燃酒糟锅炉运行性能热态试验研究

针对酒糟的燃料特点,在研究其燃烧机理的基础上,开发了一种燃酒糟锅炉,并对燃酒糟锅炉炉内空气动力场布置对锅炉燃烧及效率的影响、燃酒糟锅炉的实际运行性能进行了热态试验研究,为燃酒糟锅炉以及其它燃生物质锅炉的优化设计和运行提供了可靠依据。     

Effects of a kind of non-smooth blade on the performance of an axial fan

This paper presents an experimental investigation of effects of a kind of streamwise-grooved blade on theperformance of an axial-flow fan.The flow field at 25% chord downstream from the trailing edge at hub wasmeasured using a 5-hole pressure probe at different mass-flow conditions.The fan performance of the grooveblades was compared with that of the smooth blades.The measurement results indicate that:(1)the non-smoothblades increase mass flow of the fan at the same throttle conditions except a near stall condition;(2)thenon-smooth blades reduce the relative total pressure loss in the rotor passage and increase the fan's total pressurerise at the test mass-flow conditions except the near stall condition;(3)Negative benefits are obtained at a nearstall condition when the smooth blades are replaced by the non-smooth ones.The fan mass flow decreases 0.9%while the total-pressure rise decreases 2.4% at the near stall condition.     

EFP的气动及终点弹道优化设计新方案

本文针对常规EFP的飞行阻力大、稳定性差的缺点,以提高其侵深为目标,在综合研究轴对称裙式EFP弹形参数对气动性能及终点弹道影响规律的基础上,提出一种新的具有工程实现可能性的EFP气动优化方案:对于前体,根据杆式头部破甲弹的气动原理,通过增加一尖锥,改善其气动特性;对后体,仍采用简便的裙式,优化裙体参数.经初步分析,综合优化的EFP侵彻性能有显著提高,为其优化设计提供了一条新思路.其工程实现有待进一步研究.     

格林函数法研究机弹干扰对航弹初始弹道的影响

应用格林函数法对机翼下气流对航弹初始弹道的影响进行了研究。揭示了机弹干扰的机理，影响的主要原因是干扰气流改变了航弹初始运动阶段的压力分布，从而引起气动系数的变化，形成其特有的弹道特性。     

上海国际赛车场副看台膜结构顶篷设计

上海国际赛车场副看台顶篷由26个单体顶篷组成,每个单体呈不对称漏斗形,展开面积为720m2.采用膜结构体系,结构体系新颖,设计和施工难度大.因其外形为不规则的空间曲面,且各单体间相互气动干扰效应严重,导致其空气动力作用复杂,现有荷载规范无法确定其体型系数,因此借助风洞试验方法.在试验基础上对找形完毕的膜结构进行荷载分析,以保证结构安全,合理经济地进行材料选取、体系选取.     

蒸汽放空阀噪声传播分析及结构优化

针对某化工厂DN100-PN63蒸汽放空阀在开度0~60%的振动噪声问题,基于分离涡算法和MÖhring声类比理论,采用Fluent和Actran软件对开度为40%的阀门进行真实工况的流场和声场数值模拟分析,研究阀门内部流动情况及阀门内、外噪声分布情况,提出4种改进结构,并分别对其流场和声场进行深入的对比研究。结果表明：原结构阀门内部存在多处涡旋;阀内件和孔板的高马赫数(Ma＞0.2)区域约占90%,且存在超音速流动区域,极可能产生较大的冲击波并产生激波啸叫;离阀门及管道1 m处的噪声达116 dB(A),具有宽频特性,并有明显的四极子声源特点;与原结构相比,改进后的4种阀内件对涡旋的消失起到了促进作用,具有明显的降噪效果。     

汽车外场气动噪声仿真与计算

利用FLUENT软件,对汽车的外场远点噪声进行仿真计算：通过稳态计算,得出汽车车身的表面声功率和声源分布情况,对车身的噪声源进行定性分析;通过瞬态计算,得到车身外场某点噪声的声压频谱图。仿真结果表明：汽车外场气动噪声源主要来自车身前脸、后视镜、前风窗玻璃、前轮;远场点的声压级由前向后有增大的趋势,并且靠近尾部区域声压级较大,最大达90．4dB,直径10m弧线上接收点的声压级值比直径12m的要高,其差值最大达15．1dB。     

有头部攻角的弹丸气动性能的数值计算

运用流体力学数值计算软件对有头部攻角的弹丸气动性能进行了数值计算,分析了有头部攻角弹丸周围流场和作用在弹丸表面的空气动力.结果表明,弹头部相对弹体部有一定转角,能产生较大的控制力和力矩,为发展自适应弹箭提供了数值计算方法.     

Microstructure of rapidly-quenched ZrO2-SiO2 glass-ceramics fabricated by container-less aerodynamic levitation technology

In this work, an aerodynamic levitation technology (ALT) was utilized to prepare ZrO₂-SiO₂ glass-ceramics with two different ZrO₂ contents, that is, 35 mol% and 50 mol%. The glass-ceramics were partially melted at ∼2000°C or fully melted at ∼3000°C by ALT, followed by rapid quenching to obtain spherical glass-ceramic beads. The phase compositions and microstructures of the glass-ceramics were characterized. Crystallization of ZrO₂ occurred during the solidification process and ZrO₂ content, processing temperature, and the addition of yttrium (3 mol%) affected the crystalline phase of ZrO₂. No ZrSiO₄ or crystalline SiO₂ were formed during the solidification process and the glass-ceramics were away from thermodynamic equilibrium due to rapid quenching. The glass-ceramics showed a microstructure of irregular-shaped ZrO₂ micro-aggregates embedded in an amorphous SiO₂ matrix, with lamellar twins and lattice defects formed within ZrO₂ crystals. For samples prepared at ∼3000°C, a liquid-liquid phase separation occurred in the melt, which eventually resulted in the formation of large and irregular-shaped ZrO₂ aggregates. In comparison, for samples prepared at ∼2000°C, pre-existed ZrO₂ crystals formed during heating acted as nucleation sites during the cooling process, followed by grain growth to form large ZrO₂ aggregates. Solidification and microstructure formation mechanisms were proposed to elucidate the solidification process during rapid cooling and the microstructure of the glass-ceramics obtained.     

航天飞机三维最优再入轨道及气动加热过程

本文应用现代控制理论研究了航天飞行器三维最优再入轨道和与轨道参数密切相关的气动加热过程。文中选择飞行器迎角和倾斜角作为控制变量,以飞行器气动加热率和飞行过载沿轨道积分最小作为优化性能指标,按极大原理导出了最优再入轨道有约束控制的非线性两点边值问题。采用了数值优化法——共振梯度法求解了有升力飞行器的最优再入轨道及其热过程。文中以允许误差法讨论了权系数和罚函数的选取方法;对不同速度范围研究了不同的加热模型,按热平衡方程与优化轨道同步迭代的方法求得了算例数值结果。算例的数值结果与文献[9]的数值是一致的。