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

Zhenghao Yang, Yang Du, Qi Geng, Xu Gao, Haonan Er, Yuanfei Liu and Guangyu He ()
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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

Energies, 2022, vol. 15, issue 21, 1-20

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.

Keywords: power attenuation; high-efficiency hybrid cycle rotary engine; hydrogen doping; single-zone model; high-altitude performance (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2022
References: View references in EconPapers View complete reference list from CitEc
Citations: View citations in EconPapers (2)

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