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Inverse problem design method for quasi-s1 flow surface of axial flow compressor

A technology of axial flow compressor and design method, applied in mechanical equipment, design optimization/simulation, machine/engine, etc., can solve problems such as difficult to simulate S1 flow surface aerodynamic performance, non-convergent calculation results, long calculation time, etc., to achieve Design fast and flexible, reduced calculation time, highly targeted effects

Active Publication Date: 2020-11-20
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0008] Due to the time-consuming design and calculation of the full three-dimensional viscous inverse problem, the design cycle is relatively long, the calculation results are prone to non-convergence, and it is difficult to improve the aerodynamic performance of a quasi-S1 flow surface in a targeted and intuitive way

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  • Inverse problem design method for quasi-s1 flow surface of axial flow compressor
  • Inverse problem design method for quasi-s1 flow surface of axial flow compressor
  • Inverse problem design method for quasi-s1 flow surface of axial flow compressor

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Embodiment Construction

[0046] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0047] The present invention directly imitates the S1 flow surface through the geometric structure of the blades of the compressor, and uses it as the research object of the inverse problem design to carry out intuitive, efficient and pertinent inverse problem design research.

[0048] Step 1: Select the axial flow compressor blade for inverse problem design research, calculate and determine the coordinates of the design section (the design section can be determined at any position along the blade span direction) and the upper and lower molded lines of the quasi-S1 flow surface in the meridian plane:

[0049]

[0050] r s + r h = 2r m (2)

[0051] Among them, A S1 represents the annulus area of ​​the quasi-S1 flow surface, r s and r h represent the radius coordinates of the upper and lower profile lines on the quasi-S1 flow surface, r s -r h...

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Abstract

The invention provides an inverse problem design method of a pseudo S1 flow surface of an axial-flow compressor. The method comprises the steps of selecting an axial-flow compressor blade; calculatingcoordinates of upper and lower molded lines, and constructing the pseudo S1 flow surface to obtain flow field flow conditions and flow parameter distribution; obtaining a new load distribution curvethrough a parameterization method; calculating the virtual moving speed and the corresponding virtual displacement of an arc surface in the pseudo S1 flow surface; updating grid calculation domain boundaries and internal grid node coordinates; carrying out at least five pseudo S1 flow surface inverse problem designs with multiple design sections on the compressor blade; calculating the inverse problem to obtain the blade profile geometry of each design section meeting the target load; generating a new full-blade-height compressor blade geometry through geometric stacking; and verifying the aerodynamic performance of the new compressor blade through full three-dimensional viscous positive problem calculation. According to the inverse problem design method of the pseudo S1 flow surface of the axial-flow compressor, the load distribution of the pseudo S1 flow surface is given autonomously, the inverse problem modification design is carried out on the initial blade, and finally the new blade geometric configuration meeting the target load distribution is obtained.

Description

technical field [0001] The invention relates to the aerodynamic design of a single / multi-blade row / multi-stage fan / compressor, in particular to a design method of a blade with an inverse problem of a quasi-S1 flow surface. Background technique [0002] As we all know, the performance of compressor components plays a decisive role in the overall performance of aeroengines. Axial flow compressor is one of the most challenging design components in aero-engine, and the flow of air flow inside its complex geometric boundary conditions presents obvious three-dimensional viscous characteristics and unsteadiness; in addition, at super / transonic speed In the compressor, the existence of the shock wave will lead to a strong reverse pressure gradient of the airflow, which will easily induce flow separation, and the interaction of the shock wave / boundary layer will make the flow of the airflow inside the compressor more complicated; the high-speed rotating During the operation of the c...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/38G06F30/17G06F30/28
CPCF04D29/384
Inventor 吴虎杨晨李进广张莹
Owner NORTHWESTERN POLYTECHNICAL UNIV
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