A multi-objective pneumatic optimization design method for a transonic axial fan/compressor

An optimized design, axial flow fan technology, applied in multi-objective optimization, calculation, special data processing applications, etc. Strengthen the practical significance of engineering, solve the effect of pressure ratio and efficiency, and shorten the design cycle

Pending Publication Date: 2019-04-26
友铂空天动力(深圳)有限公司
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Problems solved by technology

[0005] The purpose of the present invention is to propose a transonic axial flow fan / compressor aerodynamic optimization design method, to solve the problem of long calculation time, poor operability in actual engineering design, and inability to optimize the single objective function in the process of aerodynamic optimization design. Better take into account multiple aerodynamic performance indicators and other issues, thereby improving the automation of the transonic axial fan / compressor aerodynamic optimization design system, improving the efficiency of aerodynamic optimization design, further shortening the calculation cycle, and reducing design costs

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  • A multi-objective pneumatic optimization design method for a transonic axial fan/compressor
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  • A multi-objective pneumatic optimization design method for a transonic axial fan/compressor

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0027] This embodiment is based on the NASA Rotor 67 fan rotor (its main design parameters are shown in Table 1), taking its design scheme as a blueprint, and applying a multi-objective aerodynamic optimization design method for a transonic compressor proposed by the present invention to complete the multi-objective aerodynamic design optimization.

[0028] Table 1 Main design parameters of NASA Rotor 67

[0029]

[0030]

[0031] refer to figure 1 , the specific implementation steps are as follows:

[0032] Step 1: First obtain the three-dimensional geometric data of the rotor blade channel of the NASA Rotor 67 fan, use it as the initial design data and perform parameterization.

[0033] In the stage of parameterizing the three-dimensional geometry of the blade channel, the number of parameterized control points for each blade section...

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Abstract

The invention discloses a multi-objective pneumatic optimization design method for a transonic axial fan / compressor. Based on the three-dimensional viscous environment, the design method selects the fan / compressor level total pressure ratio and the heat insulation efficiency as the target functions of the optimization design under the condition that the mass flow constraint of the fan / compressor is guaranteed, and completes the multi-target pneumatic optimization design work of the fan / compressor. Firstly, initial geometric definition of a transonic axial fan / compressor is completed, and geometric parameterization of a blade channel is achieved. Secondly, constructing an objective function, setting corresponding calculation boundary conditions, and performing grid division and flow field solution on a calculation domain; And finally, an optimization script program is operated, optimization of the objective function is completed in combination with a genetic algorithm, and a fan / compressor pneumatic optimization design scheme meeting the expected design objective is obtained. The pneumatic optimization design method can be applied to pneumatic optimization design of the transonic axial fan / compressor.

Description

technical field [0001] The invention relates to the technical field of aerodynamic design of aviation gas turbines, in particular to a multi-objective aerodynamic optimization design method for a transonic axial flow fan / compressor. Background technique [0002] Aeroengine is the "heart" of an aircraft or aircraft. As an important strategic equipment of the country, its design and manufacture involve the intersection and integration of aerodynamics, materials, mechanics, electronics and other multidisciplinary fields, marking the comprehensive technical level of the development of the national aviation industry. As the core aerodynamic component of the aerodynamic system, the fan / compressor has the characteristics of high technical content, great difficulty, and high precision in the manufacturing process. Its design technical level restricts the overall development of aero-engines. Therefore, the fan / compressor design and its performance optimization have always been the fo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2111/06G06F30/17
Inventor 陈焕龙张楠刘竞航刘暾李杰灵侯珍秀杨显清关国峰邹阳
Owner 友铂空天动力(深圳)有限公司
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