Abstract
Based on analytic and feature modeling methods, a parametric design method for three-dimensional internally cooling turbine blade model with ribs and bleed was developed. Blade profiles were defined by five-order polynomial expression. The cooling passage profiles were defined by the thickness of wall according to the blade profiles. A FORTRAN program was written with the intent to provide rapid and robust geometry generation of realistic turbine blades. The ribs, rabbet and margin pale were designed by means of CAD with feature modeling method. As an example, a tri-cavities internal cooling turbine blade was successfully established using this method.
Original language | English |
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Pages (from-to) | 637-640+656 |
Journal | Tuijin Jishu/Journal of Propulsion Technology |
Volume | 28 |
Issue number | 6 |
State | Published - Dec 2007 |
Keywords
- Aircraft engine
- Feature modeling
- Parametric design
- Turbine blade