公开(公告)号：US07431557B2

公开(公告)日：2008-10-07

申请号：US11441258

申请日：2006-05-25

申请人： William Lee Herron ,  Matthew William Wiseman ,  Jon Michael Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

发明人： William Lee Herron ,  Matthew William Wiseman ,  Jon Michael Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

IPC分类号： G06F19/00

CPC分类号： F01D11/24 ,  F05D2260/80 ,  F05D2270/44 ,  Y02T50/672

摘要： A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

摘要翻译： 用于补偿在飞行器燃气涡轮发动机中的旋转叶片尖端和周围护罩之间的叶片顶端间隙变差的方法包括基于一个或多个发动机工作参数的至少一个或多个移动平均值确定一个或多个变量， 操作发动机飞行循环的数量，并且基于一个或多个变量来调节热控制空气的流量以对抗叶片顶端间隙恶化。 发动机运行参数可以包括发动机循环的运行次数，起飞和巡航废气温度裕度，巡航涡轮机效率，起飞和巡航最大涡轮机速度，巡航燃料流量。 变量的一些或全部可能分别是发动机运行参数的移动平均值和相应基线之间的差异，或者变量都可以是移动平均线。 流量可以逐渐调整。

公开(公告)号：US20070276578A1

公开(公告)日：2007-11-29

申请号：US11441258

申请日：2006-05-25

申请人： William Lee Herron ,  Matthew William Wiseman ,  Jon Micheal Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

发明人： William Lee Herron ,  Matthew William Wiseman ,  Jon Micheal Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

IPC分类号： G06F19/00

CPC分类号： F01D11/24 ,  F05D2260/80 ,  F05D2270/44 ,  Y02T50/672

摘要： A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

摘要翻译： 用于补偿在飞行器燃气涡轮发动机中的旋转叶片尖端和周围护罩之间的叶片顶端间隙变差的方法包括基于一个或多个发动机工作参数的至少一个或多个移动平均值确定一个或多个变量， 操作发动机飞行循环的数量，并且基于一个或多个变量来调节热控制空气的流量以对抗叶片顶端间隙恶化。 发动机运行参数可以包括发动机循环的运行次数，起飞和巡航废气温度裕度，巡航涡轮机效率，起飞和巡航最大涡轮机速度，巡航燃料流量。 变量的一些或全部可能分别是发动机运行参数的移动平均值和相应基线之间的差异，或者变量都可以是移动平均线。 流量可以逐渐调整。