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Design method for life robustness of hot component of gas turbine

A technology of gas turbine and design method, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve the problem of low life robustness of gas turbine thermal components, achieve low cycle fatigue life of precise thermal components, reduce maintenance costs, prolong The effect of service life

Pending Publication Date: 2022-08-02
HANGZHOU TURBINE POWER GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] In order to solve the problem of low life robustness of the thermal components of the gas turbine, the invention provides a design method for the robustness of the life of the thermal components of the gas turbine

Method used

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  • Design method for life robustness of hot component of gas turbine
  • Design method for life robustness of hot component of gas turbine
  • Design method for life robustness of hot component of gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] according to Figure 1-Figure 3 The design method for the life robustness of gas turbine thermal components is shown, and the low-cycle fatigue life of a ground gas turbine turbine blade is robustly designed. The specific steps include:

[0055] Step S1: Perform CFD calculation on the flow field and solid temperature field of the turbine blade to obtain the temperature field distribution of the turbine blade. At the same time, the transient finite element analysis method is used to analyze the solid domain of the turbine blade, and the air film hole edge of the blade body is determined by the calculation result. is the check point, and then the cyclic stress-strain curve of the air film hole edge of the blade body is obtained;

[0056] Specifically, this region has a high stress level due to a large temperature gradient.

[0057] Step S2: Obtain the strain amplitude of the turbine blade from the start-up to the shutdown process of the check point through the cyclic str...

Embodiment 2

[0090] according to figure 1 , Figure 4 and Figure 5 The design method for the life robustness of gas turbine thermal components is shown, and the low cycle fatigue life of a ground gas turbine flame tube is robustly designed. The specific steps include:

[0091] Step S1: use the flow-heat-solid coupling analysis method to perform CFD calculation on the flow field and solid temperature field of the flame tube to obtain the temperature field distribution of the flame tube, and at the same time use the transient finite element analysis method to analyze the solid domain of the combustion chamber flame tube , the cyclic stress-strain curve of the gas film hole edge of the flame cylinder during the start-up to shutdown process of the gas turbine is obtained through the calculation results;

[0092] Specifically, this region has a high stress level due to a large temperature gradient.

[0093] Step S2: Obtain the strain amplitude of the flame tube from the start-up to the shut...

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Abstract

The invention discloses a gas turbine hot component life robustness design method, and particularly relates to the technical field of gas turbines.The gas turbine hot component life robustness design method comprises the steps that S1, a fluid-heat-solid coupling analysis method is adopted to obtain a temperature field, and a transient finite element analysis method is adopted to obtain a cyclic stress-strain curve of a hot component check point in the process from starting to stopping of a gas turbine; s2, establishing a low-cycle fatigue life agent model of the hot component by adopting a response surface method; s3, setting a robustness design variable of the hot part, and establishing a quantile optimization model and a constraint condition of the low cycle fatigue life; and S4, solving the quantile optimization model by adopting an SPEA-II multi-objective optimization algorithm to obtain an objective function value. According to the method, in the design stage of the hot component of the gas turbine, the design variable enabling the service life of the hot component to be robust can be found in a large design space, the design service life of the hot component is prolonged, and the maintenance cost in the whole life cycle is reduced.

Description

technical field [0001] The present invention relates to the technical field of gas turbines, in particular to a method for robust design of the life of thermal components of a gas turbine. Background technique [0002] Gas turbine thermal components, especially turbine blades, combustion chambers, shrouds, etc., are the high-temperature critical components of ground-based gas turbines. Gas turbine thermal components are used in harsh environments such as high temperature, high pressure, and high speed, and their reliability is critical to the stable operation of the gas turbine. Due to the change of working conditions caused by frequent start-up, the hot components will be subjected to large centrifugal loads with low frequency changes and large thermal loads, so low cycle fatigue is an important factor limiting the service life of hot components. Therefore, at the design stage, it is important to ensure that the thermal components have adequate low cycle fatigue life. [...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F30/27G06F30/28G06F111/06G06F113/08G06F119/04G06F119/08G06F119/14
CPCG06F30/23G06F30/27G06F30/28G06F2119/08G06F2119/14G06F2113/08G06F2111/06G06F2119/04Y02T90/00
Inventor 蓝吉兵魏佳明余沛坰徐睿邵艳红屠瑶隋永枫潘慧斌初鹏郑健生
Owner HANGZHOU TURBINE POWER GRP
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