Abstract
To solve the decoupling problem in the process of turbine blade multidisciplinary design optimization, Multi-disciplinary feasible decoupling method is applied to complete the decoupling of aerodynamics, heat transfer and structure. The blade deformation under pressure and temperature load from aerodynamic and heat transfer analysis is taken as the criteria to judge whether the decoupling circle stops. Linear interpolation and free-form deformation are used to implement the load transfer and deformation transfer among the three disciplines. Through a real application, it is indicated that the convergence criteria is descended by 90.74% before decoupling circle finishes, and the three disciplines are totally decoupled. It is showed that, in the whole decoupling process, the multi-disciplinary feasible decoupling method is stable, veracious and maneuverable; however, the efficiency problem is its limitation. Some suggestions are also put forward to overcome this limitation.
| Original language | English |
|---|---|
| Pages (from-to) | 45-49 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 28 |
| Issue number | 1 |
| State | Published - Feb 2007 |
Keywords
- Blade
- Element linear interpolation
- Free-form deformation
- Multidisciplinary design optimization