吹风比与湍流度对涡轮叶片压力面气膜冷却影响的实验研究

为研究不同吹风比下主流湍流度对涡轮导叶气膜冷却的影响,采用可进行全表面换热特性参数测量的瞬态液晶传热测量技术,获得了叶片压力面侧圆柱形孔排气膜绝热有效度和表面传热系数比的全表面分布数据。结果表明:吹风比的变化对气膜绝热有效度影响显著,随着吹风比的增大,相同主流湍流度下的气膜绝热有效度明显下降,然而吹风比的增大仅对气膜孔附近区域的对流传热系数比有一定的提升作用;随着主流的湍流度增加,强化了主流和二次流的掺混,导致二次流温度快速接近主流温度,气膜射流在叶片压力面的覆盖范围变窄,绝热气膜有效度降低;由于高湍流度下的光滑叶片对流传热系数显著提高,造成对流传热系数比随着主流湍流度的增大而减小。     

某燃气轮机涡轮叶片复合冷却结构优化设计

为了提高涡轮叶片设计效率,搭建了基于一维管网理论的iSIGHT优化设计平台,获得了叶片的优化结构,并对其进行三维仿真计算分析。研究表明：优化前后叶片的气动性能变化不大,总压损失仅在端壁处略有差别;优化后涡轮叶片的壁面温度分布更加均匀,壁面的最高温度降低,温度梯度减小,最大相对温差降低10%左右;在降低叶片热应力的同时相对冷却效率提高1.0%。     

基于流固耦合的变几何涡轮叶片传热特性研究

本文利用流固耦合数值模拟分析的方法,对某型船用燃气轮机涡轮可变几何导叶进行了气动与传热分析。在同一工况下,当导叶调整旋转角度分别为-3°、0°、+8°时,涡轮导叶叶片表面以及叶顶端区传热特性会发生改变。经计算发现:对整体导向叶片而言,叶片旋转轴所在的圆盘部位平均温度较低,圆盘所在区域的热应力分布相对较高;导叶旋转角度的变化不会从根本上改变流场及叶片表面的压力分布,但会改变泄漏涡发生的初始位置以及涡核的拓展区,从而降低了泄漏涡对压力损失造成的影响,由于固体叶片具有良好的导热特性,改变导叶角度不会大范围地改变叶片表面的温度分布及热应力分布。     

涡轮第二级动叶冷却结构设计研究

以某涡轮第二级动叶为研究对象,结合参数化特征建模技术研究设计冷却结构,并研究了温度分布,结果表明:叶片的改型对于流道内的温度分布影响很小,而叶片内部温度的分布有一定变化.在叶片后腔所在区域底部截面上,温度下降了10 K左右,在中部截面和顶部截面上冷却效果没有明显改善.     

应用准三元流动分析的涡轮性能预测研究

为了提高涡轮性能预测的精确度，提出了一种涡轮叶轮准三元流动分析的预测方法。它是根据旋转系统边界层流动稳定性的理论，在叶轮内部准三元计算结果的基础上分别考虑旋转和叶片曲率对流动稳定性的影响，从而建立涡轮叶轮速度分布的评价指标来估算分离损失的大小，然后将此评价指标应用于涡轮性能预测程序的叶轮损失模型中。通过对２种车用涡轮增压器涡轮效率预测结果和试验结果的比较，证明运用此方法可以提高涡轮性能预测的精确度。     

带有热障涂层的涡轮叶片前缘气热耦合数值研究

采用气热耦合的数值计算方法以及考虑转捩的湍流模型,对采用热障涂层技术的某型气冷涡轮叶片前缘传热进行了数值研究.结果表明,由于热障涂层的高绝热性,热障涂层一方面大幅提高叶片的抗氧化和抗热腐蚀的能力,另一方面配合高效的冷却技术,可以降低金属叶片的工作温度和叶片内的温度梯度.     

考虑变比热的冷却涡轮弯曲叶栅流场的数值模拟

对采用弯曲叶片的某型高压涡轮导向器有／无冷气喷射时的栅内流场进行了数值模拟。应用了以冷气源项反映冷气掺混影响的三维变比热计算方法。结果表明,弯曲叶栅内的冷气喷射导致了马赫数和温度的变化;叶片表面和端壁得到有效的低温保护;在相同冷气流量下,压力面附近温度降低较吸力面明显,冷却气膜的作用也更为有效;栅内二次流对冷气分布有影响。     

一种适用于车用增压器涡轮的前弯后掠式叶轮

本文给出了车用增压器涡轮叶轮的一种新型结构——前弯后掠式叶轮。这是针对车用增压器涡轮的实际工作条件以及常规叶轮的不足，基于叶轮内部流动改善以提高涡轮的变工况适应性而提出的。文中详述了新型叶轮的设计思想及其理论和实验依据，并通过数值试验证明了前弯后掠式叶轮较常规叶轮在气动热力学机理上的改进。     

涡轮增压柴油机仿真模型修正方法及试验比较研究

基于AVL BOOST仿真软件,针对一台4缸涡轮增压柴油机进行建模,在原仿真模型的基础上着重考虑了涡轮增压器传热效应的影响。计算结果与发动机试验数据的比较分析表明:经过修正的发动机仿真模型在保证发动机扭矩、功率等主要性能参数不变的基础上,计算得到的涡轮及压气机进出口温差与原模型相比误差大幅度减小;同时修正后的仿真模型与原模型相比,新鲜空气的质量流量、涡轮膨胀比、压气机压比均无明显变化,表明修正后的模型并无改变涡轮增压器的工作点位置,仅修正了由于传热所导致的压气机出口和涡轮进口的温度变化,以及涡轮增压器的效率变化。     

基于流固耦合的增压器涡轮叶片结构强度分析

采用ANSYSWorkbench软件建立涡轮流固耦合仿真计算平台。首先,运用CFX软件对涡轮流体域进行流体动力学计算。随后,将流固交接面的温度、压力分布场加载到涡轮固体域表面,并进行稳态热计算。最后,运用ANSYS软件有限元分析模块对涡轮考虑气动温度载荷、压力载荷和离心力载荷的进行综合结构强度计算研究。结果表明,所分析的涡轮叶片根部的中间部分及近出口处存在应力集中现象,与用户反馈的该款增压器使用中涡轮叶片断裂部位较为吻合。     

不同冷气/燃气温比下高温涡轮叶片旋流冷却流固耦合特性研究

采用流固耦合方法对燃气轮机高温涡轮叶片旋流冷却结构进行数值模拟分析。探究了不同冷气/燃气温度比条件下旋流冷却的流动与传热特性、叶片前缘区域固体温度、热应力以及热应变分布。研究表明：在进气腔入口雷诺数固定的条件下,随着温度比升高,冷气密度降低,冷气流速逐渐提升,同时湍动能升高,靶面努塞尔数逐渐升高;当温度比较低时冷气的流速较低、单位时间冷气带走的热量较少,当温度比较高时冷气温度较高、单位质量冷气所能吸收的热量有限,靶面处热流密度先升高后降低。受靶面热流密度分布影响,随着温度比升高,叶片前缘固体的温度、热应力以及热应变先降低后升高。     

Conjugate heat transfer investigation on the cooling performance of air cooled turbine blade with thermal barrier coating

A hot wind tunnel of annular cascade test rig is established for measuring temperature distribution on a real gas turbine blade surface with infrared camera. Besides, conjugate heat transfer numerical simulation is performed to obtain cooling efficiency distribution on both blade substrate surface and coating surface for comparison. The effect of thermal barrier coating on the overall cooling performance for blades is compared under varied mass flow rate of coolant, and spatial difference is also discussed. Results indicate that the cooling efficiency in the leading edge and trailing edge areas of the blade is the lowest. The cooling performance is not only influenced by the internal cooling structures layout inside the blade but also by the flow condition of the mainstream in the external cascade path. Thermal barrier effects of the coating vary at different regions of the blade surface, where higher internal cooling performance exists, more effective the thermal barrier will be, which means the thermal protection effect of coatings is remarkable in these regions. At the designed mass flow ratio condition, the cooling efficiency on the pressure side varies by 0.13 for the coating surface and substrate surface, while this value is 0.09 on the suction side.     

2 MW风机叶片气热法防除冰的传热试验研究

在凝冻地区风电场采用气热法进行风机叶片防除冰工程应用时,叶片传热试验至关重要。文章针对现场2 MW风机叶片,结合叶片重点结冰区域分布,设计研发叶片传热试验系统并实施9 h传热试验。试验采用12支温度传感器和红外热成像技术监测记录叶片温度,并分析叶片传热过程及传热效果。传热试验结果表明,在叶片前缘通道内施加30 kW加热器持续加热叶片本体,无日照时叶片前缘外表面15 m处温度为39.4℃,40 m处温度为25.3℃,温升在10℃以上,且分别沿叶尖和后缘两侧方向呈现递减分布。验证了利用气热法对该复合材料叶片进行防除冰,在理论上和技术上是可行的。     

大功率汽轮机叶轮轮缘传热系数的研究

提出了大功率汽轮机叶轮轮缘总传热系数的计算方法.介绍了汽轮机动叶片叶身平均对流换热表面传热系数和叶片流道下壁面对流换热表面传热系数的计算方法和计算公式.把汽轮机叶片对叶轮的传热简化为肋片传热,使用肋片传热模型计算汽轮机叶片流道的等效传热系数,采用圆筒壁模型计算汽轮机叶轮轮缘的总传热系数,并给出了应用实例.在汽轮机转子的温度场与热应力场有限元分析中,该计算方法为确定叶轮轮缘的传热边界条件提供了依据.     

Stability of Boiling on Annular Fin Surfaces

A theoretical investigation was conducted to understand the stability of boiling on annular fin surfaces with different boundary conditions. Lyapunov's function was derived for boiling on annular fin surfaces; its characteristics near the steady distribution are particularly investigated. With no pre-assumed functional form for the temperature perturbation to be imposed to the boiling system, a general stability analysis was established by optimizing Lyapunov's function. The steady temperature distribution with isothermal or isoflux condition was obtained numerically, and the boiling heat transfer characteristic was noted to be dependent of the fin configuration and boundary conditions. Annular fin surfaces can significantly benefit the heat transfer, and the fins with small inner radii have better performance of base heat flux or temperature. The most unstable mode and maximum eigenvalue were employed to describe the boiling stability under various boundary conditions, and characteristics of the obtained maximum eigenvalue very well match with those of the boiling heat transfer on annular fin surfaces.     

基于流热耦合的燃气轮机透平叶顶冷却设计

燃气轮机透平叶顶区域存在复杂的流动和换热问题,承受很高的热负荷。为了降低透平动叶叶顶温度,在透平叶顶现有结构的基础上提出气膜冷却和气膜+内冷通道冷却两种叶顶冷却方案,并通过流热耦合计算分析冷却升级前后叶顶区域的换热和流动特性。研究发现：叶顶气膜冷却方案可有效降低叶顶温度,特别是叶顶前缘至中弦区域;而气膜＋内冷通道冷却方案基于外部气膜冷却,结合内部冷却通道设计,可进一步降低叶顶尾缘的温度;与原型叶片相比,气膜+内部冷气通道的复合冷却设计可以使叶顶尾缘最高温度降低24 K。     

凹坑深度对透平叶片前缘换热的影响

涡轮叶片前缘由于受到燃气的冲击,热负荷较高,其冷却和换热情况极大的影响了燃机的性能,因此是涡轮叶片上最关键的传热区,在对涡轮进行传热设计和计算时必须对该区域予以考虑。设计冲击靶面,对凹坑结构进行冲击,建立模型,通过数值计算分析其冷却效果。通过对凹坑的温度场进行对比分析,给出凹坑深度的变化对冲击靶面换热的影响。对于带凹坑结构,通过凹坑深度分析叶片前缘换热效果,当凹坑深度不太大时,凹坑深度的增加会增强冲击靶面的换热;当凹坑深度增加得较大时,则会明显降低冲击靶面的换热。     

Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different hole pitches

Experimental investigation has been performed to study the film cooling performances of cylindrical holes and laid-back holes on the turbine blade leading edge. Four test models are measured for four blowing ratios to investigate the influences of film hole shape and hole pitch on the film cooling performances Film cooling effectiveness and heat transfer coefficient have been obtained using a transient heat transfer measurement technique with double thermochromic liquid crystals. As the blowing ratio increases, the trajectory of jets deviates to the spanwise direction and lifts off gradually. However, more area can benefit from the film protection under large blowing ratio, while the is also higher. The basic distribution features of heat transfer coefficients are similar for all the four models. Heat transfer coefficient in the region where the jet core flows through is relatively lower, while in the jet edge region is relatively higher. For the models with small hole pitch, the laid-back holes only give better film coverage performance than the cylindrical holes under large blowing ratio. For the models with large hole pitch, the advantage of laid-back holes in film cooling effectiveness is more obvious in the upstream region relative to the cylindrical holes. For the cylindrical hole model and the laid-back hole model with the same hole pitch, heat transfer coefficients are nearly the same with each other under the same blowing ratios. Compared with the models with large hole pitch, the laterally averaged film cooling effectiveness and heat transfer coefficient are larger for the models with small hole pitch because of larger proportion of film covering area and strong heat transfer region.     

A general analytical solution to the equation of transient forced convection with fully developed flow

A general solution to the energy equation under zero wall temperature or zero heat flux boundary condition for the decay of an inlet and initial temperature distribution of an incompressible transient turbulent flow heat transfer between two parallel plates is given. It is shown that these solutions may then be used to obtain solutions due to unit steps in wall temperature or wall heat flux which is sufficient to sort out prescribed wall temperature and prescribed wall heat flux boundary condition. The results are confirmed experimentally by the frequency method. An experimental apparatus has been designed, built and used for this purpose.     

Al-Si合金与高温热管的传热性能试验

提出了一种基于太阳能碟式聚光器的Al-Si合金储能锅炉的构想,搭建了Al-Si合金与高温热管传热的实验平台。试验结果表明,Al-Si合金与高温热管之间的传热密度为54.4 kJ/m2。对Al-Si合金的传热温度分布进行模拟,以热流密度为54.4 kJ/m2,换热系数为200 W/(m2.K),空气温度25℃的对流边界条件时,模拟结果和试验测试结果比较吻合,为Al-Si合金储能锅炉设计提供了依据。