涡轮叶片尾缘气膜冷却耦合传热的数值模拟

采用耦合方法对燃气轮机涡轮叶片尾缘气膜冷却流场进行数值模拟,并与绝热方法下的结果进行对比,得到不同吹风比和不同吸力面厚度下的气膜冷却规律。结果表明:与绝热方法相比,采用耦合方法时气膜冷却效率曲线更平缓,吸力面温度分布均匀,压力面尾部上方区域温度梯度较大;增大吹风比可以减弱吸力面导热对气膜冷却效率的影响,且能有效抑制流体与壁面的分离;随着吸力面厚度的增加,0.6～0.76等温度比线区域内流体温度发生变化,在劈缝出口下游温度升高,在下游的远距离处温度降低。     

燃气透平叶片尾缘内部冷却通道流动与换热特性研究

针对更为接近于真实叶片尾缘段的楔形内部冷却通道的流动与换热特性开展了数值研究,分析了不同冷却工质应用在楔形冷却通道中的性能表现以及不同扰流柱结构、柱肋组合冷却结构对尾缘内部冷却通道中的热力特性的影响.研究表明:区别于矩形内部冷却通道,楔形通道中壁面传热系数沿流动方向呈现逐渐升高的趋势;冷却工质对换热性能影响明显,蒸汽的...     

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.     

某型燃气轮机静叶空气系统分析

文章以某型燃气轮机第二级静叶空气系统为例,说明基于流体网络算法的Flowmaster软件在空气系统分析中的功用.分析结果表明,Flowmaster软件能较为准确地预测燃机在设计工况下的空气系统流量,且设计工况下的防止燃气侵入的空气系统结构设计是安全的.同时通过分析不同气封间隙工况,表明轮盘动静间隙泄漏流量随气封间隙的增加而增大.为保证较高的燃机运行效率,可将篦齿气封结构改为密封性能更好的刷子气封结构.     

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。     

涡轮叶片尾缘扰流柱对换热效果的影响

对一个有交叉排列圆形扰流柱的涡轮叶片尾缘冷却方案进行了数值研究.应用CFX计算程序对冷却方案进行了气热耦合计算,并对温度场、流场及换热系数的变化进行了详细的分析.结果表明,扰流柱对增强换热效果明显.     

多孔介质气体润滑轴承气热耦合研究

考虑气体温度梯度对工质物性及轴承热稳定性的影响,以及润滑气体和多孔介质的传热耦合,在满足Darcy定律条件下三维求解雷诺方程,计算了轴承间隙和多孔介质中气体的压力及温度分布。分析了3个给定供给压力(0.5、0.65和0.8 MPa)、3种轴承偏心率(0.2、0.5、0.8)对轴承的承载能力、偏位角及润滑流量的影响,计算结果表明：在不同的轴偏心率下均存在有一段轴承最佳渗透系数范围,表征该范围承载能力最强;偏心率越大,轴承承载能力越高,最佳渗透系数区间也越明显;轴承压缩数越大承载能力也越高;间隙中温度分布不均匀导致轴承承载能力降低,通过调整压力和偏心率增加介质的润滑流量,及时导出摩擦产生热量降低间隙中气膜温度,可使轴承平衡稳定运行。     

Computational Conjugate Heat Transfer Analysis of a Hybrid Electric Vehicle Inverter

ABSTRACT

A physics-based computational simulation of the heat transfer characteristics of an insulated gate bipolar transistor (IGBT) developmental inverter is reported. The simulation considers the fluid/thermal multiphysics interactions via a conjugate heat transfer analysis. The fluid phase includes air and liquid coolant; the solid phase, where the heat is conducted, includes various solid materials. Numerical solutions of the heat conduction and convection phenomena in and around the IGBT modules and the inverter, built as a three-dimensional computational model, are sought for by using parallel computing. Comparisons with the available experimental data show a satisfactory agreement of the inverter temperature at three power levels under two different coolant flow rates. Detailed examination of the flow field reveals that the design features of the rectangular coolant flow chamber in the heat sink and the small clearance between the tips of the pin fin and the walls lead to an evenly distributed coolant flow around most of the pin fins. The temperature distributions of the pin fins depend highly on their locations relative to the IGBT modules. The findings from the current study can be useful in future efforts to optimize the thermal performance of IGBT inverters.     

涡轮叶栅三维气热耦合数值模拟

本文借助数值模拟技术,通过气动热分析耦合计算研究了某型航空用涡轮第二级静叶在绝热及实心叶片耦合换热情况下的流道温度场分布,并分析了流场结构,特别是对叶片温度场分布结果进行了分析。通过对三维计算结果的分析表明,耦合计算得到的流场温度场分布更符合实际。耦合与非耦合计算的差别主要体现在温度场的不同上,进而导致了马赫数、压力场、波系及临界流量的不同。因此在气冷涡轮设计中使用多场耦合技术进行数值模拟是非常必要的。     

涡轮叶片尾缘偏劈缝结构二维模型的冷却研究

对叶片尾缘偏劈缝冷却结构的流动与换热进行了二维的数值模拟,研究了涡轮叶片尾缘无量纲长度L／H(即尾缘长度与冷气流出口的高度比)、偏劈缝喷射角a、吹风比M及Reynolds数(RP)对涡轮叶片尾缘平均冷却效果的影响。     

燃气透平第一级叶片燃气侧的流动与换热特性研究

对某重型燃气轮机透平第一级叶栅通道内无气膜冷却下的三维黏性流动与传热特性进行了数值模拟,对比了不同来流湍流度对叶片燃气侧流动与换热特性的影响,分析了静叶非定常尾迹对动叶换热特性的影响.结果表明:来流湍流度对静叶表面的换热特性有明显的影响,但对动叶表面换热特性的影响很小;静叶尾迹对动叶表面的换热特性影响较大.     

涡轮叶片尾缘端部冲击流动与换热特性研究

针对涡轮叶片尾缘吸力面热应力集中,容易造成叶片尾部烧毁的现象,提出端部冲击扰流柱结构,采用Realizable k-ε湍流模型和增强壁面函数分析涡轮叶片尾缘内部流场和吸力面换热特性,研究不同冲击孔与扰流柱排列方式的影响,揭示端部冲击扰流柱结构的流场与换热机理。研究表明,端部冲击扰流柱结构对于改善吸力面的换热效果要优于中间冲击扰流柱结构,对端壁的换热有显著提高;各表面平均换热系数均随着压比的增大而增大,顺排结构时,冲击孔换热最强,扰流柱换热次之;叉排结构时,冲击孔换热最强,隔板迎风换热次之;近距离冲击,顺排的综合效果优于其它几种结构,而远距离冲击,叉排的综合效果最好,其吸力面温度分布较均匀。     

Conjugate Heat Transfer Analysis for a Finite Thickness Cylinder in a Hypersonic Flow

Prediction of surface heating rates is of prime importance for the hypersonic flow regime. Experimental and conventional computational efforts overlook the heat transfer phenomenon in the solid due to the rigid assumptions involved in the solution methodologies. In order to address this fact, conjugate heat transfer (CHT) studies are carried out using various coupling techniques to examine their implementation abilities. Three types of solution methodologies are adopted, namely, decoupled, strongly coupled, and loosely coupled analysis. This study is also focused on looking into the effect of a hypersonic flow field on wall heat flux for a finite thickness insulating cylinder at moderately large time scales. Increase in wall temperature and decrease in surface heat flux have been noticed using strong and loose coupling techniques with an increase in simulation time. Decoupled fluid and solid domain analysis is found to be useful for typical shock tunnel test durations (～1 ms) while investigations with loose coupling techniques are advisable for time scales corresponding to flight testing (～1 s). Efforts are also made to reason the discrimination in prediction of stagnation point heat flux using conventional computational and experimental analysis.     

Conjugate Heat Transfer Analysis in a Glazed Room Modeled as a Square Cavity

A numerical study of conjugate heat transfer by turbulent natural convection in a room with three different glazed configurations is presented. The room is modeled as a square closed cavity, where the lower wall is adiabatic, the right wall is semitransparent, and the upper and left walls are opaque conductive surfaces. Governing equations of mass, momentum, and energy were solved by the finite volume method with a two equation turbulence model. The results are presented in terms of streamlines, isotherms, heatlines, turbulent viscosity isolines, and thermal parameters, such as indoor temperatures and heat transfer coefficients. From the three cases considered in this study, the reflective glass window was the optimal configuration from the thermal comfort point of view for both design days. On the contrary, the glass-film configuration showed the worst indoor thermal performance inside the cavity despite of being the configuration that allows lower energy transferred into the room through the glazed surface. A set of useful heat transfer correlations are obtained for building design applications and energy codes in temperate climates.     

透平叶片尾缘冷却结构唇板构型对流动和传热的影响

为了提高尾缘冷却效果和降低叶栅气动损失,采用SST k-ω模型研究简化的压力面射流冷却结构唇板构型对冷却效果的影响。结果表明:唇板改型可以提高射流出口段的传热强度,但会增大气动损失;在研究范围内抬升一倍下板尾部边界层厚度时综合效果最佳;速比0.5和1.0时,原型的射流出流后向上抬升,在下板表面附近产生低速区,降低当地传热强度;速比0.5时,原型下板尾缘出现分离区,并与板后的回流区发生掺混,改型结构增强射流刚性,分离点后移;改型结构在不同速比下的传热系数均有所增强,平均传热系数在3个速比下分别提高了26.31%、34.72%和15.33%,其中速比1.0的综合传热因子最高,传热系数增加的幅值最大,且总压损失增加不显著。     

Experimental Study of Heat Transfer in Gas Turbine Blades Using a Transient Inverse Technique

To enhance specific power output and thermal efficiency of gas turbine engines, industry searches for ways to increase the turbine inlet temperatures. Therefore, temperatures of turbine blades increase as well and necessitate active cooling of these components. Experimental design work on such internal cooling schemes is carried out to find acceptable compromises between heat transfer and pressure losses. It is often carried out by using transient thermochromic liquid crystal techniques in combination with Plexiglas models. However, for real turbine blades this experimental technique is inappropriate due to the lack of optical access. Therefore, to study actual turbine blades there is need for development of noninvasive, nondestructive methodologies. This article describes a measurement technique that allows determination of internal heat transfer coefficients of real turbine blades experimentally. Thus, a test rig with a rapidly responding heater was designed to fulfill the requirement of a sudden increase in the air temperature within the cooling passages. The outer surface temperatures were measured using infrared thermography. To estimate the spatial distribution of internal heat transfer coefficients from transient surface temperatures the inverse heat transfer problem was solved. As optimization algorithm the Levenberg–Marquardt method was chosen. Outer surface temperature data was measured for a rectangular reference model with rib turbulators and compared with simultaneously acquired data using the thermochromic liquid crystal technique. It is concluded that the new experimental measurement technique could be used to quantitatively determine internal heat transfer coefficients.     

叶片热障涂层结构内的非定常传热效应

在热冲击与脉动热流边界条件下,应用数值方法求解一维非傅立叶导热方程,分析双层结构热障涂层内的一维非定常传热特性。计算模型引入壁面曲率修正,考虑了涡轮叶片表面的型线曲率影响。分析结果表明:涂层材料热松弛时间的长短是瞬态传热特性的决定因素。边界受瞬态冲击热流条件下,涂层内的温度分布在10倍的松弛时间后达到平衡分布。边界热流脉动周期与松弛时间相当时,涂层内热流出现了波状传输,热障涂层内的温度呈波状分布。非傅立叶导热方程预测的温度交变厚度大于抛物型方程预测的厚度,显示了高频热流作用下,涂层材料可能发生疲劳破坏。叶片表面的的凸形曲率以指数率形式,增强了涂层内温度波幅度,解释了叶片前缘等处涂层易出现裂纹的现象。     

Fundamental Mechanisms That Influence the Estimate of Heat Transfer to Gas Turbine Blades

The quest for improved efficiency has motivated the elevation of turbine inlet temperatures in all types of advanced aircraft gas turbines. The accommodation of higher gas temperatures necessitates complex blade cooling schemes so as not to sacrifice structural integrity and operational life in advanced engine designs. Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major uncertainty because of the complexity of the heat transfer processes. The gas flow through these blade rows is three-dimensional with complex secondary viscous flow patterns that interact with the end walls and blade surfaces. In addition, upstream disturbances, stagnation flow, curvature effects, and flow acceleration complicate the thermal transport mechanisms in the boundary layers. Some of these fundamental heat transfer effects will be discussed. The chief purpose of this paper is to acquaint those in the heat transfer community, who are not directly involved in gas turbines, with the seriousness of the problem and to recommend some basic research that would improve the predictions of gas-side heat transfer on turbine blades and vanes.     

燃气轮机罩壳内的流动阻力和传热特性计算

为了建立具有异型结构和复杂流动过程的燃气轮机罩壳系统内部阻力和传热特性的工程计算模型,采用Fluent软件结合UDF函数对罩壳内三维流场和传热特性进行了数值模拟,并用燃机电厂实测数据进行了验证.采用数值模拟结果对异型结构通道的阻力工程计算公式和燃机本体保温层外的对流传热系数分别进行了修正.修正后的工程算法结果表明保温层...     

Improvement of a Turbulence Model for Conjugate Heat Transfer Simulation

For the conjugate heat transfer simulation, two-equation turbulence models will predict an anomalously large growth of turbulent kinetic energy in high strain rate flows, and then the flow and heat transfer will be unreasonable. The current study improved the low Reynolds number Chien k-? two-equation model using the “realizability” based C _μ limiter and the production term P _k limiter. This study was conducted based on a developed preconditioned density-based conjugate heat transfer algorithm. Calculations are presented for the flat plate turbulence flow and the conjugate heat transfer of the MarkII cooling turbine blade using the improved model. The results were analyzed and compared with semi-empirical formula and experimental data. Significant improvement in the turbulent kinetic energy anomaly was obtained using both limiters. The prediction accuracy of the Chien k-? model for the flow and heat transfer in the conjugate heat transfer simulation was significantly enhanced. The changes in the model are guaranteed to not have unfavorable influence on the simulation of low strain rate flows.