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Publishing Language: Chinese

Experiment on afterburner combustion efficiency based on self-excited sweeping nozzle

Shiqi WANG1( ), Quan WEN1, Zhigang JIA1, Yixin CHENG1,2, Lin LI1, Chi ZHANG2, Weiye HUO3, Liang MA4
Aero Engine Academy of China, Aero Engine Corporation of China, Beijing 101304, China
Research Institute of Aero-Engine, Beihang University, Beijing 100191, China
School of Aeronautics and Astronautics, North China Institute of Aerospace Engineering, Langfang 065000, China
Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China
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Abstract

To prove the feasibility of applying the self-excited sweeping nozzle in the afterburner, and the effectiveness of high frequency dynamic sweeping fuel injection methods for improving the efficiency of afterburner combustion, this study designed a fuel spray bar integrated with the self-excited sweeping nozzles, tested its basic working characteristics, such as flow rate, frequencyand sweeping angle, and further compared these characteristics with the plain-orifice spray bar. Then, based on the rectangular afterburner test rig, under the same test conditionsand the fuel-to-air ratio range, the overall combustion efficiencies are testedand the dynamic wall pressure pulsation information is monitored, employing the plain-orifice spray barand self-excited sweeping spray bar respectively. The results show that multiple self-sweeping nozzles can be integrated into the spray bar with the diameter limitation of 10mm. the flow capability of the self- excited sweeping spray bar is increased by 23%, compared to the plain-orifice spray bar with the equivalent geometric flow area. For the nozzles in the same spray bar, their operating frequencyand sweeping angle responses to the pressure drop are basically the sameand have good consistency. The afterburner combustion efficiency is improved by 3.7%, by employing the self-excited sweeping spray bar, and no dynamic pressure pulsation frequency is detected which is the same or close to the operating frequency of self-excited sweeping nozzle, indicating that high frequency dynamic sweeping fuel injection has no direct impact on the flame thermoacoustic oscillation modeand large scale shedding vortex structure downstream the flameholder.

CLC number: V231.2;V235.1 Document code: A Article ID: 1000-6893(2025)02-130621-14

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Acta Aeronautica et Astronautica Sinica

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Cite this article:
WANG S, WEN Q, JIA Z, et al. Experiment on afterburner combustion efficiency based on self-excited sweeping nozzle. Acta Aeronautica et Astronautica Sinica, 2025, 46(2). https://doi.org/10.7527/S1000-6893.2024.30621

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Received: 29 April 2024
Revised: 13 May 2024
Accepted: 31 May 2024
Published: 25 January 2025
© 2025 The Journal of Acta Aeronautica et Astronautica Sinica