Application study on plasma ignition in aeroengine strut–cavity–injector integrated afterburner

Li FEI (费力); Bingbing ZHAO (赵兵兵); Xiong LIU (刘雄); Liming HE (何立明); Jun DENG (邓俊); Jianping LEI (雷健平); Zichen ZHAO (赵子晨); Zhiyu ZHAO (赵志宇)

doi:10.1088/2058-6272/ac183c

Plasma Science and Technology > 2021 > 23(10): 105504. > DOI: 10.1088/2058-6272/ac183c

Li FEI (费力), Bingbing ZHAO (赵兵兵), Xiong LIU (刘雄), Liming HE (何立明), Jun DENG (邓俊), Jianping LEI (雷健平), Zichen ZHAO (赵子晨), Zhiyu ZHAO (赵志宇). Application study on plasma ignition in aeroengine strut–cavity–injector integrated afterburner[J]. Plasma Science and Technology, 2021, 23(10): 105504. DOI: 10.1088/2058-6272/ac183c

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Application study on plasma ignition in aeroengine strut–cavity–injector integrated afterburner

¹ Air Force Engineering University, Xi'an 710038, People's Republic of China
² Aviation University of Air Force, Changchun 130022, People's Republic of China

Funds: This work is supported by National Natural Science Foundation of China (Nos. 51806245 and 51436008) and the Science and Technology Projects of Shaanxi Province (No. 2020JM-349).

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Received Date: April 05, 2021
Revised Date: July 23, 2021
Accepted Date: July 25, 2021

Graphical Abstract

Abstract

Abstract

To increase the thrust-weight ratio in next-generation military aeroengines, a new integrated afterburner was designed in this study. The integrated structure of a combined strut–cavity–injector was applied to the afterburner. To improve ignition characteristics in the afterburner, a new method using a plasma jet igniter was developed and optimized for application in the integrated afterburner. The effects of traditional spark igniters and plasma jet igniters on ignition processes and ignition characteristics of afterburners were studied and compared with the proposed design. The experimental results show that the strut–cavity–injector combination can achieve stable combustion, and plasma ignition can improve ignition characteristics. Compared with conventional spark ignition, plasma ignition reduced the ignition delay time by 67 ms. Additionally, the ignition delay time was reduced by increasing the inlet velocity and reducing the excess air coefficient. This investigation provides an effective and feasible method to apply plasma ignition in aeroengine afterburners and has potential engineering applications.
- integrated afterburner,
- aeroengine,
- plasma ignition,
- ignition process,
- ignitioncharacteristics

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References (40)

References

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