Analysis of the Matching Line of between Turbine and Compressor in a Turbojet Engine
DOI:
https://doi.org/10.24237/djes.2025.18407Keywords:
thrust, matching line , Compressor, Turbine, performanceAbstract
Turbojet engines are now being given serious consideration owing to the high thrust power that they can deliver. The challenge that has arisen for the producers and designers of these engines relates to the problem of matching the compressor and the turbine. These components are crucial for the overall performance of the engine but differ distinctly. The problem of stalls may arise due to these disparities, thereby impacting on the flow of air and the subsequent output. In order to counter such a problem, a simulation approach has been designed by us that has an error margin of less than 0.03 as far as fuel consumption per unit thrust force. The thrust force has been determined within an accurate deviation of less than 1000 pounds. The accuracy of the simulation approach has been checked by using the data of the Pratt & Whitney J57 Turbojet engine. The simplified experimental outcomes estimated fuel consumption per unit thrust with an error margin of under 0.03. Furthermore, the thrust force for various engines was assessed with an accuracy deviation of less than 1000 pounds. The determination of the compatibility line was additionally corroborated by comparing the simulation results with established reference values for different turbojet engine components. The simulated compatibility line exhibited a 92% overlap accuracy for the Pratt-Whitney J57 engine, thereby affirming the reliability of the method.
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Copyright (c) 2025 Seyyed Kazem Yekani, mahdi nami khalilehdeh, Arash NourbakhshSadabad, Ali Sharifi
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