摘要
本文搭建了高速平面风洞实验台,在外部横流马赫数0～0.65、气膜孔压比0～2的范围内对圆柱孔、扇形孔、后倾扇形孔和收敛缝形孔进行了流量系数特性试验.基于试验数据建立了不同气膜孔型流量系数预测模型,完善了收敛缝形孔的流量系数预测模型.结果表明:无外部横流时,流量系数由大到小依次为扇形孔、后倾扇形孔、圆柱孔和收敛缝形孔;有外部横流时,其对气膜孔流量系数影响显著,外部横流降低了气膜孔的流量系数,且气膜孔压比越小外部横流马赫数的影响越大.
Abstract
In this paper,a high-speed plane wind tunnel test platform was built,and the discharge coef-ficient characteristics of cylindrical holes,fan-shaped holes,laidback fan-shaped holes and convergent slot holes were tested in the range of external crossflow Mach number 0-0.65 and gas film hole pressure ratio 0-2.Based on the test data,the flow coefficient prediction model of different gas film holes was es-tablished and the flow coefficient prediction model of convergent slot holes was improved.The results show that when there is no external crossflow,the discharge coefficients are fan-shaped holes,laidback fan-shaped holes,cylindrical holes and convergent slot holes in order from large to small.When there is external crossflow,it has a significant influence on the discharge coefficient of the gas film holes,and the external crossflow reduces the discharge coefficient of the gas film holes,and the smaller the gas film hole pressure ratio,the greater the influence on the Mach number of the external crossflow.
NETL
NSTL
万方数据