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Performance Analysis of a Hydrogen-Doped High-Efficiency Hybrid Cycle Rotary Engine in High-Altitude Environments Based on a Single-Zone Model

Author

Listed:
  • Zhenghao Yang

    (Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China)

  • Yang Du

    (Institute of Aero-Engine, School of Mechanical Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Qi Geng

    (Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China)

  • Xu Gao

    (Institute of Aero-Engine, School of Mechanical Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Haonan Er

    (Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China)

  • Yuanfei Liu

    (Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China)

  • Guangyu He

    (Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China)

Abstract

The power attenuation of internal combustion engines in high-altitude environments restricts the performance of unmanned aerial vehicles. Herein, a single-zone model of a hydrogen-doped high-efficiency hybrid cycle rotary engine that considers high-altitude environments was proposed. The indicated values for power, thermal efficiency, and specific fuel cost were used to evaluate the power performance, energy conversion efficiency, and economic performance of the engine, respectively. Then, the effects of adjusting the hydrogen fraction, ignition angle, and rotational speed on high-altitude performance were analyzed. The results showed that high-altitude environments prolonged combustion duration and reduced in-cylinder pressure, thereby causing power attenuation; however, increasing the hydrogen fraction can increase the indicated power. At an altitude of 6 km, the indicated power with a hydrogen fraction of 0.3 was approximately 20.7% higher than that obtained with pure gasoline. The ignition angle and hydrogen fraction corresponding to the optimal indicated thermal efficiency increased with increasing altitude. At an altitude of 6 km, the indicated thermal efficiency reached its maximum (36.4%) at an ignition angle of 340 [CA°] and a hydrogen fraction of 0.15. At high altitudes, rotational speeds below 6000 rpm and ignition angles of 340–345 [CA°] were beneficial in reducing indicated specific fuel costs.

Suggested Citation

  • Zhenghao Yang & Yang Du & Qi Geng & Xu Gao & Haonan Er & Yuanfei Liu & Guangyu He, 2022. "Performance Analysis of a Hydrogen-Doped High-Efficiency Hybrid Cycle Rotary Engine in High-Altitude Environments Based on a Single-Zone Model," Energies, MDPI, vol. 15(21), pages 1-20, October.
    • Handle: RePEc:gam:jeners:v:15:y:2022:i:21:p:7948-:d:953921
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    References listed on IDEAS

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    1. Oh, Sechul & Park, Cheolwoong & Nguyen, Ducduy & Kim, Seonyeob & Kim, Yongrae & Choi, Young & Lee, Jeongwoo, 2021. "Investigation on the operable range and idle condition of hydrogen-fueled spark ignition engine for unmanned aerial vehicle (UAV)," Energy, Elsevier, vol. 237(C).
    2. Lev Finkelberg & Alexander Kostuchenkov & Andrei Zelentsov & Vladimir Minin, 2019. "Improvement of Combustion Process of Spark-Ignited Aviation Wankel Engine," Energies, MDPI, vol. 12(12), pages 1-11, June.
    3. Francesconi, Marco & Antonelli, Marco, 2017. "A numerical model for the prediction of the fluid dynamic and mechanical losses of a Wankel-type expansion device," Applied Energy, Elsevier, vol. 205(C), pages 225-235.
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