Abstract
Due to the discontinuity between rotational impeller and stationary diffuser, there must be a bleed air cavity in the centrifugal compressor stage, which can affect the performance of the stage. It is more remarkable in semi-open impeller with bleed air cavity used for small size aero engine and gas turbine. Research progress including the researches of flow status in simplified and real cavity, the method for controlling complex flow status, the influence on the aerodynamic performance of stage, the multi-dimensional simulation method coupling impeller, diffuser and rear cavity are reviewed. The important effects induced by cavity bleed air on windage loss, axial thrust balance, the seal for oil and air, and cooling gas delivery are present. Also, the possibly advanced design methods are analyzed and proposed.
| Translated title of the contribution | Review of Complex Flow Status and Control Methods for Rear Disk Cavity in Centrifugal Impeller |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 34-43 |
| Number of pages | 10 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 43 |
| Issue number | 1 |
| DOIs | |
| Publication status | Published - Jan 2022 |