| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a method of compensating blade tip gap degrading between rotary blade tip and circumferential shroud in an aircraft gas turbine engine. <P>SOLUTION: This method includes the steps of fixing at least one or more variables based on at least one or more moving average deviations of at least one or more engine operating parameters, respectively, and of adjusting a flow rate of thermal control air 36 so that blade tip gap degrading value may be offset based on at least one or more variables over fixed operation engine flight cycle number. The engine operating parameter can include operation engine cycle number, take-off and cruise exhaust gas temperature margin, cruise turbine efficiency, take-off and cruise maximum turbine speed, and cruise fuel flow rate. Some or all variables can be set to be a difference between the moving average deviation of the engine operating parameter and corresponding baseline, or all variables can be set to be the moving average deviation. The flow rate can be adjusted to be increased gradually. <P>COPYRIGHT: (C)2008,JPO&INPIT |
