Discussion on back-to-back two-stage centrifugal compressor compact design techniques

2013年第8卷第4期

摘要

关键词

相关研究

回顶部

《机械工程前沿（英文）》 >> 2013年第8卷第4期 doi: 10.1007/s11465-013-0278-2

Discussion on back-to-back two-stage centrifugal compressor compact design techniques

School of Jet Propulsion, Beihang University, Beijing 100191, China

发布日期： 2013-12-05

HTML23 PDF 3 收藏 0

摘要

Design a small flow back-to-back two-stage centrifugal compressor in the aviation turbocharger, the compressor is compact structure, small axial length, light weighted. Stationary parts have a great influence on their overall performance decline. Therefore, the stationary part of the back-to-back two-stage centrifugal compressor should pay full attention to the diffuser, bend, return vane and volute design. Volute also impact downstream return vane, making the flow in circumferential direction is not uniformed, and several blade angle of attack is drastically changed in downstream of the volute with the airflow can not be rotated to required angle. Loading of high-pressure rotor blades change due to non-uniformed of flow in circumferential direction, which makes individual blade load distribution changed, and affected blade passage load decreased to reduce the capability of work, the tip low speed range increases.

关键词

back-to-back ; two-stage ; centrifugal compressor ; design ; Internal flow