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A Novel Three-Dimensional Inverse Method for Axial Compressor Blade Surface Design

  • Research Article - Mechanical Engineering
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Abstract

A novel three-dimensional inverse method based on the time-accurate solution of Navier–Stokes equations for axial compressor design is proposed in this work. The main novelty lies in the derivation of an inverse design boundary condition established on the conservation of Riemann invariant in order to directly design the blade surface. Specifically, a dynamic mesh technique is employed to update the grids and reduce the computational costs. In addition, some restrictions are imposed on the blade surface movement in order to avoid unrealistic airfoil profiles and guarantee computational robustness. Two redesign procedures are presented, including shock wave strength restrain for the NASA Rotor 37 stage and integrated controlled diffusion airfoil concept design for the Stage 35. Results indicate that this novel inverse method is effective for detailed axial compressor design.

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Abbreviations

2D:

Two-dimensional

3D:

Three-dimensional

CDA:

Controlled diffusion airfoil

CFD:

Computational fluid dynamics

CFL:

Courant–Friedrichs–Lewy

LU-SGS:

Lower–upper symmetric Gauss–Seidel

MCA:

Multiple circular arc airfoil

NURBS:

Non-uniform rational B-spline

RANS:

Reynolds-averaged Navier–Stokes equations

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Acknowledgements

This work was supported by the National Natural Science Foundation of China (Grant Number 51076131).

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Authors and Affiliations

  1. School of Power and Energy, Northwestern Polytechnical University, Xi’an, China

    Chen Yang, Hu Wu & Yan Liang

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  1. Chen Yang
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  2. Hu Wu
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  3. Yan Liang
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Correspondence to Hu Wu.

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Yang, C., Wu, H. & Liang, Y. A Novel Three-Dimensional Inverse Method for Axial Compressor Blade Surface Design. Arab J Sci Eng 44, 10169–10179 (2019). https://doi.org/10.1007/s13369-019-04083-3

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