摘要
为了探究不同进口总压分布对涡轮气动损失的影响规律及作用机理,以 GE-E3 发动机高压涡轮的第 1 级导叶为研究对象,通过设定总压畸变高度和强度,利用数值模拟方法对多种涡轮进口 1 维分布形式下的涡轮气动性能展开研究。结果表明:当端区总压强于中展区总压时,静叶压力面附近流体向中展区汇集碰撞,出口效率降低;随进口总压畸变强度的提高,静叶出口效率线性降低;当端区总压弱于中展区总压时,静叶出口效率变化不大;单级涡轮出口效率随总压畸变形式变化的规律与静叶的类似。
In order to investigate the effect of different inlet total pressure distribution on turbine aerodynamic loss and its mechanism, the first stage guide vane of GE-E3 engine high pressure turbine was studied by setting the total pressure distortion height and intensity. The turbine aerodynamic performance in the form of one -dimensional distribution of various turbine inlet was studied by numerical simulation method. The results show that when the total pressure of the endwall is higher than the total pressure of the midspan,the fluid near the vane pressure surface accumulates and collides with the midspan,and the exit efficiency decreases. With the increase of the inlet total pressure distortion intensity,the outlet efficiency of the vane decreases linearly. When the total pressure of the endwall is weaker than the total pressure of the midspan,the outlet efficiency of the vane does not change much. The variation of outlet efficiency with total pressure distortion of single stage turbine is similar to that of vane.
作者
史文通
伊卫林
季路成
SHI Wen-tong;YI Wei-lin;JI Lu-cheng(School of Mechanical Engineering,Beijing Institute of Technology,Beijing 100081,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《航空发动机》
北大核心
2019年第3期17-25,共9页
Aeroengine
基金
国家自然科学基金(51476010、51376023)资助
关键词
涡轮进口
不均匀分布
总压梯度
数值模拟
GE-E3
发动机
转捩
航空发动机
turbine inlet
nonuniform distribution
total pressure gradient
numerical simulation
GE-E3 engine
transition
aeroengine
