Rapid Compression Machine Lab

State Key Laboratory of Automotive Safety and Energy | Center For Combustion Energy

Key Project of National Science Foundation of China(NSFC 91542106)

Created: Mar 11, 2018 | 09:37

Description

Detonation mode transition and control under

wide range of temperature and pressure

 

Abstract

Detonation is the key scientific issue in aerospace engines and advanced internal combustion engines under extreme operating condition. This project focuses on the key research plan of fundamental turbulent combustion research faced to engine to investigate the common scientific issues of engine combustion. To investigate the detonation mode transition and control in combustion engines, three key scientific research problems are researched, which include coupling mechanism of shock wave, turbulence and chemical reactions; numerical models and methods of detonation; mode control of engine detonation. Advanced detonation combustion test platform, numerical simulation methods and laser measurement technology are used systematically in this project. The DDT (Deflagration to Detonation Transition) mechanism will be investigated. The coupling mechanism of multiple hot-spots, multiple flame fronts and combustion chamber walls to induce DDT will be studied. The effect of shock, turbulence and its eddy structure on detonation combustion, and its mechanism will be investigated. The control method and its mechanism of suppressing or promoting detonation will be investigated. The detonation mechanism will be revealed. The new combustion model concerning shock wave propagation and its effect on combustion will be developed. The detonation combustion calculation method of adaptive mesh and adaptive chemistry will be studied. The new suppressing methods in internal combustion engine and new promoting methods in detonation engines will be proposed. The combustion theory will be extended. Furthermore, the achievement will guide the independent development of high efficiency and clean combustion engines in China.Detonation is the key scientific issue in aerospace engines and advanced internal combustion engines under extreme operating condition. This project focuses on the key research plan of fundamental turbulent combustion research faced to engine to investigate the common scientific issues of engine combustion. To investigate the detonation mode transition and control in combustion engines, three key scientific research problems are researched, which include coupling mechanism of shock wave, turbulence and chemical reactions; numerical models and methods of detonation; mode control of engine detonation. Advanced detonation combustion test platform, numerical simulation methods and laser measurement technology are used systematically in this project. The DDT (Deflagration to Detonation Transition) mechanism will be investigated. The coupling mechanism of multiple hot-spots, multiple flame fronts and combustion chamber walls to induce DDT will be studied. The effect of shock, turbulence and its eddy structure on detonation combustion, and its mechanism will be investigated. The control method and its mechanism of suppressing or promoting detonation will be investigated. The detonation mechanism will be revealed. The new combustion model concerning shock wave propagation and its effect on combustion will be developed. The detonation combustion calculation method of adaptive mesh and adaptive chemistry will be studied. The new suppressing methods in internal combustion engine and new promoting methods in detonation engines will be proposed. The combustion theory will be extended. Furthermore, the achievement will guide the independent development of high efficiency and clean combustion engines in China.