下缘板孔对涡轮叶片尾缘内冷通道流动换热影响的数值研究

涡轮叶片下缘板出气孔对内冷通道的流动和换热性能有较大影响。通过数值模拟方法研究下缘板出 气孔对尾缘和下缘板双路出气涡轮叶片尾缘内冷通道内的流动和换热特性,对比分析孔径、孔形和孔位置对尾 缘溢流孔流量系数、尾缘出流比、尾缘通道内总压系数和尾缘内冷腔壁面换热特性的影响。结果表明:下缘板 出气孔孔径对流量系数分布的影响显著,孔径增大,尾缘溢流孔流量系数下降,尾缘出流比减小,尾缘内冷通道 内压力损失降低,内冷腔平均换热系数增大;孔形对上游内冷通道内流动和换热几乎没有影响;孔位置变化对 内冷通道壁面整体的换热系数影响很小,对局部影响较大。     

Parametric analyses for synthetic jet control on separation and stall over rotor airfoil

Numerical simulations are performed to investigate the effects of synthetic jet control on separation and stall over rotor airfoils. The preconditioned and unsteady Reynolds-averaged Navier–Stokes equations coupled with a k x shear stream transport turbulence model are employed to accomplish the flowfield simulation of rotor airfoils under jet control. Additionally,a velocity boundary condition modeled by a sinusoidal function is developed to fulfill the perturbation effect of periodic jets. The validity of the present CFD procedure is evaluated by the simulated results of an isolated synthetic jet and the jet control case for airfoil NACA0015. Then, parametric analyses are conducted specifically for an OA213 rotor airfoil to investigate the effects of jet parameters(forcing frequency, jet location and momentum coefficient, jet direction, and distribution of jet arrays) on the control effect of the aerodynamic characteristics of a rotor airfoil. Preliminary results indicate that the efficiency of jet control can be improved with specific frequencies(the best lift-drag ratio at F+= 2.0) and jet angles(40 or 75) when the jets are located near the separation point of the rotor airfoil. Furthermore, as a result of a suitable combination of jet arrays, the lift coefficient of the airfoil can be improved by nearly 100%, and the corresponding drag coefficient decreased by26.5% in comparison with the single point control case.     

调控收入差别,缩小收入差距

全面建设小康社会是党的十六大确立的奋斗目标.全面建设小康社会要求我们重视收入分配,当前收入分配的改革重点应放在缩小收入差距上,通过收入分配的市场公平和社会公平来促进全面建设小康社会.     

变循环发动机组合变几何调节方案

基于面向对象的设计思想,设计出了一个双涵道变循环发动机(VCE)的性能计算模型,并选取了双涵道VCE具有代表性的典型工作点,进行了双涵道VCE的组合变几何调节的相关研究.结果表明:在双涵道VCE的亚声速巡航和超声速巡航工作点,合理调节风扇导流叶片角度可以更大程度发挥双涵道VCE性能优势;在亚声速巡航工作点时选取的方案4和超声速巡航工作点时选取的方案4均比双涵道VCE设计点的变几何调节方案性能更优.     

Transient simulation of regression rate on thrust regulation process in hybrid rocket motor

The main goal of this paper is to study the characteristics of regression rate of solid grain during thrust regulation process. For this purpose, an unsteady numerical model of regression rate is established. Gas–solid coupling is considered between the solid grain surface and combustion gas.Dynamic mesh is used to simulate the regression process of the solid fuel surface. Based on this model, numerical simulations on a H2O2/HTPB(hydroxyl-terminated polybutadiene) hybrid motor have been performed in the flow control process. The simulation results show that under the step change of the oxidizer mass flow rate condition, the regression rate cannot reach a stable value instantly because the flow field requires a short time period to adjust. The regression rate increases with the linear gain of oxidizer mass flow rate, and has a higher slope than the relative inlet function of oxidizer flow rate. A shorter regulation time can cause a higher regression rate during regulation process. The results also show that transient calculation can better simulate the instantaneous regression rate in the operation process.     

燃油喷嘴主要性能参数的影响因素及调试技术

燃油喷嘴是航空发动机燃烧室的一个主要元件,它的主要功用是按照发动机不同的工作状态,供给燃烧室合适数量的、具有良好雾化质量的燃油。喷嘴的供油量是保证发动机推力要求、影响燃烧效率和性能的一个主要指标。根据燃油喷嘴的不同结构,对影响发动机燃烧室性能的流量、喷雾锥角和分布不均匀度等参数进行理论分析,并结合实际调试情况进行验证,解决了燃油喷嘴性能试验时流量、喷雾锥角和分布不均匀度调试困难的技术瓶颈,具有较大的指导意义和广阔的应用前景。     

用两端安装法检定热电偶

利用一种设计好的专用检具 ,使两束被检热电偶分别从检定炉的两端安装均可保证符合检定规程的要求 ,从而在不添置新设备的情况下 ,使检定热电偶效率大大提高。     

多模式离子推力器流率特性实验研究

为了实现多模式离子推力器在宽功率范围内最优性能和可靠性,基于30cm多模式离子推力器通过实验开展了阴极和中和器羽状模式转变点流率、放电电压30V对应阴极流率和放电损耗曲线与束电流关系研究。30cm多模式离子推力器束电流从0.3A增加到3.3A时,阴极羽状模式转变点流率值从0.017mg/s增加到0.163mg/s,放电电压30V对应阴极流率从0.129mg/s增加到0.231mg/s,中和器羽状模式转变点流率从0.030mg/s增加到0.191mg/s。随放电室工质利用率的增加,在小束电流下放电损耗迅速增加;当束电流大于1.5A时,放电损耗对放电室工质利用率的变化较为迟钝。基于上述流率特性实验结果完成了30cm多模式离子推力器宽功率范围35个工作点下最佳流率设计。在设计的工作流率下,放电电压小于30V,阴极和中和器均工作在点状模式,实测推力为9.6mN~185.2mN、比冲为1332s~3568s、功率为258W~4761W。     

延伸冲击孔冲击冷却流动与换热特性的数值研究

采用数值模拟方法研究了延伸冲击孔冲击冷却系统的冷却特性,分析了3个冲击雷诺数和5个冲击孔延伸长度对冲击腔内流动与换热特性的影响,给出了靶面努塞尔数分布、靶面压力分布、中心截面流速与综合换热性能的变化。结果表明：延伸冲击孔可以有效地防止横流对冲击射流的偏转作用,同时使射流出口更加贴近冲击靶面壁面,冲击速度更高,可以明显提高靶面的换热系数,并使整个靶面上的换热系数分布也更加均匀。冲击冷却的冷却性能随着冲击孔延伸长度的增加而增加,相较于传统冲击冷却（baseline）,在L/d=2.5时靶面平均努塞尔数提升达15%以上,但压力损失也相对较高;对比不同延伸长度冲击孔的综合换热性能,发现存在最佳的L/d取值范围使冲击冷却系统获得最佳的综合冷却性能。在本研究范围内,最佳的L/d= 2.5。     

双层多支板流道组合件变形控制

双层多支板流道组合件是薄壁焊接机匣,与涡轮后机匣和外支撑环组合件连接,是低压涡轮部件上的重要连接、承力件.该件焊缝密集,结构刚性差,安装边连接孔和篦齿环槽口位置度、尺寸精度高,加工难度大.采用多种工艺措施控制焊接变形,增加辅助支撑减小加工变形,综合运用筒体胀形、焊接、激光切孔、机械加工等加工工艺,实现了薄壁双层多支板流道组合件制造.