Process for controlling an aircraft engine comprises determining an inlet temperature of air in the engine during start-up, comparing with a reference temperature and influencing the angle of the guide blades

摘要

Process for controlling an aircraft engine, especially a compressor of the engine, comprises determining an inlet temperature of air in the engine during start-up, comparing with a reference temperature and influencing the angle of the guide blades when the inlet temperature lies below the reference temperature. An independent claim is also included for an aircraft engine. Preferred Features: The angular adjustment of the guide blades is influenced when the inlet temperature lies below the reference temperature depending on the difference between the inlet temperature and the reference temperature or depending on the ratio of the inlet temperature and the reference temperature.