摘要
本文提供了一个计算大功率汽轮机末级动叶顶部截面跨音速叶栅的极限进气角的方法.按本方法求得的极限进气角与吹风试验及数值试验的结果吻合较好.
A way of calculating the marginal inlet angle of transonic turbine cascade at long blade tips of large turbines is given. The marginal inlet angle thus obtained fits well with wind tunnel test results as well as existing calculations.
出处
《动力工程》
CSCD
1990年第2期1-4,共4页
Power Engineering
