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Axisymmetric gas-solid coupling heat transfer model, analysis method and application system

A heat transfer model and analysis method technology, applied in the field of solid heat transfer finite element method analysis, can solve problems such as inability to accurately analyze gas temperature changes, reducing accuracy, and error in component life estimates.

Active Publication Date: 2019-08-13
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This makes it impossible to accurately analyze the temperature change of the gas, nor can it accurately reflect the heat exchange between the solid and the gas
The assumption that the gas boundary temperature is constant reduces the accuracy of the physical system model with high gas-heat-solid coupling, which is prone to large calculation errors
According to foreign research statistics, if the calculation error of the temperature of hot-end components such as the turbine is 15K, the error of component life estimation will increase by 50%.

Method used

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  • Axisymmetric gas-solid coupling heat transfer model, analysis method and application system
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  • Axisymmetric gas-solid coupling heat transfer model, analysis method and application system

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Embodiment 1

[0056] This embodiment takes figure 1 The turbine disk of the aero-engine shown is taken as an example to illustrate the difference between the axisymmetric gas-solid coupling heat transfer model proposed by the present invention and the traditional heat transfer analysis model. figure 1 The axisymmetric section indicated by the circle, such as figure 2 shown.

[0057] Such as figure 2 As shown, in this embodiment, the fluid (including cooling gas and gas) performs convective heat exchange on the boundary of the turbine disk; wherein, the straight arrows represent the gas flow direction, and the random curved arrows represent the cooling gas flow direction.

[0058] The thermal load borne by an aeroengine during its operation has the characteristics of spatial distribution and time variation, forming a physical field problem of initial boundary value. The heat transfer mode inside the turbine disk (solid) is heat conduction, and its heat transfer control equation is as fo...

Embodiment 2

[0108] This embodiment specifically illustrates how to apply the gas-solid coupling heat transfer model described in Embodiment 1 considering the gas temperature change at the gas-solid boundary to obtain all solid node temperatures and gas node temperatures.

[0109] The calculation process for obtaining all solid node temperatures and gas node temperatures of solids is as follows: Figure 6 As shown, it specifically includes the following steps:

[0110] Step 1. Selecting and intercepting an axisymmetric plane of the solid to obtain a two-dimensional geometric model of the plane;

[0111] Step 2, generating a triangular mesh on the semi-meridian plane of the two-dimensional geometric model;

[0112] Step 3, establishing a finite element triangular classical heat transfer model inside the solid;

[0113] Step 4, setting up the heat transfer model of the gas-solid boundary triangular unit as described in any of claims 1-6;

[0114] Step 5, based on the results of the step 3...

Embodiment 3

[0121] In order to apply Embodiment 1 or Embodiment 2 to specific projects, this embodiment also designs such Figure 7 The application system shown includes geometric modeling subsystem, grid division subsystem and gas-solid coupling analysis subsystem. The geometric modeling subsystem receives a given solid computer model in the CAD system, and performs detail feature processing; the mesh division subsystem obtains the finite element triangular mesh of the solid based on the processing results of the geometric modeling subsystem , and transmitted to the gas-solid coupling analysis subsystem; the gas-solid coupling analysis subsystem establishes the internal finite element triangular classical heat transfer model of the solid and the gas-solid coupling heat transfer model of the gas-solid boundary, and calculates the Solid all solid node temperatures and gas boundary node temperature values; the CAD system can be UG system, AutoCAD system or SolidWorks system.

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Abstract

The invention discloses an axisymmetric gas-solid coupling heat transfer model, an analysis method and an application system. The model is characterized in that the temperature of gas subjected to heat exchange on a solid boundary in the heat transfer model is a variable, and the temperature of the gas rises or falls along with the heat exchange between the gas and the solid boundary, and througha linear equation set established by combining initial conditions, a gas-solid energy coupling analysis model and a finite element triangular classical heat transfer model in the solid, the temperature field and the gas temperature field of each part of the solid can be accurately solved. The invention also discloses an analysis method and an application system of the heat transfer model. According to the model, the method, and the system, the gas temperature of the gas-solid boundary is treated according to variables, the influence of solid temperature distribution on gas temperature distribution is fully considered, the defects of a classic heat transfer analysis model are overcome, the temperature rise effect of the gas at the gas-solid boundary can be accurately calculated, and the heat transfer analysis precision during gas-solid coupling is greatly improved.

Description

technical field [0001] The invention relates to the field of solid heat transfer finite element method analysis, in particular to an axisymmetric gas-solid coupled heat transfer model, analysis method and application system. Background technique [0002] Aeroengines are subject to high-intensity thermal loads during operation, and the interaction between thermal loads and structures is directly related to performance, precision, maneuverability, reliability, life, maintainability, and cost. In order to meet the design requirements of high thrust-to-weight ratio, high efficiency, and high life, the new generation of aero-engines must accurately calculate the distribution of temperature loads and predict the effects of temperature loads on solid structures (such as thermal stress and thermal fatigue, etc.). Therefore, it is one of the key technologies in the development of modern aeroengines to deeply reveal the mechanism of action between temperature loads and solid structure...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2119/08G06F30/17G06F30/23Y02T90/00
Inventor 王成恩
Owner SHANGHAI JIAO TONG UNIV
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