Development and Preliminary Validation of A Thermal Analysis Method for Hydrocarbon Regenerative-cooled Supersonic Combustor

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	Development and Preliminary Validation of A Thermal Analysis Method for Hydrocarbon Regenerative-cooled Supersonic Combustor
	Lu Y(陆阳); Wang XZ(王新竹); Li L(李龙); Cheng D(程迪); Yuan T(袁涛); Yao W(姚卫); Fan XJ(范学军)
	2015-07
会议名称	20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
会议日期	6-9 July, 2015
会议地点	Glasgow, Scotland
关键词	hydrocarbons Combustors cooling heat transfer
中文摘要	In this research, a thermal analysis method has been developed to analyze the heat transfer process associated with endothermic hydrocarbon regenerative-cooled structure of a combustor. The complex heat transfer processes relevant to such cooling structure exposed in severe heat environment are modeled by three coupled processes: hot side boundary condition specification, flow and convective heat transfer of fuel within cooling channels and heat transfer in combustor structure with cooling channels embeded. To speed up the simulation process while achieving good accuracy, efforts are made in several aspects: first, hot side heat environment of combustor is obtained either by measurement results from upgraded heat flux sensors developed based on the principle of Gardon heat-flux gauge or by quasi 1-D analysis of combustor using static pressure distribution as input; second, to quantitatively describe flow and heat transfer behavior of hydrocarbon coolant when heavy cracking happens, a five-component surrogate model is developed and together used with a thermal cracking model consisting of 18 species and 24 reactions; third, to account for multiple effects happening in redistribution channels, a special method for flow rate redistribution prediction is developed based on characteristic time scale analysis. The validness of this integrated analysis method is tested by comparing simulation results with measurement data from lab tests of a supersonic model combustor. The overall correctness of exit coolant fuel temperature and wall temperature distribution prediction is within 5% and 10% separately. The fast speed and decent accuracy of this method developed make it very promising to be put into use for hydrocarbon regenerative-cooling analysis. © 2015, AIAA American Institute of Aeronautics and Astronautics. All rights reserved.
收录类别	EI
语种	英语
内容类型	会议论文
源URL	[http://dspace.imech.ac.cn/handle/311007/58427]
专题	力学研究所_高温气体动力学国家重点实验室
推荐引用方式 GB/T 7714	Lu Y,Wang XZ,Li L,et al. Development and Preliminary Validation of A Thermal Analysis Method for Hydrocarbon Regenerative-cooled Supersonic Combustor[C]. 见:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Glasgow, Scotland. 6-9 July, 2015.