Experimental research in rotating wedge-shaped cooling channel with multiple non-equant holes lateral inlet

The heat transfer in a novel smooth wedge-shaped cooling channel with lateral ejection of turbine blade trailing edge is experimentally investigated in both non-rotating and rotating cases. Beside the conventional inlet at the bottom of the channel, an extra coolant injection from 8 lateral non-equant holes is introduced to improve the overall heat transfer. The total mass flow rate ratio (lateral mass flow rate/total mass flow rate) varies from 0 to 1.0. The major inlet Reynolds number and rotation number respectively vary from 10000 to 20000 and from 0 to 1.16. Experimental results show that the lateral inlet decreases local bulk temperature and increases local heat transfer at the middle and the top of the static channel. In rotating cases, the lateral inlet notably improves the heat transfer at the high-radius half channel and compensates the negative effects induced by the rotation. Both intensity and uniformity of heat transfer inside the channel are enhanced while flow resistance decreases with proper mass flow rate ratio of coolant from two inlets. The most satisfactory total mass flow rate ratio is around 2/3. This new structural style of cooling channel has huge potential and provides new direction of heat transfer of turbine blade trailing edge.     

参量激励过程中三波耦合的一般色散关系（Ⅰ）最容易激励参量不稳定性的频率和波矢条件

讨论了在各向同性的均匀无耗电离层背景下激励参量不稳定性的三波耦合过程.首先从波的非线性耦合理论出发,分析入射电磁波和多个等离子体本征波模间的耦合情况;然后得到了无耗情况下参量激励过程满足的色散关系,在激励等离子体波的临界情况下表现为两种频率和波矢匹配条件,进而从理论上证明最容易激励参量不稳定性的条件是耦合生成电子Langmuir波和离子声波.     

加罩转—静盘系的换热—换质实验研究

应用传热-传质类比原理于加罩转-静盘系统,通过盘缘轴向进气实验模型的研究,用萘升华法得到加罩转-静盘系旋转盘表面的局部和平均换质规律,从而类比出旋转盘的局部和平均的换热规律。文章分析了系统的几何尺寸(主要是间隙比G_c、间距比G_s)、旋转雷诺数Reθ和流量系数C_w对换质的影响。并用实验方法给出准则关系式,且对这种研究方法给出了误差分析结果。      

Analysis on capabilities of density-based solvers within OpenFOAM to distinguish aerothermal variables in difusion boundary layer

Open source feld operation and manipulation（OpenFOAM）is one of the most prevalent open source computational fluid dynamics（CFD）software.It is very convenient for researchers to develop their own codes based on the class library toolbox within OpenFOAM.In recent years,several density-based solvers within OpenFOAM for supersonic/hypersonic compressible flow are coming up.Although the capabilities of these solvers to capture shock wave have already been verifed by some researchers,these solvers still need to be validated comprehensively as commercial CFD software.In boundary layer where diffusion is the dominant transportation manner,the convective discrete schemes＇capability to capture aerothermal variables,such as temperature and heat flux,is different from each other due to their own numerical dissipative characteristics and from viewpoint of this capability,these compressible solvers within OpenFOAM can be validated further.In this paper,frstly,the organizational architecture of density-based solvers within OpenFOAM is analyzed.Then,from the viewpoint of the capability to capture aerothermal variables,the numerical results of several typical geometrical felds predicted by these solvers are compared with both the outcome obtained from the commercial software Fastran and the experimental data.During the computing process,the Roe,AUSM＋（Advection Upstream Splitting Method）,and HLLC（Harten-Lax-van Leer-Contact）convective discrete schemes of which the spatial accuracy is 1st and 2nd order are utilized,respectively.The compared results show that the aerothermal variables are in agreement with results generated by Fastran and the experimental data even if the1st order spatial precision is implemented.Overall,the accuracy of these density-based solvers can meet the requirement of engineering and scientifc problems to capture aerothermal variables in diffusion boundary layer.     

再入航天飞机表面热流密度辨识

本文给出了求解表面热流密度辨识这一热传导逆问题的顺序函数法。然后以某模型航天飞机迎风中心线上的某特征点为例，将航天飞机再入时的表面热流密度辨识问题简化为一维模型问题，用顺序函数法来对该特征点上的对流加热流密度进行了仿真辨识，得到了较理想的辨识结果。该方法在航天研究领域有着良好的工程应用前景。     

卫星空间外热流轨道参数ψ_0,Ω_0和ω_0计算

文章给出了卫星热分析空间外热流计算中所需要的轨道参数太阳黄经、升交点赤经和近地点幅角的初值φ_0、Ω_0、ω_0 的计算公式。其精确度满足卫星热分析要求。     

热传递对涡轮发动机瞬态性能影响的数值分析

给出了一种预测热传递对涡轮发动机瞬态性能影响的物理模型，并将该模型与发动机动态特性模拟程序相结合，对某型双轴发动机的加、减速及Bodie加速瞬态性能进行了数值分析，结果表明，发动机瞬态过程中的热传递影响十分显著，尤其是当发动机作Bodie加速时，热传递显著提高加速初始阶段的涡轮前温度，致使压气机工作线明显向其不稳定边界靠近，降低压气机喘振裕度。     

TC17钛合金焊接及局部热处理残余应力的数值模拟

对TC17钛合金平板的氩弧焊焊接和焊后热处理过程进行了数值模拟,模型中考虑材料相变和蠕变,计算得到焊接和热处理过程中的温度场演变情况和热处理前后残余应力分布规律。结果表明,由于存在较大的热输入,焊后产生了较大的残余应力,焊缝附近的HAZ区域纵向残余拉应力达到了650MPa左右,热处理后降低至160MPa左右。采用小孔法和X射线衍射仪测量了试件的残余应力,模拟计算得到的残余应力值与小孔法测试结果符合性较好。     

整体式液体冲压发动机

整体式冲压发动机是将固体助推火箭与巡航用液体燃料冲压发动机组合成为一个整体的新型动力装置,它是超声速、小体积、中远程导弹动力系统的最佳选择.整体式冲压发动机的出现将冲压发动机的应用推向一个新阶段,引起世界各国的广泛重视.近几年我国在整体式冲压发动机很多关键技术的研究上有所突破.液体冲压发动机和助推火箭共用一个燃烧室,使燃烧室中无法安装专门的机械式火焰稳定器和空气冷却衬筒,这为解决燃烧室的点火起动问题、振动问题及热防护问题带来了很大的困难.试验表明:冲压发动机的点火起动问题有多种解决方案,其中火焰稳定性准则的满足是点火起动的重要条件;燃烧室的进口流场,燃油浓度分布等对振动有很大的影响;计算表明,冲压发动机在飞行状态时,流经燃烧室壳体外表面的高速气流的冷却作用可大大降低燃烧室壳体的温度,在相同的冷却效果下,可降低对热防护层的要求.     

低速大尺寸传热风洞的研制

为进行航空发动机内特别是叶轮机械内的边界层、传热和气膜冷却研究，设计、建造了大尺寸低速回流式风洞。描述了风洞结构和设计中考虑的主要问题。风洞性能测试结果表明，试验段中的气流达到很高的均匀度，不用紊流发生器时可达到很低的紊流度，试验板上的边界层参数和换热系数都和公认的关系式符合良好。