The Performance Deterioration Analysis Of An Aeroengine Based On Unscented Kalman Filter Algorithm

It is significant to estimate the performance of the civil aero-engine. It can be used for not only discovering the faults which may be occurred in the electronic control parts and instruments in advance, but also predicting the reliability and the performance trend of the aero-engine. This technique can also be used to improve the safety and reduce the delay. Besides, the technique can save the fuel and the maintenance cost. For the designers and manufacturers, the deterioration model can be introduced into the control system which will improve the control accuracy.Therefore, it is necessary to monitor the performance of an aero-engine.There are varieties of techniques to monitor the aero-engine. The method of monitoring the changes of gas path parameters was used in this paper to analyze the performance parameter deterioration. Taking V2500-A5 installed on the A320 as an example. Firstly, establishing a model and choosing four parameters, they are respectively fan's efficiency, fan's pressure loss, the low pressure compressor's efficiency and the whole turbine's efficiency. Then according to the model,rearranging the original data, and finally extracting 184 groups of cruising data.Calculating the parameters based on the hybrid genetic algorithm and the unscented Kalman filter algorithm. To improve the accuracy, this paper introduces two additional relations. And finally the parameters were all solved, which reflected the changes in aero-engine time on wing.The results proved that the ways of performance deterioration are different for different parts of the engine. Generally, before 2000 cycles, the value experiences a very rapid decline which is about 10%; Between 2000 cycle and 6000 cycles, the value remains almost unchanged or declined with a slow speed, the decrease amplitude is about 2%; After the 6000 cycles, the deterioration goes quickly again,and value reaches at 3%. The tip abrasions of blade and pollutant aggradations are two major reasons creating deteriorations. Therefore, aero-engine maintenance plan can use the conclusion for reference.