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Abstract <p>The development and analysis of the aircraft engine combustor technical concepts for three variants of the second generation supersonic civil aircraft propulsion systems were carried out. For this purpose, a reduced kinetic mechanism was developed and a mathematical model to assess the harmful substances emission was validated. Based on the calculated characteristics of developed combustors, the refinement of variant for the three-engine propulsion system was carried out, which made it possible to ensure a NO<sub><i>x</i></sub> emission margin for subsonic aircraft requirements in accordance with CAEP/8. A numerical thermal state simulation of the flame tube with the proposed cooling scheme was also carried out.</p>

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Low-Emission Combustors for Aircraft Engines: Development and Numerical Analysis of Technical Concepts Using the Reduced Kinetic Mechanism

  • 期刊论文

  • 发表日期：

    2025年6月1日

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  • A. N. Tarasenko,
  • A. Yu. Vasil’ev,
  • B. I. Loukhovitski,
  • A. S. Sharipov,
  • M. V. Siluyanova

摘要

Abstract

The development and analysis of the aircraft engine combustor technical concepts for three variants of the second generation supersonic civil aircraft propulsion systems were carried out. For this purpose, a reduced kinetic mechanism was developed and a mathematical model to assess the harmful substances emission was validated. Based on the calculated characteristics of developed combustors, the refinement of variant for the three-engine propulsion system was carried out, which made it possible to ensure a NOx emission margin for subsonic aircraft requirements in accordance with CAEP/8. A numerical thermal state simulation of the flame tube with the proposed cooling scheme was also carried out.