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1、分类号 密级 U D C 编号 哈尔滨工程大学博士后研究工作报告黑龙江省博士后科学基金资助项目高负荷吸附式压气机叶栅实验研究陈绍文工作完成日期：2007年9月-2009年9月提交报告日期： 2009年10月哈尔滨工程大学（黑龙江）2009年10月黑龙江省博士后科学基金资助项目高负荷吸附式压气机叶栅实验研究MATERIALS TIIE MATERIALS CIIEMISTRY PROCESS FROM MOLECULES TO CRYSTALS博士后姓名：陈绍文合 作 导 师：刘顺隆 教授流动站（一级学科）名称：哈尔滨工程大学力学动力工程及工程热物理流动站（二级学科）名称：动力机构及工程研究工作
2、起始时间：2007年9月研究工作期满时间：2009年10月提 交 报 告 日 期：2009年10月哈尔滨工程大学2009年10月摘 要推重比1520或更高推重比发动机关键技术之一是提高压缩系统级负荷或压比，为了使得负荷或压比的增加不会引起压气机级数的增加，就需要研制更高载荷的叶片，加大叶片对气流的折转能力，而这将必然导致叶栅流道内三维分离的加剧，并引起二次流损失增加。附面层抽吸技术为满足高压比、高效率和宽喘振裕度的压气机设计要求提供了巨大的潜力，而吸气槽道的设计成为应用该项技术的关键点之一。利用数值和实验手段研究了附面层抽吸对低速高负荷压气机叶栅气动性能和流场特性的影响。首先，采用数值模拟手段
3、开发了适合低亚音速气流进口、并具有大叶型折转角的高负荷扩压叶栅叶型，并以此叶型为基础，数值研究了低速条件下附面层吸除对高负荷压气机叶栅气动性能的影响，分析了叶栅出口总压损失、扩压因子和气流角沿叶高的分布，并给出了吸力面极限流线及型面静压。结果表明，附面层吸除可有效改善叶栅气动性能，低能流体被吸除使得吸力面及角区的分离减小，叶栅负荷及扩压能力得到提升，且最佳吸气位置及吸气量的选定与扩压过程及栅内分离程度相关。由于吸气槽道位置和吸气量的设计对叶栅气动性能和流场特性至关重要，因此在之前数值研究的基础上，设计了四种不同开槽位置的高负荷叶栅进行了实验研究，分别为距离前缘25%、35%、48%和60%轴向
4、弦长开槽位置。每个开槽方案采用了三种吸气流量，分别为进口质量流量的0.5%、1.0%和1.5%。采用五孔探针详细测量了叶栅出口截面的气动参数，在叶片表面布置了静压测点测量了叶片表面的静压力分布，并利用墨迹流场显示方法对边界层的发展进行了描绘。结果表明，适合的抽吸位置和抽吸量可以有效改善高负荷压气机内的气动性能和流动特性，由于低能流体被有效吸除而吸力面分离得到抑制，且分离点之后吸除效果更好；吸力面采用附面层抽吸对叶展中部区域损失的改善要好于近端壁区。此后还实验研究了吸力面局部吸气和端壁吸气对叶栅气动性能和流动特性的影响，结果表明，采用端壁吸气对抑制角区分离流动、减弱通道涡强度和尺度、提高叶栅内流
5、动性能的效果要优于其它吸气方式，积聚在角区的低能流体在较大吸气量下被更多吸除是性能改善的关键。 关键词：高负荷扩压叶栅；附面层吸除；吸气位置；吸气量；实验研究AbstractImproving the stage loading and the pressure ratio of the compressor system is one of the key technologies of the engines with a thrust-weight ratio of 1520 or higher. More heavily loaded blades should be develope
6、d to prevent the increase of the compressor stage because of the improvement of stage load and pressure ratio. Severe flow separations occurred as stage loading and turning angle increased, resulting in a rapid secondary flow loss augmentation. The boundary layer suction technology has huge potentia
7、l in designing compressor to satisfy high pressure ratio, stall margin and efficiency, and the design of suction slot is the key of applying this technology.The effects of boundary layer suction on the aerodynamic performance and flow behavior of highly-loaded compressor cascades were investigated n
8、umerically and experimentally in low-speed condition. Numerical simulation is applied to develop a series of highly loaded compressor blade profiles which are suitable for low subsonic inlet flow and high-turning angle conditions. Based on the blade profile, the effects of boundary layer suction on
9、the aerodynamic performance of low-speed compressor cascade with super-highly loading have been numerically studied. The distribution of exit total pressure loss, diffusion factor and exit flow angle alone blade height have been analyzed, and suction limited streamline and profile static pressure al
10、so have been given. The results show that boundary layer suction improves effectively the aerodynamic performance of compressor cascade, and the flow separation at the corner will be restrained for low-energy flow aspirated, which results in the increase of blade loading and diffusion ability, and t
11、he diffusion process and the degree of the separation in compressor cascade relate to the selection of the optimal suction location and suction flow rate.Both the suction slot location and suction flow rate play important roles in the aerodynamic performance and flow behavior improvement of compress
12、or cascades, so fore sets of the highly-loaded compressor cascades with four suction locations of 25%, 35%, 48% and 60% axial chord length on the suction surface respectively were designed on the former bases of the numerical studies. The suction flow rates were 0.5%, 1.0% and 1.5% of the cascade in
13、let mass flow. The detailed cascade flow fields were measured by five-hole probe. Static pressure taps were installed on the blade surfaces to obtain the distribution of the static pressure. The ink-trace flow visualizations were performed to show the boundary layer development. The results show tha
14、t the appropriate suction slot location and suction flow rate will improve obviously the aerodynamic performance and flow behavior of highly-loaded compressor cascades. The flow separation on suction surface is restrained for low-energy flow aspirated, and the improvement is greater near the separat
15、ion point than after the separation point. The improvement of the loss near mid-span is greater than near end-wall.Furthermore，the effects of local suction and endwall suction on the aerodynamic performance and flow behavior of highly-loaded compressor cascades were also investigated experimentally. The results show that the influence of the endwall suction on suction effectiveness is better than that of the other suction types. The effective low-energy fluid removal due to a local higher suction flow rate is the key element of the performance impro
