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A Characteristic Correction Method of Multistage Axial Compressor Based on One-dimensional Mean Streamline Method

A correction method and a streamline method technology, applied in the field of simulation, can solve problems such as complex flow conditions, and achieve the effects of fast calculation speed, improved accuracy, and high precision

Active Publication Date: 2022-05-17
HARBIN ENG UNIV
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Problems solved by technology

In addition, the flow in the turbomachinery has strong three-dimensional, swirling and unsteady characteristics, and the flow situation in the multi-stage axial flow compressor is particularly complicated, so the empirical model is difficult to be generally applicable to various flow situations

Method used

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  • A Characteristic Correction Method of Multistage Axial Compressor Based on One-dimensional Mean Streamline Method
  • A Characteristic Correction Method of Multistage Axial Compressor Based on One-dimensional Mean Streamline Method
  • A Characteristic Correction Method of Multistage Axial Compressor Based on One-dimensional Mean Streamline Method

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Embodiment Construction

[0030] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0031] combine figure 1 , taking the intersection of the average streamline and the front and rear edges of each row of blades as the calculation point of the flow field parameters, the flow parameters at the positions of each calculation station represent the overall aerodynamic layout of the compressor, and the empirical models such as lagging angle and loss reflect the viscous Influenced by factors such as turbulence, turbulence, trans-sound, unsteady and other factors, the outlet parameters of blades at all levels (rows) are calculated along the axial direction, so as to advance the calculation, and finally the overall performance and aerodynamic layout parameters of the whole machine are obtained through superposition. An aerodynamic analysis method for multi-stage axial flow compressors based on the one-dimensional mean streamline method is established. One...

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Abstract

The purpose of the present invention is to provide a method for correcting the characteristics of a multi-stage axial flow compressor based on the one-dimensional average streamline method. The performance analysis method of the stage axial flow compressor, develops an automatic calibration method for the performance model of the cascade, searches for the blade wake momentum thickness coefficient that matches the pressure ratio and efficiency of the compressor with the experimental data of a specific working point, and establishes the known condition of the compressor The scalar database of the complete blade wake momentum thickness coefficient in the range; from the scalar database of the known blade wake momentum thickness coefficient, calculate the wake momentum thickness coefficient of the working point to realize the automatic calibration of the compressor characteristics. The invention has fast calculation speed and versatility, and can predict, encrypt and extrapolate the characteristics of the compressor, and is used for characteristic prediction when the inlet guide vane and stationary vane are adjustable, or to calculate the overall performance without experimental data or CFD data at a rotating speed .

Description

technical field [0001] The invention relates to a simulation method, in particular to a gas turbine simulation method. Background technique [0002] In the performance solution of the one-dimensional average streamline method, the influence of fluid viscosity is introduced for performance analysis, so empirical models such as lagging angle and loss have a significant impact on the accuracy of one-dimensional calculation. The cascade empirical models in the current open literature are mainly for standard blade shapes. However, with the development of turbomachinery, modern airfoils and advanced technologies such as bending and sweeping obtained through parametric optimization or inverse design are widely used in modern high-performance compressors. The applicability needs to be further tested. Therefore, how to use the model automatic calibration method to calibrate the empirical model becomes the key to performance analysis. [0003] Empirical models are usually averages ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17G06F30/28G06F113/08G06F119/14
CPCG06F30/17G06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 王志涛张君鑫李健高楚铭明亮于海超刘硕硕李淑英李铁磊张宗熙
Owner HARBIN ENG UNIV
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