A5079723796- Combustion and Detonation Processes
- Fire dynamics and safety research
- Computational Fluid Dynamics and Aerodynamics
- Risk and Safety Analysis
- Combustion and flame dynamics
- Energetic Materials and Combustion
- Rocket and propulsion systems research
- Plasma and Flow Control in Aerodynamics
- Electromagnetic Launch and Propulsion Technology
- Nuclear Issues and Defense
- Cassava research and cyanide
- Genetics and Plant Breeding
- Guidance and Control Systems
- Gas Dynamics and Kinetic Theory
- Genetic and Environmental Crop Studies
- Particle Dynamics in Fluid Flows
- Aerodynamics and Acoustics in Jet Flows
- Fluid Dynamics and Turbulent Flows
Nanjing University of Aeronautics and Astronautics
2022-2025
Ministry of Industry and Information Technology
2022
Nanjing University of Science and Technology
2016-2020
Washington University in St. Louis
2019
Chinese Academy of Tropical Agricultural Sciences
2017
A reverse-flow combustor has a larger liner surface area due to airflow turning, which complicates flow and cooling control, particularly heat transfer efficiency. Effective management is essential for maintaining uniform temperature distribution preventing thermal gradients. This study explores the impact of axial position diameter primary holes on performance dynamics. Results indicate that as move toward dome, recirculation vortex size decreases, leading insufficient fuel mixing,...
Abstract To enable stable performance in a rotating detonation combustor (RDC) operating with aviation fuel and air mixtures, this study develops novel RDC configuration for hydrocarbon/oxidizer systems. The experimental investigation focuses on characterizing both non-reactive flow patterns high-energy combustion phenomena under diverse supply parameters, employing premixed injection strategies initial validation. Under gas conditions, wave (RDW) mode was successfully established. pressure...
Abstract Cassava ( Manihot esculenta Crantz) is an important tropical starchy root crop that adapted to drought but extremely cold sensitive. A cold-tolerant, high-quality, and robust supply of cassava urgently needed. Here, we clarify genome-wide distribution classification CCGG hemi-methylation full-methylation, detected 77 much candidate QTLs epi for stress 103 storage quality yield in 186 population, generated by crossing two non-inbred lines with female parent KU50 male SC124 (KS...
Centrally staged combustion technique is often used in the military high-temperature-rise combustor. The pilot-stage structure affects flow characteristics centrally combustor, which further performance of ignition, combustion, and emission aero-engines. In order to increase capacity swirler, swirler with a non-rotating channel was designed. this work, influences on combustor are investigated. fields combustors different swirl numbers (0.44, 0.60, 0.71) analyzed by large eddy simulation...
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Efficient initiation of oblique detonation waves (ODWs) is crucial for optimizing the performance wave engines. A novel approach proposed enhancing ODW through expansion in this research. Validation wave-reinforced method conducted via numerical simulations employing multi-species reactive Euler equations and a pressure-dependent reaction mechanism. Results demonstrate significant reduction length ODWs with addition an ahead wedge, contrasting absence on wedge lacking wave. theoretical...
The muzzle flow with and without precursor is simulated. AUSM+ (Advection Upstream Splitting Method) scheme adopted to capture the shock waves in flow. combustion considered using detailed reaction kinetics model. model consists of 9 species 12 reactions. Besides, an inert added trace gas. By analyzing motion gas, interaction gas propellant obtained. comparing results flow, influence on discussed detail. present makes jet boundary more complex increases intensity combustion.
Abstract The reflection of a supersonic propellant gas jet always happens during the firing weapon system aircraft. induces complex non‐premixed shock induced combustion. It is great importance to investigate initiation mechanism combustion in gas. vital for design any suppression method secondary To reflected jet, solid model and numerical based on compressible multispecies Navier‐Stokes equations are established. A detailed reaction consisting 9 species 12 reactions utilized Based models,...
To realize the stable operation of liquid kerosene/air rotating detonation combustor and explore its fuel mixing atomization distribution in cold state combustion characteristics hot state, this paper, four kinds structures injection are designed, which pairwise combination between direct modes 1 4 side wall holes 2 3 oil splashing ring (1, 2, represent different radial positions from outer to inner wall). Euler-Lagrange algorithm is used numerically simulate states combustor. The results...