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Multi-point pneumatic optimization design method for an axial fan

An axial-flow fan, optimized design technology, applied in computing, special data processing applications, instruments, etc., can solve the problem that it is difficult to comprehensively consider the performance of the fan/compressor aerodynamic design scheme under variable working conditions, and it cannot effectively expand the stable working range of the aerodynamic design scheme. , It is impossible to effectively take into account the changes in the aerodynamic performance of the non-optimized point, so as to achieve the effect of improving the aerodynamic performance of the fan rotor, improving the aerodynamic performance of the fan rotor, and expanding the stable working range.

Pending Publication Date: 2019-05-24
友铂空天动力(深圳)有限公司
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AI Technical Summary

Problems solved by technology

[0003] In the fan / compressor aerodynamic optimization design, the single-point optimization design method can usually only consider the change of the aerodynamic performance of the fan / compressor under the optimal point working condition, and cannot effectively take into account the change of the aerodynamic performance of the non-optimized point, that is, it is difficult to comprehensively consider the fan / compressor The variable working condition performance of the aerodynamic design scheme of the compressor cannot effectively expand the stable working range of the aerodynamic design scheme
Therefore, the single-point optimization design method has certain limitations in practical engineering applications

Method used

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  • Multi-point pneumatic optimization design method for an axial fan
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  • Multi-point pneumatic optimization design method for an axial fan

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Embodiment 1

[0048] This embodiment provides a multi-point aerodynamic optimization design method for an axial flow fan, such as Figure 10 shown, including:

[0049] Step S1: Obtain the three-dimensional geometric data of the blade channel in the prototype scheme, and perform parameterization processing.

[0050] Here, the parameterization process includes: selecting m control sections along the spanwise direction, and setting n control points on each of the control sections. Preferably, the control point of the control section is the airfoil mid-arc control point of the control section, and the airfoil mid-arc control point includes the curvature control point and the maximum deflection control point of the airfoil mid-arc. That is to say, here, multiple control points are set, and all the control points form a control point combination, where the control point combination corresponds to the rotor blade in the prototype scheme.

[0051] Step S2: Based on the rotor blades of the blade c...

Embodiment 2

[0073] In this embodiment, the NASA Rotor 67 transonic axial fan rotor is used as a prototype solution, and parameterization is performed based on its geometric data. The main design parameters are shown in Table 1.

[0074] Table 1 Main design parameters of NASA Rotor 67

[0075]

[0076] The multi-point aerodynamic optimization design method completes the aerodynamic optimization design work of multiple optimization points at the same time, which can take into account the changes in the aerodynamic performance of the fan / compressor under design conditions and non-design conditions, and obtain good characteristics of variable conditions and high stability. Fan / compressor aerodynamic optimization design scheme with margin. Therefore, the research and development of the fan / compressor aerodynamic optimization design method with multi-working condition optimization design ability, which can automatically and efficiently complete the multi-working condition aerodynamic optimiz...

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Abstract

The invention provides a multi-point pneumatic optimization design method for an axial flow fan, and relates to the technical field of axial flow fans. According to the invention, all sample elementsin the sample space are obtained through mapping from the parameter space to the sample space; The method aims at the same sample element in a sample space. according to the peak efficiency point boundary condition and the near stall point boundary condition of the prototype fan, the flow field of the sample element is solved to obtain the heat insulation efficiency of the peak efficiency point and the near stall point; After the adiabatic efficiency of all sample element optimization points is obtained, an adiabatic efficiency combination model is constructed so as to facilitate subsequent optimization work to obtain an optimal axial flow fan design scheme. According to the optimized scheme, the aerodynamic performance of two optimization points, namely the peak efficiency point and the near stall point, is obviously improved; Compared with a prototype scheme, the non-optimized point aerodynamic performance is also obviously improved, the stall flow is obviously reduced, and the blocking flow is obviously increased, namely, under the all-working-condition condition, the aerodynamic performance of the fan rotor is improved, and the stable working range is effectively expanded.

Description

technical field [0001] The invention relates to the technical field of axial flow fans, in particular to a multi-point aerodynamic optimization design method for axial flow fans. Background technique [0002] Aeroengines are known as the "Pearl in the Crown" of modern industry, which marks the comprehensive technical level of a country's aviation industry development. The fan / compressor is one of the core aerodynamic components of an aero-engine, and its aerodynamic performance often determines the overall performance of the aero-engine. The application requirements of modern aero-engines with high thrust-to-weight ratio, high efficiency, and low fuel consumption make the fans / compressors continue to develop towards high-level aerodynamic load levels, high flow, and compact structures, and they need to be maintained under all working conditions. Good efficiency level and wide stable working range to meet the application requirements of stable operation of aero-engines under...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 陈焕龙杨显清张楠刘竞航韩伟邓宗全刘暾侯珍秀邹阳李杰灵李婷婷石丹
Owner 友铂空天动力(深圳)有限公司
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