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Method for evaluating residual life of high-temperature alloy blade

A technology for superalloy and life assessment, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of life prediction accuracy deviation, calculation result deviation, weak internal correlation, etc., and achieve the effect of improving reliability.

Pending Publication Date: 2021-11-23
CHINA UNITED GAS TURBINE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the mechanical model life prediction method has certain limitations and shortcomings: first, the mechanical model life prediction method requires that the microstructure of the blade must remain relatively stable during the creep process; second, during the life prediction process of the mechanical model, tissue damage and The inherent correlation of performance degradation is weak, so there is a large deviation in the life prediction accuracy of long-term performance
However, this patent only uses the quantitative characterization of the microstructure to make some corrections to the theoretical formula, and the calculation results may still deviate from

Method used

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  • Method for evaluating residual life of high-temperature alloy blade
  • Method for evaluating residual life of high-temperature alloy blade
  • Method for evaluating residual life of high-temperature alloy blade

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Experimental program
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Effect test

Embodiment 1

[0075] (1) damage analysis steps:

[0076] F Class turbine stage of a gas turbine moving blade 1, when the total length of 28,000 hours in service, the location service blade tip attachment such as tissue damage figure 2 FIG: matrix alloy blade tip position of gamma] 'of spherical coarse tissue, did not show significant raft phenomenon, wherein gamma] between the dendrite dendrite' significantly different relative size, dendrite gamma] 'phase average size (equivalent diameter) of about 0.83μm, the interdendritic γ 'phase average size (equivalent diameter) of about 1.15μm. Matrix alloy blade tip position of MC carbides no obvious degradation decomposition phenomena, dispersed grain boundaries have M 23 C 6 Coarse carbide particles.

[0077] (2) Modeling steps:

[0078] The establishment of microstructure degradation in service during the dynamic model, as follows:

[0079] Gas Turbine blade alloys carry in service near equivalent material damage simulation test, comprising a static...

Embodiment 2

[0098] The remaining life evaluation method of a gas turbine high temperature alloy blade is analyzed in accordance with the life evaluation method disclosed in the present invention, and the microstructure of the high-temperature alloy blade of the actual service is analyzed, and the distribution of microstructured degradation damage is established, and the development process is established. Microstructure degradation kinetics, identified test conditions, obtained an equivalent damage simulation test alloy of 900 ° C / 10000H, established a different stress level under 900 ° C, different remaining lasting Larson-Miller curves (if attached Figure 4 As shown, accordingly, the corresponding relationship between the remaining life of acceleration and long-lasting test is to extrapolate the remaining service life of the actual combustion engine blade.

Embodiment 3

[0100] The remaining life evaluation method of a gas turbine high temperature alloy blade is analyzed in accordance with the life evaluation method disclosed in the present invention, and the microstructure of the high-temperature alloy blade of the actual service is analyzed, and the distribution of microstructured degradation damage is established, and the development process is established. Microstructure degradation kinetics, identified test conditions, obtained near-service equivalent damage simulation test alloys, to conduct a long-term persistent creep performance test test under near service conditions at 900 ° C / 90MPa, the remaining persistence of the alloy is 12631 Hours, therefore, the remaining life of the orientation combustion engine blade under 900 ° C / 90 mPa was inferred in the long-time delivery of 25,000 hours.

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Abstract

The invention provides a method for evaluating the residual life of a high-temperature alloy blade. The evaluation method comprises the following steps: a damage analysis step, a model establishment step, an equivalent test alloy acquisition step and a residual life evaluation step. According to the method, the residual life of the long-time service high-temperature alloy blade can be accurately evaluated, a basis is provided for repair and maintenance of the blade, and the long-time service reliability of the blade is improved.

Description

Technical field [0001] The present invention relates to a method of evaluating a high temperature alloy blade, in particular, relating to a microstructure degradation kinetic model and a long-term service combustion engine blade life assessment method for the relationship with the remaining mechanical properties. Background technique [0002] At present, due to the awareness of high-temperature alloy blades such as long-life combustion engine blades, long-life creep mechanisms Forecasts have always been a problem. Therefore, only a reasonable data model is established based on a large amount of long life experiment data, and the total life of the alloy is accurately predicted. The life prediction method of industrial combustion engine turbine blades mainly includes mechanical model blade life prediction method and material model life prediction method. [0003] The establishment of mechanical model prediction methods is mainly based on the correspondence between the steady spree ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/20G06F119/02G06F119/04G06F119/14
CPCG06F30/17G06F30/20G06F2119/02G06F2119/04G06F2119/14
Inventor 束国刚姜祥伟楼琅洪董加胜段方苗白小龙
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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