Method for determining an efficiency fault of an aircraft turboshaft engine module

A non-transitory computer readable storage medium storing instructions that when executed by a computer, which includes a processor, performs a method, the method comprising:

• determining a performance mapping of a turboshaft engine so as to define an estimated real mapping, the estimated real mapping defining a plurality of mathematical relationships between parameters of the turboshaft engine, each of the mathematical relationships being determined from measurements of the parameters of the turboshaft engine acquired during a given flight of an aircraft,
• determining real indicators from the estimated real mapping, said real indicators corresponding to operating singularities of the turboshaft engine,
• determining a plurality of performance mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations so as to define simulated mappings, the efficiency configuration determining the efficiency of each module,
• determining simulated indicators for each of the simulated mappings, said simulated indicators corresponding to operating singularities of the turboshaft engine,
• training a mathematical model by linking the simulated indicators to the efficiency configurations, and
• applying said mathematical model to the real indicators in order to deduce a real efficiency configuration.

A computer-implemented method for determining an efficiency fault of at least one module of a turboshaft engine of an aircraft, the at least one module of the turboshaft engine comprising at least one compressor module, at least one combustion chamber module, and at least one turbine module, each of the modules having an efficiency that is specific to it, the computer-implemented method comprising:

• determining a performance mapping of a turboshaft engine so as to define an estimated real mapping, the estimated real mapping defining a plurality of mathematical relationships between parameters of the turboshaft engine, each of the mathematical relationships being determined from measurements of the parameters of the turboshaft engine acquired during a given flight of an aircraft,
• determining real indicators from the estimated real mapping, said real indicators corresponding to operating singularities of the turboshaft engine,
• determining a plurality of performance mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations so as to define simulated mappings, the efficiency configuration determining the efficiency of each module,
• determining simulated indicators for each of the simulated mappings, said simulated indicators corresponding to operating singularities of the turboshaft engine,
• training a mathematical model by linking the simulated indicators to the efficiency configurations, and
• applying said mathematical model to the real indicators in order to deduce a real efficiency configuration.