Numerical Simulation and Experimental Research on Wake Field of Ships Under off-Design Conditions

Different operating conditions （e.g. design and off-design） may lead to a significant difference in the hydrodynamics performance of a ship, especially in the total resistance and wake field of ships. This work investigated the hydrodynamic performance of the well-known KRISO 3600 TEU Container Ship （KCS） under three different operating conditions by means of Particle Image Velocimetry （P/V） and Computational Fluid Dynamics （CFD）. The comparison results show that the use of PIV to measure a ship＇s nominal wake field is an important method which has the advantages of being contactless and highly accurate. Acceptable agreements between the results obtained by the two different methods are achieved. Results indicate that the total resistances of the KCS model under two off-design conditions are 23.88% and 13.92% larger than that under the designed condition, respectively.

Off-design Characteristics of IGCC System Based on Two-stage Coal-slurry Gasification Technology

整体煤气化联合循环（integrated gasification combinedcycle,IGCC）机组在一定情况下处于非设计工况运行。为了研究IGCC系统变工况特性,采用ThermoFlex软件建立基于两段式水煤浆气化技术的200 MW级整体煤气化联合循环系统模型,主要考查燃气轮机负荷、整体空分系数Xas、大气温度、大气压力对系统性能的影响。研究结果表明,降低燃气轮机负荷或者提高大气温度系统效率均呈先升高而后降低的趋势。整体空分系数Xas增加,机组发电效率降低。大气压力对系统效率影响较小。上述条件下采用两段水煤浆气化技术,系统性能可以得到有效改善。研究结果可为采用两段式水煤浆气化技术的IGCC系统的设计、运行提供参考。

Performance Analysis of Constant-Pressure Pumped Hydro Combined with Compressed Air Energy Storage System Considering Off-Design Model of Compressor

With the wide application of renewable energy, energy storage technology has become a research hotspot. In order to overcome the shortcomings of energy loss caused by compression heating in compressed air energy storage technology, a novel constant-pressure pumped hydro combined with compressed air energy storage system was proposed. To deepen the understanding of the system and make the analysis closer to reality, this paper adopted an off-design model of the compressor to calculate and analyze the effect of key parameters on system thermodynamics performance. In addition, the results of this paper were compared with previous research results, and it was found that the current efficiency considering the off-design model of compressor was generally 2% - 5% higher than the previous efficiency. With increased preset pressure or with decreased terminal pressure, both the previous efficiency and current efficiency of the system increased. The exergy destruction coefficient of the throttle valve reached 4%. System efficiency was more sensitive to changes in water pump efficiency and hydroturbine efficiency.

Off-Design Modelling of a Turbo Jet Engine with Operative Afterburner

Gas turbines are considered as one of the leading internal combustion engines in modern air transportation due to its favourable power to weight ratio and its continuous combustion process. Recent research focus has been concerned with performance improvements aimed at reduced fuel consumption and hence reduced impact on the environment. This study is aimed at using theoretical and computational methods to model the operation and performance a turbojet gas turbine engine. The commercial software GasTurb13 was used for the theoretical simulation while Microsoft Excel was used for the analytical study. GasTurb13 solved the model using pseudo-perfect gas models i.e. component maps since the specific gas ratio could not be inputted into the solver. The effect of changes in the Mach number and altitude on the engine performance was studied. Also the effect of changes in the compressor pressure ratio, the turbine inlet temperature and the afterburner exit temperature were also studied. Results obtained showed the optimum pressure ratio at maximum thrust constraint to be 16.78 for the turbojet engine operating at Mach number (Ma) = 0.8 and altitude = 10,000 m, Turbine inlet temperature (TIT) = 1200 K and Afterburner exit temperature = 1800 K.

Optical Design for the Off-axis Reflective Optics with Wide Field

Reflective optics with wide field of view has been applied more and more widely in EUVL or space optics, and also plays an important role in promoting scientific and technological research. Among the reflective optics, the off-axis reflective optics is the most hopeful solution to the ever-highest demands of these applications. This paper gives the requirements of both the above mentioned applications and the similarities and differences between these two kinds of optical systems. Finally, a design example of off-axis reflective optics with wide field of view is presented and described.

The Tank Design Bazaar Has Opened!--DHUB 2018SS Design Fair Has Kicked Off in Beijing

On October 29th, the DHUB 2018SS Design Fair kicked off in the 79 Tank at 751D PARK. This year＇s fashion fair gathered original designs from domestic and overseas designers, while also inviting well-known fashion icons, to provide you with a unique fashion experience!

有机工质向心透平数值模拟及变工况内流特性研究

基于国内外研究现状,分别对设计工况下和非设计工况下有机朗肯循环向心透平的工作状态进行了三维数值模拟。以透平功率、效率、反动度、静叶损失系数、动叶损失系数作为评价指标,分析了透平在非设计工况下的性能;同时开展了透平在非设计工况下流动状况的描述。结果表明:设计工况下透平输出功率为122.3 kW,透平等熵效率为83.54%;在非设计工况下,透平功率和效率在转速比为0.8~1.0时的增幅较大,透平反动度和静叶损失系数均与转速呈线性关系,而动叶损失系数在转速比为0.8~1.2时存在最小值;当转速低于设计转速时,在动叶前缘吸力面存在涡流,当转速高于设计转速时,涡流存在于动叶压力面的前缘,造成此现象的主要原因是动叶转速与静叶出口流速的周向分量之间存在差值。

高速S-CO_(2)向心透平几何参数优化及变工况特性分析

透平是热力循环中实现热功转换的核心设备,优化透平几何参数以改善气动性能,是提升系统热效率的关键。该文以面向某船舶主机烟气余热利用的超临界二氧化碳布雷顿循环透平设计参数为基础,给出向心透平主要几何参数,采用耦合CO_(2)真实物性参数的CFX仿真方法,分析几何参数动、静叶包角以及叶轮出口几何角对透平性能的影响规律并进行参数优化,进一步研究非设计工况下的透平运行特性。结果表明:增大静叶包角会使动叶前缘出现扰动涡流并减少余速损失,增大叶轮出口几何角,动叶包角对透平效率的影响规律不变,但效率峰值点会沿动叶包角减小的方向移动;动、静叶包角和叶轮出口几何角分别为49°、21.5°、25°时透平设计点总-静等熵效率高达87.99%,相比优化前,提高0.54个百分点;透平偏离设计点±20%工况下等熵效率大于80%。结果可为超临界二氧化碳高速向心透平设计提供一定参考。

Risk Assessment of Aircraft’s Lateral Veer-off the Runway Surface during Landing

This article presents a methodology to determine the risk of aircrafts lateral runway excursion during landing via mathematical risk modeling. In addition, the methodology is demonstrated by means of detailed calculation of the lateral runway excursion risk value during the landing of the aircraft Airbus A310-200, in view of the maximum landing weight and the appropriate range of landing velocities according to the International Civil Aviation Organization specification. Obviously, the calculation demonstrates that the developed math solutions and equations presented herein are powerful tools to evaluate the risk of lateral runway excursion of the majority of aircrafts and for any airport. The method is also applicable to assess the residual level of risk at any specific airport and its deviation compared to the recommended safety level. Consequently, the presented mathematical solutions to determine the risk rate of lateral runway excursion during landing offers airports’ operational and safety management departments a viable tool so that appropriate measurements could be adopted. Finally, it is a methodology not only to assess the risk but also to determine the appropriate runway width.

R32热泵系统稳定性与变工况特性实验研究

实验研究了变热源进口温度工况和变热水进口温度工况下膨胀阀开度对R32热泵系统稳定性和系统性能的影响规律。结果表明:不同工况下系统存在不同的过热度振荡区间,且热源进口温度对起始振荡过热度的影响较显著,而热水进口温度对其影响则不明显;变热源进口温度(15~25℃)工况下,制热量随着过热度的变化呈现不同的变化规律,而其COP则呈现相同的变化规律,且系统均在过热度振荡区间内获得最大COP;变热水进口温度(30~40℃)工况下,制热量和COP均随着过热度的变化呈现相同的变化趋势,且两者均在过热度振荡区间内取得最大值;热源进口温度的升高和热水进口温度的降低均可使系统获得的最大制热量和最大COP增大,且两者在热源进口温度为25℃时分别为9.287 kW和4.646,而在热水进口温度为30℃时则分别为9.148 kW和5.665。

风电-火电-压缩空气储能综合能源系统运行特性研究

为提升电网消纳风电的能力,改善火电机组运行灵活性,本文基于压缩空气储能系统容量大、多能流耦合的特点提出了一种包含两台600 MW燃煤机组的风电-火电-压缩空气储能综合能源系统。首先通过构建系统热力学变工况模型,分析了关键参数对压缩空气储能系统性能的影响,然后以降低弃风率为目标,探究了综合能源系统在典型特征日的能流匹配和运行特性。结果表明,电能分配比由57.3%增加至76.0%时,储能系统输出热电比由0.84下降至0.30,对储能系统输出影响最为显著;典型特征日的仿真场景下,综合能源系统负荷调节能力强,能流匹配良好,弃风率仅为2.28%。通过上述分析,验证了所提出的系统具备可观的风电消纳潜力和运行灵活性。

基于PLC可控电源保护装置的优化设计

针对以电气设备为主的技能实训操作平台由于有时忘记关闭电源而引发的安全问题,设计一种集操作与保护为一体的电源保护装置。文章介绍该保护装置的结构设计,并从硬件及软件两个方面介绍了控制系统的设计。通过调试运行结果显示,该装置不仅能安全控制设备电源的通断,而且对长时间处于带电状态而无人操作的实训设备实现断电保护功能,在一定程度上消除了实训室的用电安全隐患,降低实训室的管理难度。

基于EBSILON仿真的Kalina循环发电系统研究及分析

为实现对内燃机排气余热利用系统经济性改造的综合评价,基于EBSILON仿真模拟软件,提出利用Kalina循环发电系统回收烟气余热,计算获得了余热回收系统的节能潜力,对比并分析了两种Kalina循环的变工况性能。结果表明,设计工况下,透平和泵的效率分别为85%和80%,当Kalina循环偏离设计工况时,恶化了透平和泵的性能,随着发电机功率降低,透平和泵的效率均降低;随着内燃机排气流量从60%增加至100%,KCS-34热效率从14.08%增加至14.17%,后降低至13.49%,BKCS热效率从12.29%增加至12.58%,后降低至10.49%。在相同内燃机排气流量下,KCS-34的热力性能优于BKCS,前者更适用于内燃机排气余热的回收。

变入口压力下大容量压缩空气储能电站空气透平动态过程及调节特性研究

压缩空气储能系统的空气透平入口压力变化较大,为了掌握该条件下透平的特性及规律,使用多学科仿真平台MSP和模块化建模工具PowerBuilder搭建了全工艺流程的300MW级压缩空气储能系统,分析空气透平在入口压力大幅变化情况下的运行特性和调节过程,揭示储气室压力大幅变化下透平膨胀比、出口温度和效率等关键参数的变化规律,确定了透平的功率调节过程及响应特性,并分析了透平入口温度对机组功率的影响和限制,为大容量压缩空气储能系统空气透平的运行和调节提供了数据支撑和科学依据。

垂直起降无人机气动布局设计研究进展

垂直起降无人机是当前航空领域的研究热点。文章介绍了倾转旋翼、倾转涵道和双系统式三类垂直起降无人机的工作原理和典型机型,分析和讨论了其气动布局特征及其设计研究进展,提出了垂直起降无人机气动布局设计和优化、飞行控制、侧风效应和结构轻量化设计方面的研究建议。

考虑设备变工况特性的园区综合能源系统双层优化

园区综合能源系统通过整合多种能源设备为用户提供可靠的能量供应,但设备的变工况特性给容量配置的合理性及调度方案的准确性带来了严峻挑战。为此,提出了一种考虑变工况特性的综合能源系统容量与调度双层优化方法。首先,采用改进的核密度估计法构建更准确的能源供需场景。其次,基于极致梯度提升算法,建立设备效率修正模型以表征设备的变工况特性,并考虑温度对设备寿命的影响,将老化成本纳入目标函数进行优化。然后,提出最优负载率跟踪策略,通过解耦调度过程中输出、效率和负载率三者的关系,主动调节能量转换设备的输出比例,实现系统的柔性供能。最后,通过仿真结果表明,所提方法考虑了设备的变工况特性,不仅提高了设备模型的准确度,还增强了配置方案的科学性和调度方案的经济性。

汽轮机当量配汽级组变工况计算方法

将汽轮机主汽阀至一段抽汽口视为当量配汽级组,建立不同总阀位指令下的当量配汽级组特性曲线,进而实现包含总阀位指令信息的汽轮机配汽端特性的变工况计算。经验证,当量配汽级组简化仿真计算与汽轮机配汽端全面仿真计算结果趋于一致。该方法计算简便,符合试验机组的实际特性,满足工程应用的要求。

新型高效空气冷却燃气轮机系统热力性能分析

为改善空气冷却重型燃气轮机热力性能,提出了一种能够高效利用抽气能量的新型空气冷却燃气轮机系统并研究了其热力性能的变化。以传统典型F级燃气轮机不同环境温度下的性能数据作为对比基础,通过数值仿真分析了新型高效空气冷却燃气轮机中冷却系统设计参数变更条件下的系统性能指标变化,计算对比了3种运行模式下的热力性能。结果表明:新型高效空气冷却燃气轮机能够有效降低压气机抽气温度,进而改善燃气轮机热力性能。在夏季工况下,进口温度分别被冷却到30、20、15℃时,燃气轮机功率分别升高了25.92、40.49、48.22 MW,燃气轮机效率分别提升了0.78、1.19、1.40个百分点。

基于Seidel像差理论的离轴四反初始结构自动化设计方法研究

离轴反射系统设计的关键环节是确定适用初始结构并进行优化,一般从同轴结构或者专利库中寻找相似的结构开始优化,这往往需要耗费大量的时间。以Seidel像差理论为依据,研究了一种获取离轴四反系统初始结构的设计方法。在设计之初引入视场偏置,通过追迹近轴光线给出五种单色像差的初级Seidel像差表示。以Seidel像差绝对值最小化作为目标函数,同时加入对光学和系统结构上的限制条件构建含有约束条件的单目标非线性优化模型,并通过粒子群优化算法进行求解。在此基础上,通过MATLAB调用CODE V API接口,判断此视场偏置情况下是否满足无遮拦的条件,并从中挑选出满足条件的初始结构。设计了一款焦距为1200 mm,视场1.2°×20°,F数为6的离轴四反光学系统,系统结构布局紧凑,成像质量良好,各项指标均满足设计要求。

基于特性数据的燃气涡轮发动机修正方法

针对燃气涡轮发动机部件特性不匹配造成的模型计算参数与实际试车参数之间的误差问题,提出一种基于特性数据的燃气涡轮发动机部件特性修正方法。通过变缩放参考中心依次对设计点、慢车点进行整体修正,实现特性图在整个工况范围内的大致覆盖。通过局部修正非设计点所在的由相邻等转速线和β线所确定矩形域的特性数据,并采用插值法和拟合椭圆曲线法对等转速线的其他数据点进行补充修正,得到与试车数据匹配的特性图。以涡扇发动机为研究对象进行仿真验证,结果表明:所提出的特性修正方法能准确、快速地对发动机部件特性进行修正,与试车数据相比,修正后的模型各稳态点误差精度均在1.5%以内,满足工程精度需求,可用于发动机控制系统研究。