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<p>To study the ejector characteristics of a turbofan engine with a fan ejector nozzle during high-altitude flight, this paper analyzes the ejector characteristics of the engine and proposes a new control law to improve its ejector performance. Firstly, a two-dimensional surface design is implemented for the ejector exhaust system, followed using CFD software to analyze the pumping characteristics. Additionally, an infrared radiation intensity prediction method is employed to evaluate the infrared characteristics of the engine's ejector exhaust system. Furthermore, a multivariable control method for the total pressure ratio of the secondary and primary streams is proposed, and control laws for the engine in cruise state are formulated. Finally, the effectiveness of the proposed control method is validated through numerical simulations. The results demonstrate that the control method effectively reduces significant fluctuations of the engine's infrared radiation intensity during flight missions while maintaining the desired engine thrust.</p>

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Study on Ejector Characteristics and Control Law for Turbofan Engine with Fan Ejector Nozzle

  • 期刊论文

  • 发表日期：

    2025年9月18日

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  • Haoying Chen,
  • Yifan Wang,
  • Kang He,
  • Qiangang Zheng,
  • Jiayi Luo,
  • Haibo Zhang

摘要

To study the ejector characteristics of a turbofan engine with a fan ejector nozzle during high-altitude flight, this paper analyzes the ejector characteristics of the engine and proposes a new control law to improve its ejector performance. Firstly, a two-dimensional surface design is implemented for the ejector exhaust system, followed using CFD software to analyze the pumping characteristics. Additionally, an infrared radiation intensity prediction method is employed to evaluate the infrared characteristics of the engine's ejector exhaust system. Furthermore, a multivariable control method for the total pressure ratio of the secondary and primary streams is proposed, and control laws for the engine in cruise state are formulated. Finally, the effectiveness of the proposed control method is validated through numerical simulations. The results demonstrate that the control method effectively reduces significant fluctuations of the engine's infrared radiation intensity during flight missions while maintaining the desired engine thrust.