摘要
以诱导轮与叶轮组合式航空燃油离心泵为研究对象,开展了轴向力出口间隙补偿优化研究.进行了轴向力的数值模拟,并将仿真结果与理论计算进行对比,对比表明两种方法计算的轴向力结果变化趋势一致,误差不大于4%,且设计流量工况下误差最小,进而验证了基于Pumplinx环境下该型离心泵轴向力数值仿真的正确性.通过改变出口间隙宽度分析离心泵的轴向力变化,仿真结果表明:扩大出口间隙至0.2mm时,增大了轴向力,且影响了泵的增压能力;而减小出口间隙至0.1mm和0.13mm时实现了轴向力的补偿,且出口间隙为0.1mm时性能最优.最后对出口间隙为0.1mm时的轴向力性能进行了分析,分析表明:该条件下不同截面的压力分布正常稳定,且设计点的轴向力为3 620N,从而实现了诱导轮与叶轮组合式离心泵的轴向力间隙补偿.
As the research object of inducer and impeller combination aero fuel centrifugal pumps,the outlet clearance optimization on axial-force of the pump was carried out.Through comparing the axial-force simulation data with theoretical calculation data,the axial-force trends of the two methods were identified similar and the simulation＇s accuracy was verified by Pumplinx because of the error less than 4%.Then the outlet clearance＇s influence on axial-force was analyzed.Simulation results show that expanding the clearance to 0.2mm increases the axial-force value,and reduces the pressure charging;but reducing the clearance to 0.1mm and 0.13 mm can make optimizations of the axial-force,and the clearance of 0.1mm is the best.The axial-force performance of the model with clearance of 0.1mm was analyzed finally,showing that this model＇s inner performance of different sections is normal and steady;the axial-force value at design point is 3620 N,so reducing the outlet clearance to 0.1mm can make a high optimization about axial-force of the inducer and impeller combination centrifugal pump.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第11期2765-2772,共8页
Journal of Aerospace Power
关键词
航空燃油离心泵
诱导轮与叶轮
组合式
轴向力
出口间隙补偿
aero fuel centrifugal pump
inducer and impeller
combination
axial-force
outlet clearances optimization
