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

Guoliang Ju; Can Chen; Rongliang Chen; Jingzhi Li; Kaitai Li; Shaohui Zhang; Guoliang Ju; Can Chen; Rongliang Chen; Jingzhi Li; Kaitai Li; Shaohui Zhang

doi:10.3934/era.2020043

Electronic Research Archive

2020, Volume 28, Issue 2: 837-851. doi: 10.3934/era.2020043

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

Guoliang Ju ^{1
,},
Can Chen ^{2
,},
Rongliang Chen ^{2
,
,},
Jingzhi Li ^{3
,
,},
Kaitai Li ^{4
,},
Shaohui Zhang ^{5
,}

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

Received: 01 December 2019 Revised: 01 March 2020
Primary: 65M30, 76D05

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.
- Rotational Navier-Stokes equations,
- semi-geodesic coordinate system,
- aeroengine turbine fan
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[J]. Electronic Research Archive, 2020, 28(2): 837-851. doi: 10.3934/era.2020043

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Abstract

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.

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