组合畸变对某型发动机稳定性的影响  

Investigation of the effect of combined distortion on engine stability

作　　者：黄顺洲[1] 胡骏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2006年第6期1085-1091,共7页Journal of Aerospace Power

摘　　要：压力和温度组合畸变对某涡轮风扇发动机稳定性影响的数值研究表明,该发动机的进口临界压力畸变强度和临界温度畸变强度分别为8.82%和8.60%,风扇的压力畸变敏感系数为2.608,高压压气机的温度畸变敏感系数为2.442。压力畸变和温度畸变的相对大小,决定了组合畸变对风扇或压气机稳定性影响的严重程度。压力畸变的相对最大强度峰值出现在风扇截面时,风扇首先失稳,反之则高压压气机首先失稳。组合畸变对发动机稳定性的影响,不是压力畸变和温度畸变单独影响的简单相加,而是一种非常复杂的非线性关系。The calculated effect of combined distortion on the engine stability shows that the critical values of pressure and temperature distortion are 8. 82% and 8. 60% respectively. The pressure distortion coefficient of the fan is 2. 608 and the temperature distortion coeffident of the compressor is 2. 442,. The magnitude of pressure distortion and temperature distortion determines the severity of the combined distortion effect on the fan or compressor stability. When the relative peak intensity of distortion appears at the fan section, the fan falls into instability first, otherwise the compressor does. The effect of the combined distortion on engine stability can＇t be calculated by superposing the effect of the pressure distortion to the temperature distortion simply, but in a complex nonlinear manner.

关 键 词：航空 航天推进系统 压力畸变 温度畸变 组合畸变 发动机稳定性 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]