Numerical investigation of combustion flow fields in low heating value fuel cannular combustor
|更新时间:2026-07-07
|
Numerical investigation of combustion flow fields in low heating value fuel cannular combustor
Vol. 28, Issue 2, (2013)
作者机构:
1. 南京航空航天大学 能源与动力学院,南京,210016
2. 中国航空工业集团公司 中国燃气涡轮研究院,四川 江油,621700
3. 南京理工大学 机械工程学院,南京,210094
作者简介:
基金信息:
DOI:
CLC:
Published:2013
稿件说明:
移动端阅览
HE Min, CAI Wen-xiang, ZHAO Jian-xing, et al. Numerical investigation of combustion flow fields in low heating value fuel cannular combustor[J]. 2013, 28(2).
DOI:
HE Min, CAI Wen-xiang, ZHAO Jian-xing, et al. Numerical investigation of combustion flow fields in low heating value fuel cannular combustor[J]. 2013, 28(2).DOI:
Numerical investigation of combustion flow fields in low heating value fuel cannular combustor
Combustion flow fields of a cannular combustor were calculated using arbitrary curvilinear coordinates for two low heating gas fuels with different chemical species.One fuel was natural gas mixed into nitrogen
and the other fuel was carbon monoxide.Predictions indicate that the chemical reaction rates of low heating gas fuels are directly related to chemical species. The combustion efficiency of the gas fuel carbon monoxide is higher than that of nature gas mixed into nitrogen. The effects of different chemical species of low heating gas fuels on combustion efficiency and outlet temperature are considerable.Therefore
it is very important to choose appropriate low heating gas fuels.The calculated combustion efficiency and outlet temperature distributions are in reasonable agreement with the measurements.These comparisons show that the mathematical models and numerical method are reasonable
and the numerical procedure is reliable and may be applied to the optimization design of the low heating value fuel cannular combustor.
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
Combustion performance of triple swirler combustor in ignition stage
Numerical simulation of spoiler ring’s effect on combustion and flow of powdered rocket motor
Experiments on influence of oxygen gas intake plan on performance of Mg/CO2 engine
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