblies to alter the clearance distance.
    • 提供了一种燃气涡轮发动机,其包括一个或多个转子组件,一个或多个护罩段和致动器。 转子组件可围绕轴向延伸的旋转轴线旋转,并且每个转子组件具有多个叶片。 每个叶片都有一个叶片尖端。 一个或多个护罩段各自具有设置在一个或多个转子组件的径向外侧的叶片密封表面。 叶片尖端和叶片密封表面(统称为叶片密封表面)具有匹配的圆锥形几何形状和在叶片尖端和叶片密封表面之间延伸的间隙距离。 叶片尖端和叶片密封表面相对于发动机的轴向中心线成角度设置,该角度大于零。 致动器可选择性地可操作以相对于护罩段和转子组件中的另一个轴向移动护罩段和转子组件中的一个或两个,以改变间隙距离。