Control device for controlling clearance between tips of rotor blades of low pressure turbine in e.g. turbojet, has control unit controlling air flow supply to cooling circuit according to information about worn thickness of abradable layer

摘要

The device has a cooling circuit (36) for cooling an annular envelope (18) by impact of air. A sensor (42) is mounted on an internal surface of the annular envelope for determining worn thickness of an abradable layer (30) in contact with the tips of rotor blades (20). The sensor is connected to a control unit (40) that controls air flow supply to the cooling circuit according to multiple parameters of which one relates to information, provided by the sensor, about the worn thickness of the abradable layer. An independent claim is also included for a method for application of a clearance control device in a turboshaft engine.