This paper presents an in-house CFD package and its derivations for turbomachinery flow simulation as well as aerodynamic design optimization which have been employed in several primary Chinese aero-engine institutions. The package contains TurboMesh, a highly automated mesh generation code for turbomachinery, and MAP, a CFD solver for general purpose. Besides the programming strategies, the numerical schemes, and the parallelization methods adopted in the codes are outlined. Emphasis is placed on a novel mixing plane model used in MAP. The proposed model satisfies flux conservation property and very robust in actual usage. Additionally, further improved performance of the model can be achieved by applying a technique similar to the perfect matching layer for non-reflecting boundary conditions. On the basis of MAP, a set of derivations have also been developed. They include several versions of MAP which are based on specific flow models, respectively, an inverse code for the design optimization of 3D blade shape, an improved-delayed-detached-eddy-simulation based code, and a scale-adaptive-simulation based code. Some of these versions of MAP are briefly introduced and demonstrated through a few examples except for the inverse code in which a direct method proposed by the author is explained with a few more words. Illustrations show the applicability of the inverse code for the design of compressor blades in practical multi-blade row environment. By embedding MAP with an in-house numerical optimization package, the numerical optimization of the 2D/3D blade shape can be realized. Some examples for 3D aerodynamic optimizations of compressors are presented.

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