Transonic two-stage centrifugal compressor

摘要

PPROBLEM TO BE SOLVED: To prevent stalling and surging of an impeller and a diffuser blade over an entire operating region from a subsonic region to a supersonic region. PSOLUTION: In an operating method of this transonic two-stage centrifugal compressor 10 having a first bleed port 21 disposed at a position near a front end of a front stage intermediate blade 12, and a second bleeding port 22 disposed at a wake flow side of a front stage return blade 14 and at the upstream side of a rear stage impeller 15, in the subsonic region, 0-20% of the entire air flow rate from the first bleeding port 21 is extracted, in a transonic region, 0-8% of the entire air flow rate from the second bleed port 22 is extracted, and in the supersonic region, extraction is not performed at all. PCOPYRIGHT: (C)2010,JPO&INPIT