An optimization process is used to design bladings in turbomachinery. A gradient-based method is coupled to Navier-Stokes solvers and is applied to three different bladings. A new rotor blade of a transonic compressor is designed by using a quasi three-dimensional approach, with a significant efficiency improvement at the design point. The off-design behavior of this new compressor is also checked afterwards. The same quasi three-dimensional approach is used on a stator blade of a turbine, but the whole stage is computed in this case. The losses are locally reduced, proving the good sensitivity of the solver. Finally, a new three-dimensional rotor blade of a compressor is designed by applying deformation functions on the initial shape. The efficiency is improved over a wide range of mass flow. The whole results indicate that the optimization process can find improved design and can be integrated in a design procedure.

Issue Section:
Technical Papers
Keywords:
optimisation, aerospace engines, transonic flow, gradient methods, Navier-Stokes equations, rotors, stators, turbines, computational fluid dynamics, compressors
Topics:
Optimization, Design, Blades, Flow (Dynamics), Deformation
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 by ASME
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