Abstract
A fast and accurate blade-to-blade viscous code which uses finite volume time marching method for solving the flow field of turbomachinery has been established. The code uses H meshes to build discrete equation. To accelerate convergence, local time stepping, residual smoothing and multigrid method are also applied. The viscous effects are approximated by a very simple mixing length model. Test cases of Hobson's second impulse cascade, a compressor rotor of NASAf Rotor 37 and Sanz's supercritical compressor cascade are presented. Results of Mach number distributions show good agreements with experimental or design data. All results illustrate that the described method can be used widely in engineering design of turbomachinery.
| Original language | English |
|---|---|
| Pages (from-to) | 51-54 |
| Number of pages | 4 |
| Journal | Qinghua Daxue Xuebao/Journal of Tsinghua University |
| Volume | 38 |
| Issue number | 10 |
| Publication status | Published - 1998 |
| Externally published | Yes |