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Abstract <p>In the paper, a method for improving the thermodynamic efficiency of a jet engine intended for space exploration is considered. In the proposed engine design, the nozzle is equipped with a second contour. The outer contour is located coaxially above the main nozzle. An additional coolant, hydrogen, is fed to the input of the second contour. The use of the heat removed from the operating fluid of the main contour to heat the external coolant increases the thermal efficiency of the engine from 75.6 to 85%. Due to heat transfer from the hot gases of the internal contour and the special shape of the channel, the flow is accelerated and an increase in the engine thrust to 3882 N is achieved. Numerical modeling of the flow and heat transfer process in the nozzles of engines of classical and modified designs is performed. The characteristic cross-sectional shape of the engine nozzle allows the use of an axisymmetric analytical model. Based on the calculation results, the values of thermal efficiency, jet thrust, specific impulse, and increase in nozzle mass are compared.</p>

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Feasibility Study of the Cooling Contour of a Jet Engine to Improve Thermodynamic Efficiency

  • 期刊论文

  • 发表日期：

    2025年6月1日

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  • A. G. Polyanskiy,
  • A. D. Ezhov

摘要

Abstract

In the paper, a method for improving the thermodynamic efficiency of a jet engine intended for space exploration is considered. In the proposed engine design, the nozzle is equipped with a second contour. The outer contour is located coaxially above the main nozzle. An additional coolant, hydrogen, is fed to the input of the second contour. The use of the heat removed from the operating fluid of the main contour to heat the external coolant increases the thermal efficiency of the engine from 75.6 to 85%. Due to heat transfer from the hot gases of the internal contour and the special shape of the channel, the flow is accelerated and an increase in the engine thrust to 3882 N is achieved. Numerical modeling of the flow and heat transfer process in the nozzles of engines of classical and modified designs is performed. The characteristic cross-sectional shape of the engine nozzle allows the use of an axisymmetric analytical model. Based on the calculation results, the values of thermal efficiency, jet thrust, specific impulse, and increase in nozzle mass are compared.