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    • 4. 发明申请
    • Methods and apparatus for maintaining rotor assembly tip clearances
    • 保持转子总成尖端间隙的方法和装置
    • US20060147303A1
    • 2006-07-06
    • US11028815
    • 2005-01-04
    • Daniel Harris
    • Daniel Harris
    • F04D29/08
    • F01D5/08F01D9/04F01D11/12F01D11/122F01D11/18F01D25/243Y02T50/67Y02T50/676
    • A method for assembling a rotor assembly for a gas turbine engine is provided. The engine includes an engine casing, a plurality of rotor blades, and at least one turbine shroud assembly. The method includes mounting a plurality of case segments together circumferentially to form the casing around the plurality of rotor blades and the at least one turbine shroud assembly, wherein each of the case segments includes at least two mounting flanges and a channel defined therebetween. The method also includes applying a thermal barrier coating to an inner surface of the channel and at least a portion of each mounting flange to facilitate maintaining axisymmetric running tip clearances between the plurality of rotor blades and the least one turbine shroud assembly during a cruise operation. The thermal barrier coating also facilitates controlling axisymmetric running tip clearances during a take-off operation such that an exhaust gas temperature and a specific fuel consumption is reduced.
    • 提供一种组装用于燃气轮机的转子组件的方法。 发动机包括发动机壳体,多个转子叶片和至少一个涡轮机罩组件。 该方法包括将多个壳体段周向地安装在一起,以围绕多个转子叶片和至少一个涡轮机护罩组件形成壳体,其中每个壳体段包括至少两个安装凸缘和在其间限定的通道。 该方法还包括将热障涂层施加到通道的内表面和每个安装凸缘的至少一部分,以便于在巡航操作期间维持多个转子叶片与至少一个涡轮机罩组件之间的轴对称运行尖端间隙。 隔热涂层还有助于在起飞操作期间控制轴对称运行尖端间隙,使得排气温度和特定燃料消耗降低。