Parametric study of turbine NGV blade lean and vortex design

The effects of blade lean and vortex design on the aerodynamics of a turbine entry nozzle guide vane (NGV) are considered using computational fluid dynamics. The aim of the work is to address some of the uncertainties which have arisen from previous studies where conflicting results have been reported for the effect on the NGV. The configuration was initially based on the energy efficient engine turbine which also served as the validation case for the computational method. A total of 17 NGV configurations were evaluated to study the effects of lean and vortex design on row efficiency and secondary kinetic energy. The distribution of mass flow ratio is introduced as an additional factor in the assessment of blade lean effects. The results show that in the turbine entry NGV, the secondary flow strength is not a dominant factor that determines NGV losses and therefore the changes of loading distribution due to blade lean and the associated loss mecha-nisms should be regarded as a key factor. Radial mass flow redistribution under different NGV lean and twist is demonstrated as an addition key factor influencing row efficiency.     

透平叶片变切削加工工艺数据库设计与开发

透平叶片是透平机械的核心零件之一,因其复杂的曲面造型和低刚度性,被认为是机械加工中的难题.通过Visual Basic编程语言进行叶片切削工艺数据库开发,在功能上实现面向叶片工艺变切削参数智能推荐、相似工艺实例推理和数控加工工序卡片、程序清单的输出,方便企业用户使用,提高工作效率和准确性..     

后掠叶栅发声机理的研究

本文研究了后掠叶栅的发声机理,并给出了相应的声压、声功率的计算公式。文中还讨论了转子尾流与后掠静子相互作用的干涉噪声随后掠角的变化规律,结果表明合理地选择后掠角将对干涉噪声的大小产生重要的影响。     

Numerical analysis for impacts of nozzle end-clearances on aerodynamic performance and forced response in a VNT turbine

It has been well known that nozzle end-clearances in a Variable Nozzle Turbine (VNT) are unfavorable for aerodynamic performance, especially at small openings, and efforts to further decrease size of the clearances are very hard due to thermal expansion. In this paper, both the different sizes of nozzle end-clearances and the various ratios of their distribution at the hub and shroud sides were modelled and investigated by performing 3D Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) simulations with a code of transferring the aerodynamic pressure from the CFD results to the FEA calculations. It was found that increasing the size of the nozzle end-clearances divided equally at the hub and shroud sides deteriorates turbine efficiency and turbine wheel reliability, yet increases turbine flow capacity. And, when the total nozzle end-clearances remain the same, varying nozzle end-clearances’ distribution at the hub and shroud sides not only shifts operation point of a VNT turbine, but also affects the turbine wheel vibration stress. Compared with nozzle hub clearance, the shroud clearance is more sensitive to both aerodynamic performance and reliability of a VNT turbine. Consequently, a possibility is put forward to improve VNT turbine efficiency meanwhile decrease vibration stress by optimizing nozzle end-clearances’ distribution.     

Effect of inlet rotating swirl on endwall film cooling for two representative hole arrangements

The swirl generator is widely used in lean-burn combustor to guarantee flame stability and reduce NO_x emissions. Thus, the non-uniformities induced by the swirler would affect and damage film-cooling effectiveness on the turbine components, even blow-off coolant coverage, to some certain extent. The arrangement of film-cooling holes was normally designed to be perpendicular to the axial direction and in standard straight row. In this work we experimentally studied the effects of inlet swirl and mass flow ratio on traditional film cooling holes arrangement and a new arrangement pattern whose holes are located along the isobars. Results indicated that the swirl perturbation would damage film coverage. The film-cooling effect of endwall on which the holes are along the isobars, is invariably more promising than that of endwall on which hole arrangement is perpendicular to axial with the same mass flow of coolant, whether the inlet conditions is uniform or not.     

有间隙涡轮叶栅壁面流谱实验与数值模拟研究

对具有 3 .6 %相对叶顶间隙的涡轮叶栅进行了壁面流动显示和三维流场数值模拟 ,分析了大叶顶间隙涡轮叶栅的壁面流动特点 ,从数值模拟上特别对尾缘附近的壁面流动结构进行了详细讨论。实验与计算结果表明叶栅尾缘附近的流动是非常复杂的 ,同时由于叶顶间隙的存在 ,上下尾缘附近的壁面流谱明显不同     

涡轮的重复进气道的试验研究

用小型涡轮取代蓄电池和高压气瓶作为导弹上的辅助能源是明显地发展趋势.重复进气涡轮能较好地适应这种辅助能源系统的要求.本文研究了涡轮的不同形状的重复进气道,及其与喷嘴的匹配,不同的喷嘴出口角、流速等因素对损失的影响,给出了在所研究的条件下最佳形状的重复进气道、喷嘴和重复进气道的最佳匹配.     

冲击粗糙肋壁面换热准则关系式的建立

模拟高性能航空发动机涡轮叶片弦中区冷却结构，建立冲击粗糙复合冷却实验模型，通过对大量实验数据的分析和整理，建立了换热准则关系式。与实验结果对比表明：该准则关系式与实验实测数据吻合较好，精度较高，对于冲击粗糙肋壁面复合冷却技术的研究和工程结构设计都具有一定的指导价值。     

涡轮叶片疲劳寿命公式及可靠性预测方法

本文推导了液体火箭发动机涡轮叶片疲劳寿命公式,并用概率统计、断裂力学方法,分析了可靠性预测方法.     

二次启动前火箭发动机泵构件温度特性数值计算

用数值计算的方法研究了液体火箭发动机在二次启动前，发动机泵系统各构件的温度特性和泵腔含汽率。建立了基于集总参数法的发动机启动前排放过程中涡轮、泵及进口管的温度变化计算模型。排放冷却过程中冷却剂N2O4的单相强制对流换热系数用Dittus-Boelter公式计算，流动沸腾换热系数采用Shan M M强化模型。并对某液体火箭发动机二次启动前排放过程涡轮泵系统各构件温度变化和泵腔含汽率进行了计算，模型计算结果与试车数据吻合良好，研究结果表明，二次启动前的主动排放过程对泵壳体及进口管的冷却效果很好。