# American Institute of Mathematical Sciences

June  2020, 28(2): 837-851. doi: 10.3934/era.2020043

## Numerical simulation for 3D flow in flow channel of aeroengine turbine fan based on dimension splitting method

 1 School of Mechatronics Engineering, Harbin Institute of Technology, Harbin 150001, China 2 Shenzhen Institutes of Advanced Technology Chinese Academy of Sciences, Shenzhen 518055, China 3 Department of Mathematics, Southern University of Science and Technology, Shenzhen 518055, China 4 School of Science, Xi'an Jiaotong University, Xi'an 710049, China 5 School of Mathematical Sciences, South China Normal University, Guangzhou 510631, China

* Corresponding authors

Received  December 2019 Revised  March 2020 Published  May 2020

In this paper, we introduce a dimension splitting method for simulating the air flow state of the aeroengine turbine fan. Based on the geometric model of the fan blade, the dimension splitting method establishes a semi-geodesic coordinate system. Under such coordinate system, the Navier-Stokes equations are reformulated into the combination of membrane operator equations on two-dimensional manifolds and bending operator equations along the hub circle. Using Euler central difference scheme to approximate the third variable, the new form of Navier-Stokes equations is splitting into a set of two-dimensional sub-problems. Solving these sub-problems by alternate iteration, it follows an approximate solution to Navier-Stokes equations. Furthermore, we conduct a numerical experiment to show that the dimension splitting method has a good performance by comparing with the traditional methods. Finally, we give the simulation results of the pressure and flow state of the fan blade.

Citation: Guoliang Ju, Can Chen, Rongliang Chen, Jingzhi Li, Kaitai Li, Shaohui Zhang. Numerical simulation for 3D flow in flow channel of aeroengine turbine fan based on dimension splitting method. Electronic Research Archive, 2020, 28 (2) : 837-851. doi: 10.3934/era.2020043
##### References:

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##### References:
Aeroengine turbine fan
The channel of impellers when $\Theta = 0$
One of blade in R-coordinate system
The mesh of central surface generated by different methods
The comparisons of velocity magnitude calculated by different methods
The comparisons of velocity $u_1$ calculated by different methods
The comparisons of velocity $u_2$ calculated by different methods
The comparisons of velocity $u_3$ calculated by different methods
The comparisons of Pressure calculated by different methods
The pressure distribution of positive pressure surface
The pressure distribution of negative pressure surface
The 3D model of pressure distribution of positive pressure surface
The 3D model of pressure distribution of negative pressure surface
The blade mesh in R-coordinate system
Velocity distribution at outlet
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