| Citation: | TAO Rui, ZHAO Jun, JIANG Jin, et al. Overall performance of different heating configurations of turbojet engines[J]. Journal of Aerospace Power, 2025, 40（5）：20230688 doi: 10.13224/j.cnki.jasp.20230688
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In order to study the overall performance differences of two heating configurations of turbojet engines, the Visual C++ (VC) platform was employed, and a component-level modeling method was utilized. Simulation models for the two heating configurations of the turbojet engines were established, and a comparative analysis was conducted through simulation to evaluate their performance under different operational parameters. The results indicated that when the interstage turbine burner turbojet engine’s effective efficiency exceeded that of the afterburner turbojet engine by 7%, the total pressure ratio of the interstage turbine burner turbojet engine’s selected compressor was higher than that of the afterburner turbojet engine by 25.07%. The interstage turbine burner turbojet engine required a higher compressor pressure ratio to be selected. Regarding throttling characteristics, the fuel consumption of the interstage turbine burner turbojet engine in the fully open state was reduced by 33.33% compared with the fully open afterburner state. In terms of altitude and speed characteristics, the performance of the interstage turbine burner turbojet engine was less affected by changes in flight conditions compared with the afterburner cycle turbojet engine and conventional cycle turbojet engine.
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