弯曲壁上开孔倾角对气膜孔流量系数的影响

对弯曲壁上的多孔气膜冷却方式的流量系数进行了实验研究, 目的是确定在一定曲率的弯曲壁上不同开孔倾角冷却孔的平均流量系数随压力参数的变化规律, 并从流动损失方面进行深入分析.研究结果表明, 对于几何参数一定的多孔冷却方式, 影响其流量系数的气动因素用压力参数来表示是合理的, 但对于不同的开孔倾角, 压力参数对流量系数的影响效果有很大差别.      

气冷涡轮叶片三维换热问题计算

建立了三维气冷涡轮叶片换热计算的热-流耦合计算模型, 将辐射热量作为源项加入到方程中, 采用热-流耦合方法完成了某气冷涡轮叶片带辐射的三维换热计算.辐射热量的计算采用了P-1辐射模型, 比较了计算辐射和不计辐射时叶片表面的温度值及温度分布的差异.计算表明对于1600 K这样的高温燃气, 辐射热量不可忽略, 考虑辐射热量后, 叶片温度明显升高, 温度分布也产生了显著差异.      

高压涡轮动叶内部冷却结构的改进设计

对某型高压涡轮动叶的内部冷却结构进行了详细的分析,提出了具体的改进方案,并利用有限元方法对改进前后的方案进行了叶片温度分布计算分析。结果表明,在相同冷却空气流量比的条件下,叶片尖截面表面最高温度降低了33°C,截面温差减小了131°C,改进效果明显。同时,改进后的冷却结构有效降低了叶片进口压力,提高了预旋喷嘴压比,减轻了高压涡轮转子的重量,达到了增加发动机推重比,减少冷却空气泄漏量,改善发动机性能的目的。     

先进涡扇发动机空气系统与零件传热设计技术验证

本文简要介绍了中国燃气涡轮研究院在先进涡扇发动机空气系统与零件传热设计技术验证方面的研究情况,内容涉及发动机空气系统设计技术、零件热分析设计技术、涡轮叶片冷却设计技术及新型铸冷双层壳型高效涡轮冷却叶片设计中的关键技术。探讨了空气系统与零件传热设计技术中的设计计算方法、设计软件校核与改进、试验研究与参数测试、以及设计体系建设等问题,通过系统的模型、部件和发动机整机三个层次的试验验证,初步形成了空气系统与零件传热设计体系。     

大型双曲冷却塔平均风荷载的数值模拟研究

对双曲冷却塔的平均风荷载进行CFD数值模拟,获得冷却塔内外表面的三维流场特性和各高度截面的平均风压系数分布曲线,并与以往文献的实测数据和风洞试验结果进行比较,以验证数值模拟的准确性.根据内外表面的风速矢量图,描述冷却塔内外流体的流动特征,发现旋涡的存在使风压分布趋于均匀的规律.并分析塔底的边缘效应及其对冷却塔内外表面风压的影响.讨论现行设计规范在外压的三维效应和内外压的共同作用等方面的不完善之处,给出部分改进建议和冷却塔外表面、内表面和内外表面压差的风压系数等压图,以供设计参考.     

Designing a power plant with highest efficiency:results from SFB 561

The goal of Collaborative Research Centre(SFB) 561 "thermally highly loaded,porous and cooled multi-layer systems for combined cycle power plants" is to expand the current technological and scientific knowledge on power plants in order to achieve total efficiencies of 65% in a combined cycle power plant in the year 2025.Therefore,the aero-thermomechanical,structural-mechanical,materials' scientific and production fundamentals for the development of steam and gas turbine components that are able to withstand highest thermal loads are being worked out within this SFB.This means for the gas turbine that combustion chamber outlet temperatures of 1520℃ at 1.7MPa are to be attained.In order to control these high temperatures,it is not only required to develop new materials' solutions,including thermal barrier coatings,but also to apply improved cooling techniques,as for example effusion cooling.This novel cooling concept is to be realised through open-porous structures.These structures can consist of drilled open-porous multi-layer systems or open-porous metallic foams.The development of graded multi-layer systems is also extremely important,as the grading will enable the use of coolant in dependence of the requirements.The live steam parameters in the high pressure turbine are expected to be increased up to approximately 700℃ with pressure of 30MPa.These elevated steam parameters can be encountered with Ni-base alloys,but this is a costly alternative,associated with many manufacturing difficulties.Therefore,the SFB proposes cooling the highly loaded turbines instead,as this would necessitate the application of far less Ni-base alloys.To protect the thermally highly loaded casing,a sandwich material consisting of two thin face sheets with a core of a woven wire mesh is used to cover the walls of the steam turbine casing.The current state of the research shows that by utilising innovative cooling technologies a total efficiency of 65% can be reached without exceeding the maximum allowable material temperature,thereby prolonging the life-span.      

Isothermal study of effusion cooling flows using a large eddy simulation approach

An isothermal numerical study of effusion cooling flow is conducted using a large eddy simulation(LES) approach.Two main types of cooling are considered,namely tangential film cooling and oblique patch effusion cooling.To represent tangential film cooling,a simplified model of a plane turbulent wall jet along a flat plate in quiescent surrounding fluid is considered.In contrast to a classic turbulent boundary layer flow,the plane turbulent wall jet possesses an outer free shear flow region,an inner near wall region and an interaction region,characterised by substantial levels of turbulent shear stress transport.These shear stress characteristics hold significant implications for RANS modelling,implications that also apply to more complex tangential film cooling flows with non-zero free stream velocities.The LES technique used in the current study provides a satisfactory overall prediction of the plane turbulent wall jet flow,including the initial transition region,and the characteristic separation of the zero turbulent shear stress and zero shear strain locations.Oblique effusion patch cooling is modelled using a staggered array of 12 rows of effusion holes,drilled at 30° to the flat plate surface.The effusion holes connect two channels separated by the flat plate.Specifically,these comprise of a channel representing the combustion chamber flow and a cooling air supply channel.A difference in pressure between the two channels forces air from the cooling supply side,through the effusion holes,and into the combustion chamber side.Air from successive effusion rows coalesces to form an aerodynamic film between the combustion chamber main flow and the flat plate.In practical applications,this film is used to separate the hot combustion gases from the combustion chamber liner.The numerical model is shown to be capable of accurately predicting the injection,penetration,downstream decay,and coalescence of the effusion jets.In addition,the numerical model captures entrainment of the combustion chamber mainstream flow towards the wall by the presence of the effusion jets.Two contra-rotating vortices,with axes of rotation along the stream-wise direction,are predicted as a result of this entrainment.The presence and characteristics of these vortices are in good agreement with previous published research.      

涡轮叶片吸力面上收敛缝形孔气膜冷却对叶栅气动损失的影响

 运用RNG湍流模型对具有气膜冷却的涡轮叶栅通道内部的三维流场进行了数值模拟,分析在叶栅通道主流入口雷诺数Re=4×105~6×105和二次流吹风比M=0.5~3.0范围内,沿吸力面3个典型弦向位置处(分别对应叶栅通道喉部上游、喉部和喉部下游)开设收敛缝形孔对叶栅通道损失系数的影响。计算结果表明：冷气喷射仅对孔附近区域的压力系数产生影响;位于喉部上游位置收敛缝形孔的能量损失及总压损失系数最低,大部分工况中位于喉部下游位置收敛缝形孔的损失系数最高;与圆形孔相比,位于喉部上游位置收敛缝形孔既具有好的冷却效率又具有低的损失系数。     

Measured overall effusion cooling effectiveness over a wide blowing ratio range using infrared imaging

Experimental investigations were performed on the overall cooling effectiveness η of a flat effusion wall over a wide range of blowing ratio(M=0.47～5.27).The effusion wall had a staggered multi-hole pattern typical of gas turbine combustor application,with a ratio of hole pitch to row spacing P/S=1∶2,a porosity PS/d2=72,and an inclination angle α=30°.The current paper documented distribution of the overall cooling effectiveness on the wall surface,based on infrared imaging of the 2-D surface tem...      

基于大涡模拟分析气膜冷却的湍流场

用大涡模拟考察了单孔平板气膜冷却的湍流场,气膜孔沿流向倾斜30°,气膜出流的雷诺数为2600,吹风比为0.5.计算结果表明:①气膜孔内的流动分离增加了湍流动能,导致气膜冷却效率的降低,在设计中要尽量避免或减少流动分离;②与射流侧向扩展有关的涡黏性系数在气膜孔两侧存在峰值,而采用各向同性的湍流模型预测气膜冷却时,涡黏性系数的峰值出现在射流与主流的剪切区,因此会高估射流的垂直穿透而低估射流的侧向扩展;③可以用大涡模拟辅助建立各向异性的湍流模型,以便提高湍流模型的预测精度.