Numerical investigation on non-premixed rotating detonation with the induced forward motion shock wave

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-04-04 DOI:10.1016/j.ast.2025.110187

Zhipeng Sun, Yue Huang, Han Peng, Sijia Gao, Anjia Song

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Abstract

Three-dimensional (3D) numerical simulations were conducted in a non-premixed rotating detonation combustor with an axial inlet duct to study the flow characteristics of the strong motion shock wave induced by the detonation. A transient, implicit density-based solver was applied to solve the 3D unsteady Navier-Stokes equations governing the flow, and led to the identification of the single-wave propagation of the detonation wave and the structure of the forward spiral shock wave. The fresh fuel-filled zone was classified into partial and ideal mixed zones, as well as a fuel-rich zone. The detonation wavefront exhibited folding that consisted of the detonation wave of the trailing edge, the main detonation wave, and the secondary detonation wave. In detail, the analysis also focused on the impact of the forward shock wave on both the air intake into the combustion chamber and the mixing of the reactants. The results showed that when the detonation wave temporarily blocked the passage of fuel, the suppressed effect of the forward shock wave on the incoming air was more notable. Equations were derived to establish correlations between the velocity and angle of the forward shock wave in the axial inlet duct and the intensity of the detonation wave, as well as the thermal parameters of the incoming flow. The relationship was validated based on comparisons under different incoming flow temperatures. Finally, a summary was provided for the fundamental structure of the flow field featured by the coupling of a rotating detonation wave and a forward shock wave.

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诱导正向激波非预混旋转爆轰的数值研究

在带轴向进气道的非预混旋转爆轰燃烧室中进行了三维数值模拟，研究了爆轰引起的强运动激波的流动特性。利用瞬态隐式密度求解器求解了三维非定常Navier-Stokes方程，得到了爆震波的单波传播和前向螺旋激波的结构。新燃料填充区分为部分混合区和理想混合区，以及富燃料区。爆轰波前呈现褶皱，由尾缘爆轰波、主爆轰波和次爆轰波组成。详细分析了前向激波对燃烧室进气口和反应物混合的影响。结果表明，当爆震波暂时阻断燃料通道时，前向激波对来风的抑制作用更为显著。推导了轴向进气道内前向激波的速度、角度与爆震波强度以及来流热参数之间的关系式。通过对不同来流温度下的对比，验证了这一关系。最后，总结了旋转爆震波与前向激波耦合流场的基本结构。

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来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.