Control systems for multi-stage axial flow compressors

摘要

A control system is provided for the multi-stage axial flow compressor of a gas turbine engine. The control system embraces a stage of variable angle guide vanes, a first detector adapted to detect a first pressure in the compressor which is influenced by the vane angular setting, and a second detector adapted to detect a second pressure independent of the vane setting but bearing a functional relationship to the rotational speed of a compressor of the engine. A control unit is adapted to use the pressures detected by the detectors to cause an actuation mechanism to adjust the angular setting of the guide vanes in a predetermined manner dependent upon the ratio of the second pressure to the first pressure.