Design method of impeller blade drag reduction micro-texture

A technology of impeller blades and design methods, applied in the field of blade drag reduction, can solve the problems of waste of resources and time, lack of pertinence and flexibility, lack of universality, etc.

Active Publication Date: 2018-02-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, these design methods lack universality in different flow field states, which

Method used

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  • Design method of impeller blade drag reduction micro-texture
  • Design method of impeller blade drag reduction micro-texture
  • Design method of impeller blade drag reduction micro-texture

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0040] Table 1 Point coordinate data of blade example

[0041]

[0042]

[0043]

[0044]

[0045]

[0046]

[0047]

[0048] Table 2 Numerical simulation model parameters

[0049] name

parameter

Inlet speed (m / s)

75

fluid

ideal gas

temperature (k)

300

Turbulence model

k-ε(2eqn); Realizable

wall function

Enhanced Wall Treatment

[0050] Table 3 Experimental results of micro-texture height h and drag reduction effect

[0051] Microtexture height h and H max ratio / %

Drag reduction percentage / %

3.6

3.1

4

5

4.4

6.1

4.8

6

5.2

5.5

5.6

4

6

3.1

6.4

1.1

6.8

0.5

7.2

-1.3

[0052] Table 4 Experimental results of micro-texture center distance l and drag reduction effect

[0053]

[0054]

[0055] Table 5 The experimental results of the angle θ between the upstream edge and the incom...

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Abstract

The invention discloses a design method of a blade surface drag reduction micro-texture, and belongs to the field of blade drag reduction. According to an impeller blade model, a flow field domain isestablished; numerical simulation is carried out on the flow field domain, a streamline graph of the middle section of a blade in the height direction is obtained, and accordingly a blade pressure surface, a boundary layer separation area and a suction surface backflow area serve as a micro-texture placement area; the micro-texture placement area is closely attached to a blade wing-shaped arrangement micro-texture section, and the micro-texture placement area sweeps on the surface of the blade in the height direction of the blade to form ribs or grooves; finite element simulation is conductedon the blade model with the rib or groove micro-texture to optimize the placement position and the section shape of the micro-texture, the placement position and the section shape of the micro-texturewith the best drag reduction are obtained, and accordingly the blade surface drag reduction micro-texture is constructed. The drag reduction of the optimized blade surface drag reduction micro-texture reaches 5-10%, the energy consumption is reduced, fuel resources are saved, and the design method of the drag reduction micro-texture can be applied and popularized in other fields.

Description

technical field [0001] The invention relates to a design method for a drag-reducing micro-texture of an impeller blade. The blades involved are mainly wind blades with an incoming flow velocity between 50m / s and 100m / s, and belong to the field of blade drag reduction. Background technique [0002] Turbomachinery has a wide range of applications in the fields of aviation, aerospace, energy, transportation, chemical industry and petroleum. Blades are key parts of turbomachinery such as aero-engines, gas turbines, and fans, and their aerodynamic drag reduction performance directly affects the performance of such products. In order to improve the aerodynamic drag reduction performance of the blade, experts and scholars at home and abroad have done a lot of research work on the optimal design of the blade. Aerodynamic drag reduction performance of flat machinery. Among various drag reduction technologies, the bionic microstructure surface prepared by micro-nano manufacturing te...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17Y02T90/00
Inventor 张臣魏盼
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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