Aerodynamic instabilities in transonic centrifugal compressor
Aerodynamic instabilities in transonic centrifugal compressor
复制标题
DOI：
10.1051/meca/2014023
复制
发表时间：
2014-03
影响因子：
1.2
通讯作者：
N. Buffaz;I. Trébinjac
中科院分区：
文献类型：
--
作者：
N. Buffaz;I. Trébinjac
本文分析了跨音速离心压气机在不同转速下的不稳定性起始。根据在诱导轮、无叶扩压器和有叶扩压器中植入非定常压力传感器获得的实验结果进行了分析。超过稳定极限，无论速度如何，压缩机都进入深度喘振而没有任何前兆。喘振过程是由叶片扩压器内的大量附面层分离引起的。对于低速，连同在扩压器中保持触发的喘振，在诱导轮中检测到空气动力学不稳定性。这些不稳定性可以被理解为“叶尖间隙旋转扰动”，因为它们产生于叶轮主叶片的前缘处，并且沿着叶尖间隙轨迹移动。
This paper presents the analysis of the instabilities inception in a transonic centrifugal compressor for different rotation speeds. The analysis was conducted from experimental results obtained with unsteady pressure sensors implanted in the inducer, vaneless diffuser and vaned diffuser. Beyond the stability limit the compressor enters into a deep surge without any precursor, whatever the speed. The surge process is initiated in the vaned diffuser by a massive boundary layer separation. For low speeds, together with the surge which remains triggered in the diffuser, aerodynamic instabilities are detected in the inducer. These instabilities can be understood as “tip clearance rotating disturbances” because they are generated at the leading edge of the impeller main blades and move along the tip clearance trajectory.