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Method for estimating reverse twisting process of fan blade of gas turbine

A technology of fan blades and gas turbines, which is applied in special data processing applications, instruments, electrical digital data processing, etc., and can solve problems such as imperfect anti-twist design methods of gas turbine fan blades

Inactive Publication Date: 2012-11-28
BEIHANG UNIV
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Problems solved by technology

[0005] The purpose of the invention is to solve the problem that the current gas turbine fan blade anti-twist design method is not perfect, and then provide a method for predicting the anti-twist process of the gas turbine fan blade

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  • Method for estimating reverse twisting process of fan blade of gas turbine
  • Method for estimating reverse twisting process of fan blade of gas turbine
  • Method for estimating reverse twisting process of fan blade of gas turbine

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Embodiment Construction

[0040] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0041] Such as Figure 1~3 As shown, a method for estimating the anti-twist process of a gas turbine fan blade in this embodiment is realized by the following steps:

[0042] Step 1: Take the geometrical data of the blade as the original thermal blade profile and the blade material as the material selected during the design to obtain the elastic constant and Poisson's ratio performance parameters. Such as titanium alloy: the elastic constant is EX=1.12E11Pa, Poisson's ratio is 0.3, and the density is 4440kg / m3. Take the aerodynamic condition of the design point as the working point;

[0043] Step 2: According to the geometric value of the thermal blade under the original design condition, use the three-dimensional solid configuration software UG to construct the geometric model of the fan blade;

[0044] Step 3: Import the geometric model of...

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Abstract

The invention provides a method for estimating a reverse twisting process of a fan blade of a gas turbine, and aims to solve the problem that the conventional gas turbine fan blade reverse twisting design method is incomplete. According to the method, a cold state blade profile can be finally obtained by steps of performing analysis software (ANSYS) centrifugal force static deformation analysis on a thermal state blade profile, forecasting the cold state blade profile, then performing ANSYS centrifugal force static deformation analysis on the forecast cold state blade profile, transitioning a virtual thermal state blade profile, correcting a solid and liquid grid, performing aerodynamic force deformation fluid-solid coupling analysis and the like. The method has great significance for implementing consistency between the forecast thermal state blade profile and an actual working state blade profile of the blade under each pneumatic working condition and researching a method for precisely estimating the reverse twisting process of the fan blade of the gas turbine; and particularly, the method has important engineering application value in developing transonic speed fans with large bypass ratios.

Description

technical field [0001] The invention relates to the technical field of blade profile design, in particular to a method for estimating the anti-twist process of a fan blade of a gas turbine. Background technique [0002] The performance of gas turbine, especially the fan stage of turbofan engine has a crucial influence on the overall performance of the engine, and the blade shape is one of the most important parameters to determine the performance of the fan, so ensure that the shape and design point of the fan blade at the working point The same or close to the key link to achieve its design performance indicators. During the working process of the gas turbine fan, under the joint action of aerodynamic force, centrifugal force and thermal stress, the blade will produce complex deformations such as elongation and expansion, and the blade will change from the processed shape (cold blade shape) to the working speed. The airfoil (hot airfoil), and the hot airfoil is restricted ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 郑赟杨慧王彪方韧
Owner BEIHANG UNIV
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