摘要
为合理控制涡轮叶栅内超声速区域的流动结构、降低激波损失,提出一种跨声速涡轮叶型设计方法。通过构造叶栅跨声速流动区域的波系结构,采用预压缩等设计,在提高涡轮叶型气动负荷的同时降低了涡轮叶栅内激波强度。应用该方法完成了高压涡轮的气动改进。结果表明:全新的高负荷跨声速涡轮叶型设计方法,对提高涡轮气动效率和涡轮叶型气动负荷、降低跨声速涡轮叶栅内的激波损失具有明显的效果。
Transonic high pressure turbine（HPT） profile design was proposed to reasonably control the su-personic flow structure of the area and reduce the shock loss. By properly constructing the wave systemstructure of the transonic flow region and pre-compression design, the aerodynamic load of the profile wasincreased and the shock wave intensity was reduced. AHPT was improved aerodynamically by this method.Results show that the new high load transonic turbine blade design method can effectively improve the aero-dynamic load of turbine profile, reduce the shock wave loss in the transonic turbine and increase the aerody-namic efficiency of the turbine.
作者
陈云
王雷
马广健
CHEN Yun;WANG Lei;MA Guang-jian(AECC Shenyang Engine Research Institute,Shenyang 110015,China)
出处
《燃气涡轮试验与研究》
北大核心
2018年第3期18-21,37,共5页
Gas Turbine Experiment and Research
关键词
航空发动机
高压涡轮
跨声速
高负荷
叶型设计
激波
aero-engine
high pressure turbine
transonic
high loading
profile design
shock wave
