Experimental investigation for temperature and emissivity by flame emission spectrum in a cavity of rocket based combined cycle combustor chamber

扫码查看

原文链接

万方数据
维普

外文摘要：Flame temperature and spectral emissivity were the important parameters characterizing the sufficient degree of fuel combustion and the particle radiative characteristics in the Rocket Based Combined Cycle(RBCC)combustor.To investigate the combustion characteristics of the complex supersonic flame in the RBCC combustor,a new radiation thermometry combined with Levenberg-Marquardt(LM)algorithm and the least squares method was proposed to measure the temperature,emissivity and spectral radi-ative properties based on the flame emission spectrum.In-situ measurements of the flame temperature,emissivity and spectral radiative properties were carried out in the RBCC direct-connected test bench with laser-induced plasma combustion enhancement(LIPCE)and without LIPCE.The flame average temperatures at fuel global equivalence ratio(α)of 1.0b and 0.6 with LIPCE were 4.51％and 2.08％higher than those without LIPCE.The flame combustion oscillation of kerosene tended to be stable in the recirculation zone of cavity with the thermal and chemical effects of laser induced plasma.The differ-ences of flame temperature at α=1.0b and 0.6 were 503 K and 523 K with LIPCE,which were 20.07％and 42.64％lower than those without LIPCE.The flame emissivity with methane assisted ignition was 80.46％lower than that without methane assisted ignition,due to the carbon-hydrogen ratio of kerosene was higher than that of methane.The spectral emissivities at 600 nm with LIPCE were 1.25％,22.2％,and 4.22％lower than those without LIPCE at α=1.0a(with methane assisted ignition),1.0b(without methane assisted ignition)and 0.6.The effect of concentration in the emissivity was removed by normalization to analyze the flame radiative properties in the RBCC combustor chamber.The maximum differences of flame normalized emissivity were 50.91％without LIPCE and 27.53％with LIPCE.The flame radiative properties were stabilized under the thermal and chemical effects of laser induced plasma at a=0.6.

外文关键词：

Rocket-based combined-cycleSupersonic combustionFlame temperature measurementEmissivityLaser induced plasma combustionenhancement

作者：

Weiguang Cai、Shu Zheng、Yan Wang、Bing Liu、Shaohua Zhu、Li Zhao、Qiang Lu

展开 >

作者单位：

National Engineering Research Center of New Energy Power Generation,North China Electric Power University,Beijing 102206,China

Science and Technology on Combustion,Internal Flow and Thermal-structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China

基金：

National Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaFundamental Research Funds for the Central UniversitiesNatural Science Foundation of Jiangsu ProvinceProofof-Concept Project of Zhongguancun Open Laboratory

项目编号：

5227618552276189519760572021MS126BK2023120920220981113

出版年：

2024

DOI：

10.1016/j.dt.2024.04.019

防务技术

中国兵工学会

防务技术

CSTPCD

影响因子：0.358

ISSN：2214-9147

年,卷(期)：2024.39(9)