Designing The Matching Line of Turbine Performance with Compressor in UAV Turbofan Engine Containing Hot and Cold Thrusts

Turbofan engines have attracted a lot of attention due to their high propulsion power. Compatibility of the simultaneous operation of the two main components of the turbofan engine, i.e., compressor and turbine, is one of the main concerns of designers and manufacturers. Because the form of characteristic curves of turbine and compressor are different and almost contradictory and will cause stagnation. In order to prevent turbofan surge, determining the matching of different components of this type of motors has become very important. The sensitivity of different parameters in the design of these types of engines is very high and achieving precalculated simulations that can have less calculation error will reduce the cost and time of the design stage. In this research, a lowerror simulation is designed to calculate the matching line of turbofan engines. In the stages of this research, first, the parameters affecting the matching line have been determined, and the method of calculating it has been extracted and simulated. Validation has been done for this simulation using the specifications of the RR-Trent 772-60, PW-PW4098 engines. According to the experiment performed, the thrust fuel consumption has been calculated with an error accuracy of less than 0.05 and the amount of thrust for different engines is less than 2000 (lbs). In another experiment, the correctness of determining the matching line for different components of the turbofan engine has been confirmed using the available resources. On the other hand, the accuracy of the overlap of the matching line of the simulation is 92% for the RR-Trent 772-60 engine and 94.2% for the PW-PW4098 engine.