TS-29 Optimization System for Compressor Aerodynamic Design(Session B-2: Cascade Design 2)

概要

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An aerodynamic design of a multistage axial-flow compressor is still performed in trial and error basis. In order to make the design procedure more efficient, a new design system is proposed, in which non-linear numerical optimization algorithms are combined with aerodynamic analysis programs. This paper describes two types of optimization systems. In the first type, the optimization algorithms are combined with streamline curvature through-flow programs. Examples applied to both one dimensional and quasi-three dimensional cases are shown. The second type is the optimization of two dimensional compressor airfoils and is twofold. First one utilizes a simple gradient-based optimization algorithm along with a compressible Navier-Stokes flow solver. This design system is applied to the multiple circular arc airfoils (MCA). Another one applies the implicit function theorem to residual vector of the flow solver in order to achieve efficient optimization. Applications to transonic compressor airfoil design illustrate remarkable reduction of total pressure loss.
公益社団法人日本ガスタービン学会の論文
1999-11-14