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    • 4. 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
    • US20060140756A1
    • 2006-06-29
    • US11253235
    • 2005-10-17
    • Frederick SchwarzJ. Smith
    • Frederick SchwarzJ. Smith
    • F01D11/08
    • F01D11/122F01D11/22F01D21/04F04D29/052F05D2260/403F16C23/06F16C2360/23Y02T50/671
    • A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine having one or more second rotor assemblies and one or more second stator assemblies disposed adjacent the one or more second rotor assemblies; one or more shroud segments having blade seal surfaces disposed radially outside of the tips of blades of both the first and second rotor assemblies and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator selectively operable to axially move the first and said second rotor assemblies to alter the clearance distance.
    • 用于燃气涡轮发动机的零运行间隙系统包括具有一个或多个第一转子组件和邻近一个或多个第一转子组件设置的一个或多个第一定子组件的燃气涡轮发动机压缩机; 具有一个或多个第二转子组件和邻近所述一个或多个第二转子组件设置的一个或多个第二定子组件的燃气涡轮发动机涡轮机; 一个或多个护罩段具有设置在第一和第二转子组件的叶片的尖端的径向外侧的叶片密封表面和在叶片尖端和叶片密封表面之间延伸的间隙距离; 以及致动器,其选择性地可操作以轴向移动所述第一和所述第二转子组件以改变所述间隙距离。
    • 5. 发明申请
    • Thermal management system for turbofan engines
    • 涡扇发动机热管理系统
    • US20070264133A1
    • 2007-11-15
    • US11432111
    • 2006-05-11
    • Frederick SchwarzMikhail Gorbounov
    • Frederick SchwarzMikhail Gorbounov
    • F04F1/18B60H1/00F25B19/00
    • F01D25/18F01D25/125F02C7/14F02K3/06Y02T50/671Y02T50/675
    • A heat exchange system for use in operating equipment in which a working fluid is utilized needing a heat exchange system to provide air and working fluid heat exchanges to cool the working fluid at selectively variable rates in airstreams. The system comprises a plurality of heat exchangers including a first heat exchanger in the plurality of heat exchangers that is mounted with respect to the equipment so as to permit corresponding portions of the airstreams to pass through the core thereof during at least some such uses of the equipment. Also, a second heat exchanger is mounted with respect to the equipment so as to selectively permit corresponding portions of the airstreams to pass through the core thereof during such uses of the equipment. A core actuator is mounted with respect to the second heat exchanger to selectively increase or reduce the passing of those corresponding portions of the airstreams through the core.
    • 一种用于操作设备的热交换系统,其中使用工作流体需要热交换系统以提供空气和工作流体热交换,以在气流中以可选择的速率冷却工作流体。 该系统包括多个热交换器,其包括相对于设备安装的多个热交换器中的第一热交换器,以便在至少一些这样的使用期间允许空气流的相应部分通过其核心 设备。 而且,相对于设备安装第二热交换器,以便在设备的这种使用期间选择性地允许气流的相应部分通过其核心。 核心致动器相对于第二热交换器安装以选择性地增加或减少气流的这些相应部分通过芯的通过。
    • 6. 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。