Operational mode transition in a rotating detonation engine
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2020 21(9):721-733
721
Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: [email protected]
Operational mode transition in a rotating detonation engine∗ Zhi-di LEI1 , Zheng-wu CHEN2 , Xiao-quan YANG†‡1 , Jue DING†‡1 , Pei-fen WENG1 1Shanghai
Key Laboratory of Mechanics in Energy Engineering, Shanghai Institute of Applied Mathematics and
Mechanics, School of Mechanics and Engineering Science, Shanghai University, Shanghai 200072, China 2Key
Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000, China † E-mail:
[email protected]; [email protected]
Received July 23, 2019; Revision accepted Jan. 21, 2020; Crosschecked July 15, 2020
Abstract: The relationship between the number of detonation waves and the evolution process of the flow field in a rotating detonation engine was investigated through a numerical analysis. The simulations were based on the Euler equation and a detailed chemical reaction model. In the given engine model, the flow-field evolution became unstable when a single detonation wave was released. New detonation waves formed spontaneously, changing the operational mode from single-wave to four-wave. However, when two or three detonation waves were released, the flow field evolved in a quasi-steady manner. Further study revealed that the newly formed detonation wave resulted from an accelerated chemical reaction on the contact surface between the detonation products and the reactive mixture. To satisfy the stable propagation requirements of detonation waves, we proposed a parameter called NL , which can be compared with the number of detonation waves in the combustor to predict the evolution (quasi-stable or unstable) of the flow field. Finally, we verified the effectiveness of NL in a redesigned engine. This study may assist the operational mode control in rotating detonation engine experiments. Key words: Rotating detonation engine; Chemical reaction; Multiple detonation waves; Stability https://doi.org/10.1631/jzus.A1900349 CLC number: V231
1 Introduction Unlike ordinary isobaric combustion in traditional aerospace engines, detonation is a chemical reaction induced by a shock wave. Owing to its fast chemical reaction rate, detonation approximates a constant-volume process in which the entropy of det‡ *
Corresponding author
Project supported by the National Natural Science Foundation of China (No. 11702329), the Open Project Program of the Key Laboratory of Aerodynamic Noise Control of China Aerodynamics Research and Development Center (CARDC) (No. ANCL20180103), the CARDC Fundamental and Frontier Technology Research Fund (No. PJD20180143), and the Open Project Program of Rotor Aerodynamics Key Laboratory (No. RAL20180403), China ORCID: Zhi-di LEI, https://orcid.org/0000-0003-2520-8302 c Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2020
onation is less than that of isobaric combustion. Fo
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