Abstract: A system and method for detecting erosion in turbine engine blades is provided. The blade erosion detection system includes a sensor data processor and a cluster analysis mechanism. The sensor data processor receives engine sensor data, including exhaust gas temperature (EGT) data, and augments the sensor data to determine sensor data residual values and the rate of change of the sensor data residual values. The augmented sensor data is passed to the cluster analysis mechanism. The cluster analysis mechanism analyzes the augmented sensor data to determine the likelihood that compressor blade erosion has occurred. Specifically, the cluster analysis mechanism performs a 2-tuple cluster feature analysis using Gaussian density functions that provide approximations of normal and eroded blades in a turbine engine. The 2-tuple cluster feature analysis thus provides the probability that the sensor data indicates erosion has occurred in the turbine engine.

Abstract: A method of monitoring turbine engines used in aircraft from sensor signals from an engine for a predetermined set of engine characteristics. The signals are transmitted to a nonlinear engine model that predicts the output values for the given set of engine characteristics. The model generates residuals by calculating the difference between the actual values and the predicted values for each member of the set. The generated residuals are evaluated to estimate bounds of uncertainties as indicative of sensor noise. Incoming residuals from ongoing actual engine values are continuously tested against the bounds. A fault is signaled for each of the set of characteristics when a detected bound is exceeded. A computer is used to calculate the fault residual for each of the set of characteristics and the closest fault residual is selected as a diagnosed fault.

Abstract: A control system and method for controlling the split between premix fuel flow and pilot fuel flow to a combustor in a gas turbine engine so that an acceptable emissions are maintained. Engine speed and exhaust gas temperature are used to obtain a combustor pilot zone temperature that will result in the desired level of emissions. From this pilot zone temperature a desired split between premix fuel flow and pilot fuel flow is obtained and compared to the actual split to generate an error signal. The actual premix fuel flow and pilot fuel flow are then adjusted until the desired split and hence the desired emission levels are obtained.