摘要
利用三维湍流数值模拟方法模拟某一级跨声速高压涡轮流场,研究转子叶片叶尖间隙高度对涡轮性能及二次流动损失分布的影响.研究结果表明:转子叶尖间隙高度对涡轮性能影响明显,随着间隙高度的增加涡轮效率明显降低,但效率的降低速度与间隙高度并非简单线性关系,间隙高度增加1%相对叶高,涡轮性能最快下降1.8%.分析表明:涡轮转子间隙高度变化主要影响转子叶栅通道上部流动并对通道内的损失分布产生影响.其中损失最严重的区域为转子通道中部至叶片尾缘处;尾缘后的损失则对间隙的高度最敏感,随着间隙高度的增加,叶片尾缘后损失明显增加.
The influence of the tip clearance height of turbine rotor blades on the aerody- namic performance and secondary flow losses of an axial turbine stage were investigated by numerical simulation and different tip clearance heights were taken into account. Results show that the efficiency of the turbine stage would decrease markedly due to the increase of the tip clearance height. The efficiency would decrease 1.8% as the tip clearance height in- creased 1% of blade relative height. Analyses of the rotor flow field indicated that as the height if tip clearance increased, the distribution of flow losses changed in the upper passage of the rotor. The most losses were induced in the region between the middle of the rotor blade and the trailing edge, while secondary flow losses increased most behind the trailing edge. Mixing losses were the main factors which led to the efficiency decreased as the height of tip clearance increased.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第1期169-175,共7页
Journal of Aerospace Power
关键词
航空发动机
高压涡轮级
叶尖间隙
流动损失
数值模拟
aero-engine
high pressure turbine stage
tip clearance
flow loss
numerical simulation
