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Method for predicting aeroelasticity stability numerical value of turbomachinery with error frequency included

A technology of aeroelasticity and numerical prediction, applied in calculation, electrical digital data processing, special data processing applications, etc., can solve problems such as predicting the aeroelastic stability of turbomachinery blades, and achieve the effect of saving calculation amount

Inactive Publication Date: 2013-02-20
BEIHANG UNIV
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Problems solved by technology

One of the biggest difficulties is how to solve the equations of motion that include aerodynamic coupling terms
There is currently no mature technique for predicting the aeroelastic stability of turbomachinery blades taking into account frequency error

Method used

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  • Method for predicting aeroelasticity stability numerical value of turbomachinery with error frequency included
  • Method for predicting aeroelasticity stability numerical value of turbomachinery with error frequency included
  • Method for predicting aeroelasticity stability numerical value of turbomachinery with error frequency included

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Embodiment Construction

[0058] In the present invention, a method for numerical prediction of aeroelastic stability of impeller machinery including frequency error, the specific steps are as follows:

[0059] Step 1: Establish a finite element model of the blade;

[0060] Establish a blade finite element model in the CAE pre-processing software for a given solid model;

[0061] Step 2: Perform modal analysis with prestress on the established finite element model;

[0062] Firstly, the established finite element model is imported into the finite element software ANSYS, the corresponding material parameters are defined, and the rotational speed and displacement constraints are given, and the prestress caused by centrifugal force is obtained through static analysis;

[0063] Then, using mass-normalized modal analysis and taking into account the prestress caused by centrifugal force, the natural vibration characteristics of the blade are obtained, and the natural frequency and mode shape of the blade vi...

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Abstract

The invention provides a method for predicting an aeroelasticity stability numerical value of a turbomachinery with an error frequency included. An aeroelasticity characteristic value method is adopted, the aeroelasticity of the turbomachinery with the error frequency included is predicted by calculating the characteristic value of an aeroelastic system, and the method provided by the invention comprises seven steps in total. The method provided by the invention adopts a unidirectional coupling technology, firstly natural mode analysis is carried out on an isolated blade, and then blade modal displacement is transmitted to a fluid grid; flow field calculation is divided into constant analysis and non-constant analysis, a specified blade vibrates in the natural mode in the non-constant analysis, an influence coefficient method is applied for processing the obtained non-constant aerodynamic force, and finally the error frequency is introduced by changing generalized rigidity of the blade, a blade motion equation containing an airload is solved to obtain the characteristic value of the aeroelastic system, and whether the system flutters or not is judged by virtue of a symbol of the real part of the characteristic value. The method provided by the invention has good practical value and wide application prospect in the field of aeroelasticity of turbomachinery.

Description

technical field [0001] The invention belongs to the technical field of impeller machinery simulation, and in particular relates to a numerical prediction method for aeroelastic stability of impeller machinery including frequency error based on an eigenvalue method. Background technique [0002] With the in-depth research on the flutter of turbomachinery blades, the application of frequency shift technology to improve the aeroelastic stability of turbomachinery blades has become an effective means of suppressing flutter, and has been widely used in aeroengines with good results. [0003] In the early design research, the blisk rotor was usually regarded as coordinated, that is, the blades on the same stage of the rotor were exactly the same, and of course they had the same vibration characteristics. However, in actual work, due to manufacturing tolerances and service During different degrees of wear and tear, all blisk structures have a certain degree of frequency error. [...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 付志忠王延荣
Owner BEIHANG UNIV
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