Gas turbine for aircraft, has compressor unit provided with compressor modules, which are swivelably supported on drive shaft and are separable from shaft in propulsive manner, where each compressor module is provided with sensor units

摘要

The turbine (EEC) has a multi-level compressor unit (2) provided with a set of individual independent compressor modules (3-5), which are swivelably supported on a drive shaft (1) and are separable from the drive shaft in a propulsive manner. Each compressor module is provided with sensor units (12-14) that are connected with an electronic control (15), where the sensor units are designed as vibration measuring device. The compressor modules cover a compressor stage with a rotor that comprises multiple rotor blades and stators with multiple stator blades.