Design method of blade suction surface groove for controlling flow separation

A suction surface and blade technology, applied to blade support components, mechanical equipment, engine components, etc., to reduce weight, reduce fuel consumption, and improve the characteristics of large angle of attack

Inactive Publication Date: 2014-04-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As the angle of attack of the airfoil becomes larger, when the entire suction surface is almost entirely turbulent flow, this treatment technology has no effect of inhibiting the separation of the boundary layer

Method used

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  • Design method of blade suction surface groove for controlling flow separation
  • Design method of blade suction surface groove for controlling flow separation
  • Design method of blade suction surface groove for controlling flow separation

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] In this embodiment, a certain cascade primitive blade type (as shown in the appendix) Figure 5 shown) is a design object. The design inlet Mach number of this primitive airfoil is 0.7, and the critical angle of attack is 8°. To design the groove 4 on the blade suction surface 1 of the original primitive airfoil, it is first necessary to determine the initial position of the groove starting point, the initial projection length of the groove on the blade suction surface profile, and the initial description of the groove curve. functional equation.

[0027] To determine the initial position of the groove starting point, it is necessary to calculate and analyze the flow field of the original element blade cascade channel. The initial position of the groove starting point is selected within the projection range of the separation zone development stage on the blade suction surface, and the projection range of the separation zone development stage on the blade suction surfa...

Embodiment 2

[0038] In this embodiment, a certain cascade primitive blade shape is taken as the design object. The design inlet Mach number of the primitive airfoil is 0.5, and the critical angle of attack is 8°. To design the groove on the blade suction surface of the original primitive airfoil shape, it is first necessary to determine the initial position of the groove starting point, the initial projection length of the groove on the blade suction surface shape line, and the initial function equation describing the groove curve .

[0039] To determine the initial position of the starting point of the groove, it is necessary to calculate and analyze the flow field of the original primitive blade type cascade channel. The initial position of the starting point of the groove is selected within the projection range of the development stage of the separation zone on the suction surface of the blade, and the projection range of the development stage of the separation zone on the suction surf...

Embodiment 3

[0050] In this embodiment, a certain cascade primitive blade shape is taken as the design object. The design inlet Mach number of the basic airfoil is 0.6, and the critical angle of attack is 7°. To design the groove on the blade suction surface of the original primitive airfoil shape, it is first necessary to determine the initial position of the groove starting point, the initial projection length of the groove on the blade suction surface shape line, and the initial function equation describing the groove curve .

[0051] To determine the initial position of the starting point of the groove, it is necessary to calculate and analyze the flow field of the original primitive blade type cascade channel. The initial position of the starting point of the groove is selected within the projection range of the development stage of the separation zone on the suction surface of the blade, and the projection range of the development stage of the separation zone on the suction surface ...

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Abstract

The invention provides a design method of a blade suction surface groove for controlling flow separation, which comprises the steps of: firstly, determining the initial position of the initial point of a groove, the initial projection length of the groove on the molded line of a blade suction surface and the initial function equation for describing the curved line of the groove; and secondly, optimizing the groove by adopting genetic algorithm, wherein the initial position of the groove, the projection length of the groove on the molded line of the blade suction surface and the initial function equation for describing the curved line of the groove are taken as optimization variables, and the static pressure rise, the total pressure recovery coefficient, the total pressure coefficient and the airflow turning angle of a blade grid passage are taken as variables of the fitness function in the genetic algorithm, so that the optimization variable combination which can be maximize the fitness function is taken as the modeling parameters of the groove. According to the design method, the flow in the blade grid passage can be improved, a burbling zone in the passage can be decreased or even eliminated, the efficiency and the total pressure recovery coefficient of the passage are improved, the loss coefficient of the passage is reduced, the high attack angle of the elementary blade type is improved, and the available attack angle range of the elementary blade type is enlarged.

Description

technical field [0001] The invention relates to the field of impeller machinery, in particular to a design method for a blade suction surface groove for controlling airflow separation. Background technique [0002] In today's society, turbomachinery is increasingly playing an important role in the field of national defense science and technology. It is an important component in the fields of aviation, aerospace, navigation, energy, and chemical industry. The blade is an important part of the turbomachinery, and the turbomachinery mainly realizes the work on the external medium through the blade. Therefore, the working ability of the blades determines the efficiency of the turbomachinery. Improving the working ability of blades is in line with the theme of energy conservation and emission reduction in today's society, and is of great significance for alleviating the energy crisis and implementing sustainable development strategies. [0003] With the continuous improvement o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14G06N3/12
Inventor 刘波史磊张国臣曹志远王雷
Owner NORTHWESTERN POLYTECHNICAL UNIV
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