A micro annular combustor was designed based on research both inland and oversea
and simulated the combustion in the annual combustor.And then
according to the simulation result
the design of combustor was optimized and re-computed.All case including chemical reaction
heat radiation
evaporating of fuel and secondary breakup of spray was comprised in numerical simulation
the boundary condition of inlet was gained through computing and the parameter of spray was gained through experiment.The result of computation can reflect the reality case exactly.At last
the numerical simulation result of two combustor was compared
the result indicate the optimized design is reasonable
fuel can combusted sufficiently in chamber and the performance parameter is satisfied the design requirement.All data can provide numerical foundation for better performance in combustion chamber.
Simulation method of short crack propagation in turbine disks based on crystal plasticity
Numerical simulation of internal flow field in gas generator of fire extinguishing bomb
Numerical simulation of light-craft effects onlaser supported donation wave with gas-liquid two phase propellant
Low-Reynolds-number wake flows of a triangular prism
Influence of combustor shape on self-ignition in solid fuel scramjet
Related Author
Ping ZHANG
Shan LU
Xin JING
Mao YANG
Zhongbing LUO
Rongxin ZHOU
Yunfeng LI
Kangqing DENG
Related Institution
School of Power and Energy,Northwestern Polytechnical University
Nondestructive Testing and Evaluation Laboratory, Dalian University of Technology
College of Civil Engineering, Hefei University of Technology
Key Laboratory of Aerospace Chemical Power Technology, Hubei Institute of Aerospace Chemical Techologh, China Aerospace Science and Technology Corporation,Xiangyang Hubei
Hubei Institute of Aerospace Chemistry Technology, China Aerospace Science and Technology Corporation,Xiangyang Hubei