Mixing enhancement mechanism of combined H2–Water jets in supersonic crossflows in a combustor with an expanded section

To obtain the mixing enhancement mechanism of H₂–Water combined jets in supersonic crossflows in a combustor with expanded section for rotating detonation ramjet, the flow field shape and spray structure were studied by experimental and numerical methods. The Eulerian–Lagrangian method was used to investigate the diffusion mechanism and H₂–Water interaction law of combined jets with different sequences. At the same time, high-speed photography and the schlieren technique were used to capture the flow field. The effects of jet pressure drop, orifice diameter, orifice spacing, incoming Mach number, and other parameters on the penetration depth of water jets were studied. The results of experiment and simulation show that using H₂–Water combined jets, the penetration depth of the jet spray can be greatly increased and the jet mixing effect can be significantly improved, which will contribute to the engine's ignition and stable combustion. In the case of pre-water/post-H₂, the penetration depth of the hydrogen jet is greater. In the case of pre-H₂/post-water, the hydrogen jet raises the water spray mainly by protecting the integrity of the water column.     

New anti-ablation candidate for carbon/carbon composites: Preparation,composition and ablation behavior of Y2Hf2O7 coating under an oxyacetylene torch

Y₂Hf₂O₇ possesses low thermal conductivity and high melting point, which make it promising for a new anti-ablation material. For evaluating the thermal stability and the potential applications of Y₂Hf₂O₇ on anti-ablation protection of C/C composites, Y₂Hf₂O₇ ceramic powder was synthesized by solution combustion method and Y₂Hf₂O₇ coating was prepared on the surface of SiC coated C/C composites using SAPS. Results shown that the coating exhibits good ablation resistance under the heat flux of 2.4?MW/m² with the linear and mass ablation rates are 0.16?μm?s^?1 and ?0.028?mg?s^?1, respectively, after ablation for 40?s. With the prolonging of the ablation time, the increasing thermal stress causes the increase of cracks. Moreover, the chemical erosion from SiO₂ and the physical volatilization of low temperature molten products aggravate failure of the Y₂Hf₂O₇ coating.     

MPID─TOF质谱的快速时间分辨微弱信号测试系统

把瞬态记录仪Ｂｉｏｍａｔｉｏｎ８ｌ００与微型计算机ＩＢＭ─ｐＣ／ＸＴ联接建成了一个高速数据采集系统，本文介绍了系统的硬件接口设计及软件设计。在超声分子束条件下，把它应用于环氧乙烷（Ｃ＿２Ｈ＿４Ｏ）的多光子电离与离解飞行时间（ＭＰＩＤ─ＴＯＦ）质谱的实验研究中，并给出了实验结果；本系统在微观基元化学反应动力学实验研究中广泛适用于对时间分辨微弱信号的探测。     

Si相的析出状态对Al—Si合金性能的影响

控制Si相的析出状态,会对Al-Si(1wt％)合金的性能产生不同的影响。本文阐述通过不同的热处理工艺改变了Al-Si(1wt％)合金的机械、物理性能,获得了高形变强化率、高塑性变形能力、高拉伸强度的工艺,还讨论了具有上述高拉伸强度的微细丝在半导体器件应用中所具有的优越性。     

天然气超音速分离脱水技术研究进展

超音速分离技术在国外的研究与应用已经成熟,但国内的研究仍处于探索阶段。现已开展了较多的基础性研究和数值模拟研究,其中数值模拟研究主要集中在旋流流动过程、内部流动过程和凝结过程等方面,并取得一定成果,但实验性研究仍然较少,特别是在高压天然气的凝结机理及分离机理方面,未见工业性试验和现场测试试验的报道。在结构设计方面做了大量工作,主要集中在对比性分析和敏感性分析,未提出实质性的结构设计方法和思路。在液滴凝结方面的基础性研究更为少见,目前该过程主要由CNT模型和Gyamathy模型来表征液滴成核、生长过程,实际需根据各修正模型特点选择合适模型用于计算分析。今后的研究需加大入口温压、过饱和度、旋流器安装位置、超音速喷管结构参数等主要因素对凝结过程的影响性研究及高压天然气超音速分离脱液实验性研究,提高气体凝结和气液分离效率,尽早实现国内自主产权的超音速分离器的工业化应用,为空间有限的海上天然气的脱水、脱酸、脱重烃处理及外输提供有效手段。     

超声改性水玻璃砂的初步研究

在实验室条件下，较系统地研究了超声改性水玻璃砂的性能。结果表明：超声改性可有效改善水玻璃砂初强度、干强度和溃散姓，且能使水玻璃的加入量由８％降至４％左右。     

超音速扩压器喷雾冷却数值仿真研究

为了探讨研究喷雾冷却中冷却水流量、喷射速度及喷嘴轴向分布位置等因素对超音速扩压器壁面温度的影响,借助CFD计算软件FLUENT,采用标准k-ε湍流模型,对喷雾冷却下超音速扩压器内流场进行了数值仿真。通过计算,得到了扩压器内压强分布及壁面温度分布。分析了喷雾冷却中冷却水流量、喷射速度及喷嘴轴向位置对超音速扩压器壁面温度的影响。研究表明：随着冷却水流量的增大,扩压器壁面温度降低。同时,扩压器入口处静压升高,对应仿真高度降低;减小冷却水喷射速度,可以有效降低扩压器入口处壁面温度;喷嘴的轴向分布位置对扩压器壁面温度有较大影响,仿真结果证明,喷嘴沿轴向呈对数分布有利于降低扩压器壁面温度。     

网络节点超声波测距与定位技术研究

针对国内外网络弹药的发展,提出了采用超声波测距手段实现战场网络节点的自定位的方法,并且通过硬件电路实现了两节点间的超声波测距与定位试验样机系统,利用试验验证了系统的性能及定位精度等参数。     

Aeroelastic stability of heated functionally graded cylindrical shells containing fluid

The article is concerned with the analysis of panel flutter of heated circular clamped cylindrical shells made of functionally graded (FG) material, which are subject to a simultaneous action of the external supersonic gas flow and the internal flow of ideal compressible fluid. The effective properties of the material change throughout the thickness of the shell according to a power law and depend on temperature. The aerodynamic pressure is calculated based on the quasi-static aerodynamic theory. The behavior of the fluid is described in the framework of the potential theory. A mathematical formulation of the dynamic problem for elastic structure is developed based on the classical theory of shells and the principle of virtual displacements. Based on the results of numerical simulation the influence of different consistencies of the examined FG materials, thermal load, and internal flow velocity on the boundary of aeroelastic stability is analyzed.     

Normal shock boundary layer control with various vortex generator geometries

Various vortex generators which include ramp, split-ramp and a new hybrid concept “ramped-vane” are investigated under normal shock conditions with a diffuser at Mach number of 1.3. The dimensions of the computational domain were designed using Reynolds Average Navier–Stokes studies to be representative of the flow in an external-compression supersonic inlet. Using this flow geometry, various vortex generator concepts were studied with Implicit Large Eddy Simulation. In general, the ramped-vane provided increased vorticity compared to the other devices and reduced the separation length downstream of the device centerline. In addition, the size, edge gap and streamwise position respect to the shock were studied for the ramped-vane and it was found that a height of about half the boundary thickness and a large trailing edge gap yielded a fully attached flow downstream of the device. This ramped-vane also provided the largest reduction in the turbulent kinetic energy and pressure fluctuations. Additional benefits include negligible drag while the reductions in boundary layer displacement thickness and shape factor were seen compared to other devices.