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稀燃缸内直喷氢内燃机NH_(3)-SCR后处理系统工作特性研究

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车用发动机 2024年第4期 1-8页

作者：邹凯翔孙柏刚罗庆贺北京理工大学机械与车辆学院北京100081

氢内燃机具有零碳排放的特点,是实现低成本碳中和的重要手段。但是缸内燃烧的高温环境会生成大量的氮氧化物(NO_(x))排放,在日益严苛的排放法规要求下,利用选择性催化还原(SCR)NO_(x)的后处理技术是拓展氢内燃机大规模应用、不断提升其... 详细信息

氢内燃机具有零碳排放的特点,是实现低成本碳中和的重要手段。但是缸内燃烧的高温环境会生成大量的氮氧化物(NO_(x))排放,在日益严苛的排放法规要求下,利用选择性催化还原(SCR)NO_(x)的后处理技术是拓展氢内燃机大规模应用、不断提升其动力性和经济性的必要手段。首先通过试验验证了Cu基分子筛的NH_(3)-SCR后处理系统是一种高效的针对直喷氢内燃机的NO_(x)净化方案,接着使用简化反应机理对NH_(3)-SCR反应过程进行了建模仿真,并研究了反应温度、空速和氨氮比对氢内燃机边界下NH_(3)-SCR还原NO_(x)的影响。研究结果表明:在稀燃缸内直喷氢内燃机边界下,NH_(3)-SCR低温活性仍保持良好,后处理系统起燃温度(T_(50))为110℃,活性窗口(T_(90))范围为150~425℃;在空速大于25000 h^(-1)时,NO_(x)转化效率都大于95%;当控制氨氮比为0.5,并保持反应温度在350~400℃时可保证最高的NO_(x)转化效率,实现直喷氢内燃机的近零NO_(x)排放。

关键词：氢内燃机氮氧化物稀薄燃烧选择性催化还原缸内直喷

Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method

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Chinese Journal of Aeronautics 2012年第1期25卷 42-50页

作者： YANG Hui LI Feng sun baigang School of Jet Propulsion Beihang University Beijing 100191 China

Trajectory analysis of fuel injection into supersonic cross flow is studied in this paper. A directly-connected wind tunnel is constructed to provide stable supersonic freestream. Based on the test rig, the schlieren system is established to reveal the fuel injection process visually. Subsequently, the method of quantitative schlieren is adopted to obtain data of both fuel/air interface and bow shock with the aid of Photoshop and Origin. Finally, the mechanism based on two influential factors of fuel injection angle and fuel injection driven pressure, is researched by vector analysis. A dimensionless model is deduced and analyzed. The curve fitting result is achieved. The relationship between the data and the two influential factors is established. The results provide not only the quantitative characteristics of the fuel injection in supersonic cross flow but also the valuable reference for the future computational simulation.

关键词： fuel injection schlieren supersonic flow injection driven pressure injection angle characteristic velocity

Experiment of gas plasma plume deflection by magnetic control

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航空动力学报 2020年第3期35卷 581-588页

作者： ZHAO Kai HU Jianbo LU Yongji LI Feng MING Ming sun baigang School of Energy and Power Engineering Beijing University of Aeronautics and AstronauticsBeijing 100191China School of Aviation Operations and Services Aviation University of Air ForceChangchun Jilin 130022China Department of Contract Tactics Air Force Command CollegeBeijing 100097China

To investigate the deflection effect of gas plasma plume controlled by magnetic field,a novel experimental scheme was *** Cs2CO3 catalytic ionization seeds were injected into the combustion chamber to obtain gas plasma on a high temperature magneto hydrodynamic(MHD)experiment *** plasma jet was deflected under the action of an external magnetic field,resulting in a thrust-vector *** image velocimetry(PIV)collected two-dimensional images of jet flow *** image processing and velocity vector analysis,the jet deflection angle can be obtained *** 1800-2500 K,the jet deflection was verified experimentally under the condition of 0.45 T magnetic field *** results indicate that the jet deflection angle increases gradually with the increase of gas temperature,and above 2200 K,the jet deflection angle increase *** the process of gas plasma jet,it is feasible to realize the jet deflection controlled by MHD by adding an external magnetic field.

关键词： gas plasma plume deflection magnetic fluid thrust vector particle image velocimetry

Numerical and experimental investigation of plasma plume deflection with MHD flow control

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Plasma Science and Technology 2018年第6期20卷 152-160页

作者： Kai ZHAO Feng LI baigang sun Hongyu YANG Tao ZHOU Ruizhi sun School of Energy and Power Engineering Beihang University Beijing 100191 People's Republic of China School of Aviation Operations and Services Aviation University of Air Force Changchun 130022 People's Republic of China Air Force Command College Beijing 100191 People's Republic of China

This paper presents a composite magneto hydrodynamics（MHD） method to control the lowtemperature micro-ionized plasma flow generated by injecting alkali salt into the combustion gas to realize the thrust vector of an *** principle of plasma flow with MHD control is *** feasibility of plasma jet deflection is investigated using numerical simulation with MHD control by loading the User-Defined Function model.A test rig with plasma flow controlled by MHD is *** alkali salt compound with a low ionization energy is injected into combustion gas to obtain the low-temperature plasma ***,plasma plume deflection is obtained in different working *** results demonstrate that plasma plume deflection with MHD control can be realized via numerical simulation.A low-temperature plasma flow can be obtained by injecting an alkali metal salt compound with low ionization energy into a combustion gas at 1800–2500 *** vector angle of plasma plume deflection increases with the increase of gas temperature and the magnetic field *** is feasible to realize the aim of the thrust vector of aeroengine by using MHD to control plasma flow deflection.

关键词： MHD plasma ionization degree thrust vector aero engine

Development of performance and combustion system of Atkinson cycle internal combustion engine

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Science China(Technological Sciences) 2014年第3期57卷 471-479页

作者： LIU FuShui sun baigang ZHU HuaRong HU TieGang DU Wei LI XiangRong ZHANG Zheng School of Mechanical Engineering Beijing Institute of Technology Chang'an Auto Co. Ltd

The application of hybrid vehicle is a practical technical solution to the energy shortage and the environmental *** internal combustion engine(ICE)plays a key role in the development of the hybrid *** on the requirements of the hybrid vehicle and the characteristic of Atkinson cycle,a set of designing methods for the Atkinson cycle gasoline engine is presented through the analysis of the optimized matching for the compression ratio,valve timing and the combustion *** designing method has been verified by the bench test and the results show that the fuel consumption can be improved by12%–15%with the reduction of the low speed torque by 10%,and the low fuel consumption region in the fuel map extends significantly with the rated power almost keeping *** may be of great reference for the development of hybrid vehicle technology in China.

关键词： hybrid vehicle Atkinson cycle compression ratio valve timing combustion chamber

Experimental investigation on plasma jet deflection with magnetic fluid control based on PIV measurement

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Plasma Science and Technology 2019年第2期21卷 83-89页

作者： Kai ZHAO baigang sun Yongji LU Feng LI Yongbo LIU Xiangbin LIU Kefu WANG School of Energy and Power Engineering Beihang University School of Aviation Operations and Services Aviation University of Air Force Air Force Command College Air Force Harbin Flight Academy

This paper is devoted to experimentally investigating the influence of magnetic field intensity and gas temperature on the plasma jet deflection controlled by magneto hydrodynamics. The catalytic ionization seed CS_2CO_3 is injected into combustion gas by artificial forced ionization to obtain plasma fluid on a high-temperature magnetic fluid experimental platform. The plasma jet was deflected under the effect of an external magnetic field, forming a thrust-vector *** oxide was selected as a tracer particle, and a two-dimensional image of the jet flow field was collected using the particle image velocimetry(PIV) measurement method. Through image processing and velocity vector analysis of the flow field, the value of the jet deflection angle was obtained quantitatively to evaluate the thrust-vector effect. The variation of the jet deflection angle with the magnetic field intensity and gas temperature was studied under different experimental conditions. Experimental results show that the jet deflection angle increased gradually with a rise in gas temperature and then increased substantially when the gas temperature exceeded 2300 K. The jet deflection angle also increased with an increase in magnetic induction intensity. Experiments demonstrate it is feasible to use PIV test technology to study the thrust vector under magnetic control conditions.

关键词： PIV plasma jet deflection MHD image processing

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氢氧内燃机增氧定容燃烧特性研究

宇航总体技术 2024年第3期8卷 68-74页

作者：张霞孙柏刚吴胜宝王书廷张万旋中国运载火箭技术研究院研究发展中心北京100076 北京理工大学机械与车辆学院北京100081

航天器携带推进剂有限,氢氧内燃机适宜采用纯氢纯氧+富氢燃烧方式,但目前内燃机纯氢纯氧燃烧缺乏地面试验验证。为此开展氢氧内燃机增氧定容燃烧试验,采用内燃机定容燃烧逐步增氧的技术路线,获得增氧乃至纯氧条件下氢氧内燃机的层流燃... 详细信息

航天器携带推进剂有限,氢氧内燃机适宜采用纯氢纯氧+富氢燃烧方式,但目前内燃机纯氢纯氧燃烧缺乏地面试验验证。为此开展氢氧内燃机增氧定容燃烧试验,采用内燃机定容燃烧逐步增氧的技术路线,获得增氧乃至纯氧条件下氢氧内燃机的层流燃烧特性,实现氢氧内燃机高性能高可靠工作。试验结果表明:随着氧气浓度的增大,层流燃烧速度随当量比成倍增加,变化的幅度会逐渐减小;高氧气浓度条件下,层流燃烧速度维持在很高的水平,且随当量比的变化很小。

关键词：氢氧内燃机定容层流燃烧特性增氧

Power and Emission Characteristics of Hydrogen Internal Combustion Engine

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Power and Emission Characteristics of Hydrogen Internal Comb...

利用废气再循环与米勒循环提高氢内燃机压缩比的研究

2015中国汽车工程学会年会

作者： Tang Hongyang sun baigang Liu Fushui School of Mechanical Engineering Beijing Institute of Technology

To study the power and emission characteristics of hydrogen internal combustion engine,an experimental study was carried out using a 2.0 L port fuel-injected（PFI）hydrogen internal combustion *** results show the power of hydrogen internal combustion fell 40%comparing to the gasoline;NOx emission concentration is always higher than 8000ppm when the equivalent fuel-air ratio is larger than 0.8 and lower than 500ppm when the equivalent fuel-air ratio is smaller than *** increases with the increase of the ignition advance *** the equivalent fuel-air ratio is larger than *** test results and the conclusions exhibit a guiding role on hydrogen internal combustion engine optimizations.

关键词： HICE emission NOx equivalence ratio ignition advance angle

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内燃机工程 2021年第5期42卷 52-59页

作者：郝嘉田孙柏刚北京理工大学机械与车辆学院北京100081

建立了氢内燃机一维模型,分别仿真分析了废气再循环(exhaust gas recirculation,EGR)技术和米勒循环技术对抑制爆震及氮氧化物(NO_(x))排放的效果,最后结合两种技术探索了可达到的最大压缩比和最好的NO_(x)排放性能。结果显示EGR技术对... 详细信息

建立了氢内燃机一维模型,分别仿真分析了废气再循环(exhaust gas recirculation,EGR)技术和米勒循环技术对抑制爆震及氮氧化物(NO_(x))排放的效果,最后结合两种技术探索了可达到的最大压缩比和最好的NO_(x)排放性能。结果显示EGR技术对抑制NO_(x)排放更有效,米勒循环对抑制爆震更有效,最终在本研究的工况下,可以将内燃机的压缩比从10.0提升到18.4,指示热效率提升了8.0%,达到了44.87%,同时NO_(x)排放减少了26.2%,达到了1.937 g/(kW·h)。

关键词：氢内燃机废气再循环技术米勒循环 NO_(x)排放爆震仿真模拟