Improving the efficiency of a bypass turbofan engine by intermediate cooling during compression

The preliminary analysis of the current state and trends of the development of aircraft gas turbine engines such as turbojets, turboprops, turbofans, etc. shows the importance of the theoretical study and design research aimed at improving the efficiency of turbofan engines by implementing regeneration cycles, intermediate cooling during compression, intermediate heating during expansion, and their possible combinations. A thermodynamically reasonable structure that can easily be implemented and does not require significant structural modifications of the gas generator was chosen to perform the analysis. The heat accumulated during the intermediate inlet air cooling in the high-pressure compressor was recovered by heating the air in the second contour. The excessive turbine capacity of the high-pressure compressor was redistributed between low- and high-pressure turbines to increase the fan capacity, that is, the air flow through the second contour. The results of the study are presented for a model turbofan engine whose parameters are similar to those of the D-436 turbofan engine used in civil aviation. The implemented intermediate cooling increases the total turbofan thrust by 20...22 % and reduces the specific fuel consumption by 2.5...3 % depending on the thermal resistance of heat exchangers.

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