论文部分内容阅读
为降低跨音压气机叶尖损失,开展超音叶栅流动机理及叶型设计研究。首先考虑栅前激波损失,并引入极限特征线上的等熵马赫数和总压恢复系数,得到更准确的唯一进气角计算方法;然后将此计算方法用于超音叶型设计,给出叶型前段形状;最后结合经验和理论分析,完成叶型后段设计。研究结果表明:此设计实现三道斜激波加一道正激波组合增压;在设计点,静压比为2.27,总压比为1.99,总压损失系数为0.091(对应效率0.902);在近失速点时,正激波移至喉道处,叶栅总压损失系数最小;正激波移至叶栅出口时,正激波最强,总压损失系数最大。
In order to reduce the transonic compressor tip loss, carry out the supersonic cascade flow mechanism and leaf design research. Firstly, considering the shock loss before grid and introducing the isentropic Mach number and the total pressure recovery coefficient on the limit characteristic line, a more accurate calculation method of the single inlet angle is obtained. Then, this calculation method is applied to the design of supersonic leaves, Out of the previous shape; the last combination of experience and theoretical analysis, to complete the back leaf design. The results show that this design achieves a combination of three diagonal shock waves plus a positive shock wave. In the design point, the static pressure ratio is 2.27, the total pressure ratio is 1.99, the total pressure loss coefficient is 0.091 (corresponding to an efficiency of 0.902) At near stalling point, the positive shock wave moves to the throat and the total pressure loss coefficient of the cascade is the smallest. When the positive shock wave moves to the exit of the cascade, the positive shock wave strongest and the total pressure loss coefficient is the largest.