Abstract
The quasi-three dimensional flow fields of axial-centrifugal compressor were solved with the streamline curvature method. Calculating stations were set in the leading edge, trailing edge and the middle of blade row. The streamline locations were fitted by cubic spline curves at each iteration computation. Performance calculation codes with loss and deviation angle models were developed by using the methods mentioned above. Available loss and deviation angle models were selected by considering the special configuration of axial-centrifugal compressor. At different rotational speed, optimum angles of IGV and stator one were determined by stator vane angle adjustment method and performance analysis codes of axial-centrifugal compressor. At 90% design speed, peak efficiency, three-dimensional numerical simulations were performed for detail flow field analysis of axial-centrifugal compressor. Research results indicate that stator vane angle adjustment can weaken the intensity of shock wave, decrease the loss, prevent the air flow deviation of the blade surface, and improve the performance of axial-centrifugal compressor.
| Original language | English |
|---|---|
| Pages (from-to) | 878-881+893 |
| Journal | Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics |
| Volume | 33 |
| Issue number | 8 |
| State | Published - Aug 2007 |
Keywords
- Axial-centrifugal compressor
- Deviation angle model
- Loss model
- Performance curve
- Stator setting angles adjustment