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Key Technology and Experimental Results of the Clean Air Heated Facility for Supersonic Combustion

Chinese Journal of Mechanical Engineering 2009年第5期22卷 760-765页

作者： ZHONG Zipeng SONG Wenyan le jialing School of Power and Energy Northwestern Polytechnical University Xi ＇an 7100 72 China

The scramjet, which is the propulsion of hypersonic vehicle, has become the focus in many military developed countries. The ground tests play an important role in the research of scramjet. There is defect of test medium contamination （the thermochemical characteristic of the ground test medium is different from that of the flight medium） in existing ground test facilities for scramjet combustor experiment. To solve the problem of test medium contamination, the first clean air heated facility of China for scramjet combustor experiment is designed. The key technology of designing the clean air heated facility is summarized. By using bypass duct, combustor model is protected from high temperature. To reduce the switching time between main duct and bypass duct, solenoid valve and water-cooled system were used. Having centrosymmetric structure, the heat radiating area of the facility and heat loss of the facility are much lower than others. Clean air heated facility is adopted to conduct experiment, which is the first experiment of China in clean air inflow, research on hydrogen-fueled and ethylene-fueled ignition and combustion for scramjet combustor at different equivalence ratio. Successful ignition and sustained combustion of hydrogen has been achieved. Successful ethylene ignition and sustained main stream combustion is achieved with normal fuel injection and taking hydrogen as pilot flame. Experiment result shows that the wall pressure of combustor model rises when the equivalence ratio of hydrogen rises. As the wall pressure of combustor model rises, the pressure disturbance influences the shock train in the upstream.

关键词： scramjet clean air resistance heater combustion experiment

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面向内流的激波/边界层湍流模型数据同化及应用

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推进技术 2024年第8期45卷 44-55页

作者：杨茂桃郭明明田野易淼荣乐嘉陵张华西南科技大学信息工程学院四川绵阳621010 中国空气动力研究与发展中心四川绵阳621000

为研究压缩拐角激波/边界层干扰问题和机器学习方法在湍流模型参数辨识中的有效性,提出一种面向内流的激波/边界层湍流模型数据同化方法,以Kriging代理模型传播参数不确定量化过程,基于贝叶斯框架构建似然函数作为评判标准,最后利用粒... 详细信息

为研究压缩拐角激波/边界层干扰问题和机器学习方法在湍流模型参数辨识中的有效性,提出一种面向内流的激波/边界层湍流模型数据同化方法,以Kriging代理模型传播参数不确定量化过程,基于贝叶斯框架构建似然函数作为评判标准,最后利用粒子群优化算法近似获取参数的最大似然估计并进行参数验证。结果表明,通过校准大角度(24°)压缩拐角获取的湍流模型参数,可以应用到相同条件下相对较小的小角度(20°,16°和8°)压缩拐角,获取的壁面压力、摩阻系数和速度剖面均与试验值基本吻合。在Ma=2.85下校准的壁面压力,均方根误差由60.29%下降到16.56%。将大角度下获取的参数应用到Ma=2.9和不同的入射边界层厚度的条件下,获取的壁面压力和速度剖面仍与试验值基本吻合,验证了小范围马赫数内湍流模型参数的适用性。

关键词：激波/边界层干扰数据同化 SST湍流模型贝叶斯优化参数辨识普适性分析

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Design and experimental study of a practical Osculating Inward Cone Waverider Inlet

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Chinese Journal of Aeronautics 2016年第6期29卷 1582-1590页

作者： He Xuzhao Zhou Zheng Qin Si Wei Feng le jialing Science and Technology on Scramjet Laboratory Hypervelocity Aerodynamics Institute of CARDC

A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet（OICWI）. A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a total contraction ratio of 4.61 and inner contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number（Ma） of 4.0, 3.5 and 3.0 respectively. The experimental results show that the OICWI has high flow capture ratio and compression abilities. It can self-start at Ma= 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma= 4.0, and Angle of Attack（AOA） 0°. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airbreathing hypersonic vehicles.

关键词： Inlet Integration design Inward turning cone Waverider Wind tunnel experiment

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Experimental research of air-throttling ignition for a scramjet at Ma 6.5

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Chinese Journal of Aeronautics 2017年第3期30卷 932-938页

作者： Weixin DENG jialing le Shunhua YANG Wanzhou ZHANG Ye TIAN Science and Technology on Scramjet Lab Hypersonies Aerodynamics Institute China Aerodynamics Research and Development Center Mianyang 621000 China

An experimental investigation on ignition characteristics with air-throttling in an ethylene-fueled scramjet under flight Ma 6.5 conditions was *** dynamic process of air-throttling ignition was explored *** influences of throttling parameters,i.e.,throttling mass rate and duration,were *** the throttling mass rate was 45% of the inflow mass rate,ambient ethylene could be ignited *** delay time from ignition to throttling was about 45–55 *** was a threshold of throttling duration under a certain throttling mass *** was shorter than 100 ms when the throttling mass rate was 45%.While a 45%throttling mass rate would make the shock train propagate upstream to the isolator entry in about10–15 ms,four lower throttling mass rates were tested,including 30%,25%,20%,and 10%.All of these throttling mass rates could ignite ***,combustion performances varied with them.A higher throttling mass rate made more ethylene combust and produced higher wall *** these experiments,some aspects of the relationships between ignition,flame stabilization,combustion efficiency,and air-throttling parameters were brought to *** results could also be a benchmark for CFD validation.

关键词： Air-throttling Combustion Flame stabilization Ignition Scramjet Shock

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超燃冲压发动机燃烧室流场超分辨率重建

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推进技术 2024年第1期45卷 174-184页

作者：陈皓郭明明田野乐嘉陵张华岳茂雄西南科技大学信息工程学院四川绵阳621000 中国空气动力研究与发展中心四川绵阳621000

超声速燃烧室受限空间内复杂流场波系结构的获取受到光学测量装置精度的制约。为提升流场时空分辨率特征,本文应用中国空气动力研究与发展中心地面脉冲燃烧风洞获取的试验数据,在发动机入口马赫数2.5的条件下,构建了6种不同当量比下基... 详细信息

超声速燃烧室受限空间内复杂流场波系结构的获取受到光学测量装置精度的制约。为提升流场时空分辨率特征,本文应用中国空气动力研究与发展中心地面脉冲燃烧风洞获取的试验数据,在发动机入口马赫数2.5的条件下,构建了6种不同当量比下基于压力数据重构的燃烧室流场低分辨率图像数据集,研究了三种提高图像分辨率的方法来提升超燃冲压发动机燃烧室流场重构图像的分辨率。结果表明,本文所提出的流场超分辨率稠密网络(Flow-field Super-Resolution Dense Network,FSRDN)、流场超分辨率生成对抗网络(Flow-field Super-Resolution Generative Adversarial Network,FSRGAN)、传统的双三次插值法(Bicubic interpolation,Bicubic)对流场图像分辨率都提高了4^(2)倍。FSRDN网络所得流场图像结果的峰值信噪比(Peak Signal-to-Noise Ratio,PSNR)、相关性系数(Correlation coefficient,CORR)、感知指数(Perceptual Index,PI)指标均优于双三次插值法,但实际图像存在过于平滑的现象。FSRGAN网络所得流场结果消除了图像平滑现象,使流场图像的细节更加丰富,大幅度优化了PI指标,对燃烧室内的剪切层、斜激波、分离激波等主要波系结构的清晰度有了极大的增强作用。

关键词：超燃冲压发动机燃烧室双三次插值超分辨率生成对抗网络

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Influence of contaminations on combustion kinetics in hydrogen-fueled engine

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Chinese Science Bulletin 2009年第8期54卷 1317-1321页

作者： LIU WeiXiong HE Wei LI HongBin LI XiangYuan le jialing School of Power and Energy Northwest Polytechnical University Xi'an 710072 China Aerodynamics Research and Development Center Mianyang 621000 China College of Chemical Engineering Sichuan University Chengdu 610065 China

In this work,we investigate the combustion of hydrogen fuel through the wind tunnel *** kinds of fuel,the pure hydrogen and the hydrogen-ethene mixture,have been chosen to heat the oxygen-enriched *** is found that the stable pressure in the engine combustor and the thrusts is almost the same in two cases.A valuable feature we revealed is that the heating pattern of hydrogen and ethene mixture leads to a considerable delay of the establishment of the wall pressure in the combustor,compared with the pure hydrogen *** phenomenon implies a longer ignition delay time for the mixture *** shorter ignition delay resulting from the hydrogen heater is attributed to the continuity of chain propagation and the exclusion of the less active C-containing radicals.

关键词：氢燃料发动机燃烧动力学污染物发动机燃烧室点火延迟时间混合物风洞试验供暖模式

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Numerical Simulation of Shock (Blast) Wave Interaction with Bodies

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Communications in Nonlinear Science and Numerical Simulation 1999年第1期4卷 1-7页

作者： jialing le (China Aerodynamics Research and Development Center P.O. Box 211 Mianyang Sichuan China) China Aerodynamics Research and Development Center P.O. Box 211 Mianyang Sichuan China China

Some typical results of computation on the shock (blast) wave interaction (2-D and 3-D) with bodies and its experimental validation in shock tube are summarized, suggestions for improving the numerical method (difference scheme and grid systems),developing 3-D optical quantitative visualization technology and further studying the unsteady turbulent flow are put forward.

关键词： shock wave blast wave numerical simulation

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Flow field reconstruction and shock train leading edge position detection of scramjet isolation section based on a small amount of CFD data

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Advances in Aerodynamics 2022年第1期4卷 599-613页

作者： Hao Chen Ye Tian Mingming Guo jialing le Yuan Ji Yi Zhang Hua Zhang Chenlin Zhang Southwest University of Science and Technology Mianyang621000China China Aerodynamics Research and Development Center Mianyang621000China Shanghai Jiao Tong University Shanghai200240China Shenyang Aircraft Design and Research Institute Shenyang110035China

Scramjet is the main power device of hypersonic vehicles. With the gradual expansion of wide velocity domain, shock wave/shock wave and shock wave/boundary layer are the main phenomena in scramjet isolator. When the leading edge of the shock train is pushed out from the inlet of the isolator, the engine will not start. Therefore, it is very important to detect the flow field structure in the isolator and the leading edge position of the shock train. The traditional shock train detection methods have low detection accuracy and slow detection speed. This paper describes a method based on deep learning to reconstruct the flow field in the isolator and detect the leading edge of the shock train. Under various back pressure conditions, the flow field images of computational fluid dynamics (CFD) data and the corresponding upper and lower wall pressure data were obtained, and a data set corresponding to pressure and flow field was constructed. By constructing and training convolutional neural networks, a mapping model with pressure information as input and flow field image as output is obtained, and then the leading edge position of shock train is detected on the output flow field image. The experimental results show that the average structure similarity (SSIM) between the reconstructed flow field image and the CFD flow field image is 0.902, the average peak signal-to-noise ratio (PSNR) is 25.289, the average correlation coefficient (CORR) is 0.956, and the root mean square error of shock train leading edge detection is 3.28 mm. Moreover, if the total pressure input is appropriately reduced, the accuracy of flow field reconstruction does not decline significantly, which means that the model has a certain robustness. Finally, in order to improve the detection accuracy of the leading edge position, we fine tuned the model and obtained another detection method, which reduced the root mean square error of the detection results to 1.87 mm.

关键词： Scramjet Shock train CFD Convolutional neural network Reconstruction

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Optimization of aero-engine combustion chambers with the assistance of Hierarchical-Kriging surrogate model based on POD downscaling method

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Advances in Aerodynamics 2023年第1期5卷 403-427页

作者： Shuhong Tong Yue Ma Mingming Guo Ye Tian Wenyan Song Heng Wang jialing le Hua Zhang Southwest University of Science and Technology Mianyang 621000China China Aerodynamics Research and Development Center Mianyang 621000China Northwestern Polytechnical University Xi’an 710072China

In view of the long calculation cycle,high processing test and cost of the traditional aero-engine combustion chamber design process,which restricts the engine optimization design cycle,this paper innovatively proposes a surrogate model for the performance of aero-engine combustion chambers based on the POD-Hierarchical-Kriging *** experiments,the predicted results of the POD-Hierarchical-Kriging model are compared and analyzed with the calculated results of the one-dimensional program,and the root mean square error of the predicted values of combustion efficiency and total pressure loss is 0.0064%and 0.1995%,*** accuracy of the POD-Hierarchical-Kriging model is compared with the cubic polynomial model,the basic Kriging model and the Hierarchical-Kriging *** verifies the feasibility and accuracy of the POD-Hierarchical-Kriging model for the prediction of performance of aero-engine combustion *** global sensitivity analysis method is applied to obtain the influence effect of design variables on the ***,a multi-objective optimization method based on the NSGA-II algorithm is studied,and finally the optimal set of Pareto solutions is obtained and analyzed,which can be used to guide the optimal design of aero-engine combustion chambers and accelerate the progress of aero-engine development.

关键词： Aero-engine combustion chamber Surrogate model POD-Hierarchical-Kriging Multi-objective optimization

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Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle

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Journal of Thermal Science 2001年第2期10卷 103-108页

作者： HE Yuanyuan le jialing NI Hongli Computational Aerodynamic Institute, China Aerodynamic Research and Development Center, Mianyang Sichuan 621000, China Computational Aerodynamic Institute China Aerodynamic Research and Development Center Mianyang China

To meet the requirements for the aerodynamic performance and thrust force demanded in hypersonic missions, the integration design of fuselage and. engine must be considered for hypersonic vehicle with a scramjet engine. The configuration of wave rider is a typical hypersonic vehicle shape, whose fore-body can compress the flow in advance and provide uniform flow for the air intake, and whose aft-body,is used as an expansion surface of nozzle. In the present paper, an engineering method is applied to define total aerodynamic characteristics of an approximate wave rider configuration. A finite volume method based on the center of grid is also employed to numerically investigate the outflow pass the same configuration. The flow field details and the aerodynamic characteristics at given conditions are obtained. The evaluation for this configuration may be used as a guide for the hypersonic vehicle experiment.

关键词： hypersonic vehicle integration finite volume method.

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