Patent ID: 9666051
Date: 2017-05-30
CPC Classifications: B64D,G08B

Claim:
1. A method of detecting that an aircraft is flying in icing conditions, the aircraft having a turboshaft engine receiving air coming from an outside medium situated outside the aircraft via an air inlet, the engine including a gas generator provided with at least one compressor and a combustion chamber, the engine further including a power assembly having at least one power turbine driven in rotation by exhaust gas from the combustion chamber, the method comprising: a processor unit determining a real power developed by the engine as a function of a torque developed by the power assembly as measured by a torque measurement system and of a speed of rotation of the power assembly as measured by a speed measurement system, the speed of rotation of the power assembly being referred to as a “second speed of rotation”; the processor unit determining a theoretical power that the engine can develop in theory, the theoretical power being determined by the processor unit as a function at least of a theoretical model of the engine, the theoretical model of the engine providing the theoretical power as a function at least of a speed of rotation of the gas generator as measured by a speed measurement sensor, the speed of rotation of the gas generator being referred to as a “first speed of rotation”; the processor unit determining a power difference between the real power and the theoretical power; and the processor unit generating a warning to indicate a presence of icing conditions when: