Aero Engine Component Fault Diagnosis Using Multi-Hidden-Layer Extreme Learning Machine with Optimized Structure

<div>Schematic layout of studied turbine fan engine. A, inlet; B, fan; C, high pressure compressor; D, main combustor; E, high pressure turbine; F, low pressure turbine; G, external duct; H, mixer; I, afterburner; J, nozzle.</div>

International Journal of Aerospace Engineering

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Figure 4

Figure 4: Aero Engine Component Fault Diagnosis Using Multi-Hidden-Layer Extreme Learning Machine with Optimized Structure 