Automatic optimization method of turbomachinery blade

A turbomachinery and automatic optimization technology, applied in design optimization/simulation, random CAD, calculation model, etc., can solve high-dimensional, black-box, time-consuming problems, etc., achieve less design parameters, improve comprehensive performance, and good robustness Effect

Pending Publication Date: 2021-10-29
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology

[0006] In order to break through the limits of existing turbomachinery blade design and maximize the performance of turbomachinery blades, this invention proposes a novel automatic optimization method for turbomachinery blades to solve the high-dimensional, time-consuming, and black-box problems in the optimal design of turbomachinery blades. Three major problems

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  • Automatic optimization method of turbomachinery blade
  • Automatic optimization method of turbomachinery blade
  • Automatic optimization method of turbomachinery blade

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[0066] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present invention, and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0067] The purpose of the present invention is to provide an automatic optimization method for turbomachinery blades, aiming at breakin...

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Abstract

The invention provides an automatic optimization method for a turbomachinery blade, and the method comprises the following steps: performing parametric modeling on an initial blade profile by adopting an improved category shape transformation method, and flexibly constructing a suction surface molded line and a pressure surface molded line of the blade profile on the basis of applying fewer variables, so the method has the advantages of good robustness, few design parameters, high modeling precision and the like; employing a sample sampling method, an agent model and a cubic chaotic mapping whale optimization algorithm for automatically optimizing the blades, so the method has the advantages of high sampling efficiency, high agent precision, high optimization capacity and the like. By applying the automatic optimization method, the comprehensive performance of the impeller mechanical blade is improved.

Description

technical field [0001] The invention belongs to the technical field of turbomachinery optimization design, and relates to a method for optimizing a turbomachinery blade, in particular to an automatic optimization method for a turbomachinery blade, and is especially suitable for turbomachinery such as compressors, steam turbines, turbines, flue gas turbines, and expanders. Automatic optimization of blades. In the implementation of this method, firstly, the initial airfoil shape is parametrically modeled by using the improved category shape transformation method, and the suction surface and pressure surface shape lines of the airfoil are flexibly constructed on the basis of using less variables. Sampling method, surrogate model and cubic chaos map whale optimization algorithm are used to automatically optimize the blades. By using the above automatic optimization methods, the comprehensive performance of the blades is improved. Background technique [0002] Designing turbomac...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/27G06N3/00G06F111/08G06F119/14
CPCG06F30/17G06F30/27G06N3/006G06F2111/08G06F2119/14
Inventor 黄松阳诚武韩戈赵胜丰卢新根张燕峰周创鑫
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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