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Thermodynamic analysis of a novel precooled supersonic turbine engine based on aircraft/engine integrated optimal design

Author

Listed:
  • Cai, Changpeng
  • Chen, Haoying
  • Fang, Juan
  • Zheng, Qiangang
  • Chen, Cheng
  • Zhang, Haibo

Abstract

Aircraft and precooled engine efficient matching work is a key issue in the thermal cycle design of precooled engines, to solve this problem, an aircraft/precooled turbine engine integrated design method considering the fuel precooling impact mechanism is newly proposed. The impact of n-decane, ammonia, and hydrogen fuel precooling on aircraft design parameters and engine thrust requirements is revealed. Furthermore, a parameter optimal design method for fuel precooled engine is carried out to satisfy the multi-objective performance requirements of high specific thrust, low fuel consumption, high exergy efficiency, and low weight. The simulation results show that the n-decane fuel precooled engine reduces the takeoff weight of the aircraft by 4.23% and the fuel load by 11.6%, which has a better comprehensive performance than that of ammonia and hydrogen. Ammonia fuel has the maximum precooling heat sink and performance improvement space. After multi-objective optimization, it increases the maximum specific thrust by 7.3%, reduces fuel consumption by 2.2%, and improves the engine exergy efficiency by 2.7%, with only a 1.3% increase in rotating component weight. Ammonia and n-decane dual fuel precooling can achieve complementary advantages of high combustion heat value and high precooling heat sink, making it an ideal precooled engine scheme.

Suggested Citation

  • Cai, Changpeng & Chen, Haoying & Fang, Juan & Zheng, Qiangang & Chen, Cheng & Zhang, Haibo, 2023. "Thermodynamic analysis of a novel precooled supersonic turbine engine based on aircraft/engine integrated optimal design," Energy, Elsevier, vol. 280(C).
    • Handle: RePEc:eee:energy:v:280:y:2023:i:c:s0360544223015554
    DOI: 10.1016/j.energy.2023.128161
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    References listed on IDEAS

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