摘要
对一个具有典型涡轮导向器叶片型线的直叶栅，由叶片表面不同位置以不同的质量流量比喷射冷气，进行型面压力分布变化规律的实验研究。结果表明，前缘正对来流方向喷射冷气时压力变化较小。压力梯度和主流速度的不同使得压力面喷射冷气对压力分布的影响要小于吸力面喷射冷气时的情况。冷气射流对主流的滞止作用所造成的压力升高值比卵型涡导致的压力降低值小。从型面压力降低程度可以定性看出不同位置喷射冷气时卵型涡强度的大小。
The effects on turbine blade surface pressure distribution were investigated experimentally with air coolant discharge from each of nine individual rows of coolant holes on the blade surface in a rectilinear cascade with typical turbine guide van profile.Mass flow ratios of air coolant to mainstream were 0,0.6,and 1.2 percent,respectively.The experimental results showed that the variations of the surface pressure distribution were dependent chiefly on the amount of air coolant and the location of injecting holes.Injection from the blade leading edge right against the mainstream altered the surface pressure distribution slightly,and the pressure surface injection did not change the surface pressure distribution so obviously as the suction surface injection due to the difference of mainstream pressure gradients and mainstream velocity.In general,the surface pressure decrease caused by kidney-shaped vortex was more significant than the pressure increase due to the mainstream stagnation resulted from air coolant injection.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1998年第1期57-60,共4页
Journal of Aerospace Power
基金
国家自然科学基金
