Meteosat Second Generation : MSG1 Performances and MSG Future.
- Paper number
IAC-04-B.1.09
- Author
Mr. Alain Lamothe, Thales Alenia Space, France
- Year
2004
- Abstract
The increasing popularity of high fidelity computational fluid dynamics simulations in aerodynamic design has stimulated the research into more efficient design optimization methods. The focus of this paper is on the high fidelity aerodynamic design of the multi-stage LOX turbine blade shapes for cryogenic rocket engines. Performances of design candidates were evaluated by the turbine efficiency based on the 3D airfoil geometry design and the full channel flow analysis using commercially available CAD and CFD packages. A new swarm intelligence algorithm, which combines the Differential Evolution (DE) and Particle Swarm Optimization (PSO), was developed to serve as the optimization solver. In order to reduce the computational cost, the Radial Basis Function (RBF) interpolation was employed to approximate the objective function in the adaptive surrogate based design optimization process. The reasonable solution is finally achieved that includes the turbine efficiency of the optimal design is 5% greater than that of the origin one, while satisfies the structural requirement confirmed with the 3D finite element stress analysis. In addition, sensitivity to various design variables was also explored using the Uniform Design (UD) method in the vicinity of the optimal design, thus examining the effects of the parameter bounds as well as investigating the key factors, which would provide insight for the future design of similar turbine blades.
- Abstract document
- Manuscript document
IAC-04-B.1.09.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.