Enabling Technologies for Advanced Turbine Component Life Extension

Liburdi, J.; Lowden, P.

doi:10.1115/99-gt-445

Cited by 3 publications

(3 citation statements)

References 8 publications

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“…Due to high replacement costs of turbine blades, immense research studies have been investigated to refurbish the damaged turbine airfoils at lower costs. Tungsten inert gas (TIG) welding becomes one of the most desirable and economical refurbishment methods for a commercial restoration [1,2]. Dendritic microsegregation or microfissuring and inhomogeneity of second phase precipitates (eg.…”

Section: Introductionmentioning

confidence: 99%

Effect of Pre-Weld Heat Treatment Temperatures on TIG Welded Microstructures on Nickel Base Superalloy, GTD-111

Rojhirunsakool

Thongpian

Chuankrerkkul

et al. 2015

KEM

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Nickel-base superalloys have been used as high temperature materials in land-base gas turbine application. When subjected to long term, high temperature service, large crack propagation was observed. Typical refurbishment method of these turbines is carried out by using TIG welding followed by post-weld standard heat treatment. However, new crack initiation is found in the heat-affected zone after TIG welding. Pre-weld heat treatment has been discovered to improves final γ + γ’ microstructure. This study focuses on the effect of pre-weld heat treatment temperature on final γ + γ’ microstructure. Seven different conditions of pre-weld heat treatment temperature were investigated. Scanning electron microscopy studies were carried out after pre-weld and post-weld heat treatments to compare the γ + γ’ microstructure and capture microcracks. The best pre-weld heat treatment temperature produces uniform distribution of finely dispersed γ’ precipitates in the γ matrix without post-weld crack.

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Section: Introductionmentioning

confidence: 99%

Effect of Pre-Weld Heat Treatment Temperatures on TIG Welded Microstructures on Nickel Base Superalloy, GTD-111

Rojhirunsakool

Thongpian

Chuankrerkkul

et al. 2015

KEM

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“…Material properties are not the only fundamental factor. Lifing methodologies are fundamental in declaring safe component life, in optimizing material usage without unnecessary inspection and in establishing maintenance procedures 2–13 . Life‐to‐first crack (LTFC) assumes that, initially, parts are considered to be free of defects.…”

Section: Introductionmentioning

confidence: 99%

“…Lifing methodologies are fundamental in declaring safe component life, in optimizing material usage without unnecessary inspection and in establishing maintenance procedures. [2][3][4][5][6][7][8][9][10][11][12][13] Life-to-first crack (LTFC) assumes that, initially, parts are considered to be free of defects. Component 'failure' is defined as the occurrence of an 'engineering crack' of specified length.…”

Section: Introductionmentioning

confidence: 99%

Fatigue life prediction and failure analysis of a gas turbine disc using the finite‐element method

Cláudio

Branco²,

Gomes³

et al. 2004

Fatigue Fract Eng Mat Struct

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A B S T R A C T A numerical prediction of the life of a gas turbine model disc by means of the finite-elementtechnique is presented and the solution is compared with an experimental rim-spinning test. The finite-element method was used to obtain the K solution for a disc with two types of cracks, both at the notch root of the blade insert and located in the corner and in the centre. A crack aspect ratio of (a/c) = 1 was assumed. The fracture mechanics parameters J-integral and K were used in the assessment, which were computed with linear elastic and elastic-plastic material behaviour. Using a crack propagation program with appropriate fatigue-creep crack growth-rate data, previously obtained in specimens for the nickel-based superalloy IN718 at 600 • C, fatigue life predictions were made. The predicted life results were checked against experimental data obtained in real model discs.The numerical method, based on experimental fatigue data obtained in small laboratory specimens, shows great potential for development, and may be able to reduce the enormous costs involved in the testing of model and full-size components. a = crack depth c = half crack length at surface C, m = Paris law parameters E = Young's modulus f = frequency J = J-integral K = stress intensity factor K C = critical stress intensity factor N = number of cycles N t = total number of cycles N p = number of cycles in propagation N i = number of cycles in initiation R = radius r 2 = regression correlation coefficient S UTS = True ultimate tensile stress α = Thermal expansion coefficient K th = Threshold stress intensity factor Correspondence: R.A. Cláudio.

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Refurbishment of Creep Damage Using Re-Heat Process for Ni-Based Superalloy under Bending Load

Sekihara¹,

Ichikawa²,

Imano³

et al. 2011

J. Soc. Mat. Sci., Japan

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Enabling Technologies for Advanced Turbine Component Life Extension

Cited by 3 publications

References 8 publications

Effect of Pre-Weld Heat Treatment Temperatures on TIG Welded Microstructures on Nickel Base Superalloy, GTD-111

Effect of Pre-Weld Heat Treatment Temperatures on TIG Welded Microstructures on Nickel Base Superalloy, GTD-111

Fatigue life prediction and failure analysis of a gas turbine disc using the finite‐element method

Refurbishment of Creep Damage Using Re-Heat Process for Ni-Based Superalloy under Bending Load

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