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NUMERICAL CALCULATIONS OF GASEOUS REACTING FLOWS IN A MODEL OF GAS TURBINE COMBUSTORS

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Chinese Journal of Aeronautics 1991年第1期6卷 26-34页

作者： yan chuanjun, Tang Ming, Zhu Huiling and Sun HuixianNorthwestern Polytechnical University Northwestern Polytechnical Univ

This paper describes the numerical calculations of gaseous reaction flows in a model of gas turbine combustors. The profiles of hydrodynamic and thermodynamic patterns in a three-dimensional combustor model are obtained by solving the governing differential transport equations. The well-established numerical prediction algorithm SIMPLE, the modified k-ε turbulence model and k-ε-g turbulent diffusion flame model have been adopted in computations. The β function has been selected as probability density function. The effect of combustion process on flow patterns has been investigated. The calculated results have been verified by experiments. They are in remarkably good agreement.

关键词： NUMERICAL CALCULATIONS OF GASEOUS REACTING FLOWS IN A MODEL OF GAS TURBINE COMBUSTORS GAS Flow work

Experimental investigation of effect of partial filling on the impulse of pulse detonation engine

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Chinese Science Bulletin 2007年第20期52卷 2859-2865页

作者： ZHANG Qun yan chuanjun FAN Wei LI Qiang College of Power and Energy Northwestern Polytechnical University Xi'an 710072 China

Using poor-detonable liquid C8H16/air mixture with low-energy system (total spark energy of 50 mJ) and a new one-step detonation initiation method developed in this study, partial-tube fill experiments have been conducted in a fixed length PDE tube with a fuel/air mixture section of different length, covering a wide range of the detonation tube fill fraction (ratio of fuel/air mixture length to tube length). Impulse was calculated by integrating the pressure differential at the closed end of the tube. Based on the re- sults obtained experimentally, it is found that the fuel-based specific impulse declines when fill fraction increases. On the other hand, the total-mixture-based specific impulse rises as fill fraction increases. A multi-cycle partial-fill model is developed to predict the impulse obtained from a partially-filled detona- tion tube, which is valuable for the optimization of PDE performance.

关键词：脉冲爆震发动机填充分数冲量性能

Experimental Investigation of Nozzle Effects on Thrust and Inlet Pressure of an Air-breathing Pulse Detonation Engine

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Chinese Journal of Aeronautics 2012年第3期25卷 381-387页

作者： CHEN Wenjuan FAN Wei ZHANG Qun PENG Changxin YUAN Cheng yan chuanjun School of Power and Energy Northwestern Polytechnical UniversityXi'an 710072China

Nozzle effects on thrust and inlet pressure of a multi-cycle air-breathing pulse detonation engine （APDE） are investigated experimentally. An APDE with 68 mm in diameter and 2 050 mm in length is operated using gasoline/air mixture. Straight nozzle, converging nozzle, converging-diverging nozzle and diverging nozzle are tested. The results show that thrust augmentation of converging-diverging nozzle, diverging nozzle or straight nozzle is better than that of converging nozzle on the whole. Thrust augmentation of straight nozzle is worse than those of converging-diverging nozzle and diverging nozzle. Thrust augmentations of diverging nozzle with larger expansion ratio and converging-diverging nozzle with larger throat area range from 20% to 40% on tested frequencies and are better than those of congeneric other nozzles respectively. Nozzle effects on inlet pressure are also researched. At each frequency it is indicated that filling pressures and average peak pressures of inlet with diverging nozzle and converging-diverging nozzle with large throat cross section area are higher than those with straight nozzle and converging nozzle Pressures near thrust wall increase in an increase order from without nozzle, with diverging nozzle, straight nozzle and converging-diverging nozzle to converging nozzle.

关键词： nozzle effect thrust inlet pressure air-breathing pulse detonation engine

Two-Way Coupling Vortex Method and Its Application

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Journal of Thermal Science 1992年第3期1卷 160-165页

作者： Chenggang Xu (1) chuanjun yan (1) Hongji Wang (1) 1. Northwestern Polytechnical University 710072 Xi’an China

Because of the success of the discrete vortex method for the simulation of large-scale vortex structure, many researchers extend this method to two-phase flow simulations, especially, to the simulation of particle dispersion in mixing layer, which is characterized by large-scale vortex structure. But the previous work is limited to one-way coupling, which neglects the effect of particles on fluid flow. In this paper, a discrete vortex method involving two-way coupling for two-phase flows is first proposed and then used in numerical simulation of two-dimensional gas-particle mixing layers. The numerical results show that the introduction of particles into the mixing layer has significant effects on the creation, development and merging process of large-scale vortex structures. It makes the mean size of large-scale vortex structure larger and the distance needed for development of large-scale vortex structure shorter.

关键词： discrete vortex method shear layer turbulence coherent structure.

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双旋流器燃烧室流场的数值计算

西北工业大学学报 1986年第1期4卷 87-96页

作者：严传俊西北工业大学副教授

本文提供了一种新型双旋流器燃烧室火焰筒内等温旋流湍流流场的数值计算结果。采用了类似于 SIMPLE(压力耦合半隐式法)算法求解时均纳维-斯托克斯方程和连续方程。运用湍流动能 k 和湍流耗散率ε的微分输运方程封闭雷诺方程。研究中预... 详细信息

本文提供了一种新型双旋流器燃烧室火焰筒内等温旋流湍流流场的数值计算结果。采用了类似于 SIMPLE(压力耦合半隐式法)算法求解时均纳维-斯托克斯方程和连续方程。运用湍流动能 k 和湍流耗散率ε的微分输运方程封闭雷诺方程。研究中预估了同向旋流和反向旋流两种情况。研究过程中特别注意反向旋流参数对于回流区的形成、尺寸、位置及旋流强度的影响。计算结果表明仅在一定条件下才能产生回流区,外旋流器对于回流区有较强的影响。回流区的直径和强度可以通过选择适当的旋流器参数加以控制。由作者编制的二元椭圆型流动计算机程序是分析旋流回流流动的非常有用的工具。本程序克服了某些数值上的困难,获得较好的收敛解。由于篇幅所限,本文将不涉及解法技巧问题。总的讲,计算结果与可用的实验数据符合得很好。

关键词：燃烧室流场旋流实验值计算值流动(力学) 回流区近尾流火焰筒火焰管旋流器湍流动能数值计算

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分区多重网格法在复杂区域中的数值研究

推进技术 2000年第1期21卷 54-56页

作者：侯凌云严传俊清华大学工程力学系北京100084 西北工业大学航空动力与热力工程系陕西西安710072

突破多重网格方法在多连通域中应用的局限性,将分区法与多重网格法结合,形成分区多重网格法,应用在复杂几何域及复杂多连通域中,结果表明,它不仅能提高精度,而且能加快收敛。

关键词：航空发动机进气道数值计算分区多重网格

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脉冲爆震火箭发动机收敛扩张喷管数值模拟

北京航空航天大学学报 2007年第7期33卷 789-792页

作者：李强范玮严传俊西北工业大学动力与能源学院西安710072

排气喷管是脉冲爆震火箭发动机(PDRE)的重要部件,对提高发动机的推进性能起着重要的作用.应用特征线法给出一维CJ爆震波在理想爆震管内传播过程的解析解.对爆震波到达爆震管口后,发动机的非定常排气过程进行了二维轴对称数值模拟.数值... 详细信息

排气喷管是脉冲爆震火箭发动机(PDRE)的重要部件,对提高发动机的推进性能起着重要的作用.应用特征线法给出一维CJ爆震波在理想爆震管内传播过程的解析解.对爆震波到达爆震管口后,发动机的非定常排气过程进行了二维轴对称数值模拟.数值模拟结果形象地反应了非定常流场的演变,详细讨论了激波和涡等的发展变化过程.所选用的收敛扩张喷管能够提高发动机性能达到18.24%.

关键词：脉冲爆震火箭发动机爆震喷管数值模拟

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爆震燃烧横向声振现象的机理研究

西北工业大学学报 2008年第5期26卷 531-534页

作者：张群严传俊范玮西北工业大学动力与能源学院．陕西西安710072

发展了一种新型低能量（50mJ）单级起爆系统，在内径为60mm的脉冲爆震发动机模型上，采用汽油／空气混合物，成功地进行了两相脉冲爆震发动机原理性实验，所测量的爆震波压力接近充分发展的爆震波。通过实验发现，爆震反应区中存在频率... 详细信息

发展了一种新型低能量（50mJ）单级起爆系统，在内径为60mm的脉冲爆震发动机模型上，采用汽油／空气混合物，成功地进行了两相脉冲爆震发动机原理性实验，所测量的爆震波压力接近充分发展的爆震波。通过实验发现，爆震反应区中存在频率范围为10～12kHz以爆震管内径为特征尺度的横向声振现象。当对爆震波时间一压力曲线进行该频段范围的带阻滤波时，爆震波峰值压力显著降低，说明该横向声振现象对于爆压等特性参数具有较为明显的影响作用。根据爆震波的横向声振机制，提出了在爆燃向爆震转变过程及爆震自持过程中，通过抑止或促进这种横向声振机制来实现对爆震波及其转变过程进行控制的方法。

关键词：爆震两相流控制横向声振

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喷雾场特性的实验研究

推进技术 1995年第2期16卷 31-36页

作者：刘伟刘燕严传俊西北工业大学航空动力与热力工程系

采用全息方法对流动环境中实际喷嘴的喷雾场进行了大量的实验研究，获得了在不同工况下喷雾场液滴尺寸分布、液滴运动速度及运动角度和空间分布等许多实验结果。这些结果给出了喷雾特性随喷雾压力、气流速度和喷嘴尺寸等因素的变化特点... 详细信息

采用全息方法对流动环境中实际喷嘴的喷雾场进行了大量的实验研究，获得了在不同工况下喷雾场液滴尺寸分布、液滴运动速度及运动角度和空间分布等许多实验结果。这些结果给出了喷雾特性随喷雾压力、气流速度和喷嘴尺寸等因素的变化特点，揭示了喷雾场中液滴速度及角度的分布规律，为喷雾运动的计算提供了有用的数据。

关键词：全息摄影喷嘴液体雾火箭发动机喷雾场