热斑对涡轮级转静干涉噪声影响数值研究  

Investigation of tonal noise in high pressure turbine stage due to non-uniform inlet entropy of inflow

作　　者：母忠强[1] 乔渭阳[1] 赵磊[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2012年第3期666-673,共8页Journal of Aerospace Power

摘　　要：利用结合相位延迟方法的求解器,对进口有热斑存在的某高压涡轮级流场进行三维非定常计算,然后利用模态匹配方法在涡轮转子下游管道中提取出转静干涉离散噪声信息.通过与进口无热斑存在算例比较表明:在一倍叶片通过频率下,向下游传播的转静干涉离散噪声总声功率级增加了约5.9dB;在二倍叶片通过频率下增加了约11.6dB.Through using the flow solver which activated phase-lag method, got the three-dimensional （3-D） unsteady flow field in a high pressure turbine stage which had hot spots in inlet, and then by using the mode matching method in the duct of downstream ro tor, the rotor-stator interaction discrete noise which propagated downstream was obtained. After compared with the case without hot spots in turbine inlet, the results show that the total acoustic power level of rotor-stator interaction discrete noise emitted in the downstream direction is increased by 5.9 dB at the blade-passing frequency and by remarkably 11.6 dB at the first harmonic of the blade-passing frequency.

关 键 词：涡轮级转静干涉噪声 叶片通过频率 相位延迟方法 模态匹配方法 声功率级 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]