A model-based fault tolerant control strategy for civil turbofan engine was discussed in order to mitigate or eliminate the adverse effect caused by certain faults through adjustments on existing controller. A controlling objective of recovering operability was presented for engines experiencing deterioration in high-pressure compressor and high-pressure turbine. In order to accomplish this objective

a fault accommodation look-up table was established offline

which was formed by optimal adjustments for design points calculated by solving an optimization problem using genetic algorithm. For a general point in the flight envelope

the adjustments were gained through online interpolation among design points. The strategy was validated simple and effective through simulation. Results showed that stall margins of the booster were all recovered to the corresponding levels of the unfaulted engine without exceeding temperature limitations. Stall margins of the fan and high pressure compressor decreased by less than 5% and the thrust by less than 3%.