Failure Analysis of a Compressor Blade of Gas Turbine Engine

Biswas, Swati; Ganeshachar, M.D.; Kumar, Jivan; Kumar, Varada N. Satish

doi:10.1016/j.proeng.2014.11.116

Cited by 15 publications

(4 citation statements)

References 9 publications

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“…In the first four crack propagation stages, the SIF range at u = 90°DK u = 90 8 is larger than DK u = 0 8 and DK u = 180 8 , indicating that the crack depth increases faster than the crack length. In the initial stage of crack propagation, the initial semi-elliptical crack tends to grow into a semi-circular crack, which is consistent with the conclusion drawn by Biswas et al 34 In the subsequent crack propagation stage, DK u = 0 8 and DK u = 180 8 are larger than DK u = 90 8 , indicating that the crack length grows faster than the crack depth. In addition, the value of DK u = 180 8 is the largest after the 21st crack growth stage, which means that the crack tends to expand near the crack end point u = 180°closer to the free surface.…”

Section: Crack Propagation Analysissupporting

confidence: 90%

A hybrid modeling method of fatigue crack growth for gas turbine blades under combined high and low cycle fatigue loadings

Yang,

Huang,

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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Fatigue crack is one of the major faults of the gas turbine blades. Previous modeling studies on fatigue crack growth of blades mainly focus on a single numerical or analytical approach considering different sizes of cracks under various fatigue loadings. However, the actual crack propagation process is time-varying. The iteration and update of the model are necessary to evaluate the fatigue life of blades precisely. This paper proposes a hybrid modeling method to study blade crack growth under combined high and low cycle fatigue (CCF) loadings. The method emphasizes the combination and interaction between the finite element (FE) numerical simulation and the analytical calculation based on the fracture mechanics model. The current crack propagation length of the blade FE model is calculated from the crack growth rate obtained by the stress intensity factor (SIF) range according to Paris law. Then, a new SIF range is resolved from the FE model with the updated crack length. The proposed method is verified by the first-stage compressor blade from an in-service gas turbine. Results show that the crack growth is faster using the proposed hybrid modeling method than the traditional method. The update of the SIF range under CCF loadings cannot be ignored when predicting the fatigue life of the blade. Also, a sensitivity analysis is carried out. Suggestions are given on how to set the crack extension length at each stage during modeling, especially when the blade approaches failure.

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Section: Crack Propagation Analysissupporting

confidence: 90%

A hybrid modeling method of fatigue crack growth for gas turbine blades under combined high and low cycle fatigue loadings

Yang,

Huang,

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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show abstract

“…Statistics indicate that fatigue failure contributes to almost 50% of all component damages in gas turbines [71]. Similarly, the fatigue failure also causes problems in the compressor blade, as reported in [72]. The damage experienced in blades and nozzles (stationary blades) will be hard to cure since they have complicated configurations.…”

Section: Faults In Dle Gas Turbinementioning

confidence: 99%

Dry-Low Emission Gas Turbine Technology: Recent Trends and Challenges

et al. 2022

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Dry-low emission (DLE) is one of the cleanest combustion types used in a gas turbine. DLE gas turbines have become popular due to their ability to reduce emissions by operating in lean-burn operation. However, this technology leads to challenges that sometimes interrupt regular operations. Therefore, this paper extensively reviews the development of the DLE gas turbine and its challenges. Numerous online publications from various databases, including IEEE Xplore, Scopus, and Web of Science, are compiled to describe the evolution of gas turbine technology based on emissions, fuel flexibility, and drawbacks. Various gas turbine models, including physical and black box models, are further discussed in detail. Working principles, fuel staging mechanisms, and advantages of DLE gas turbines followed by common faults that lead to gas turbine tripping are specifically discussed. A detailed evaluation of lean blow-out (LBO) as the major fault is subsequently highlighted, followed by the current methods in LBO prediction. The literature confirms that the DLE gas turbine has the most profitable features against other clean combustion methods. Simulation using Rowen’s model significantly imitates the actual behavior of the DLE gas turbine that can be used to develop a control strategy to maintain combustion stability. Lastly, the data-driven LBO prediction method helps minimize the flame’s probability of a blow-out.

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“…It means that the increase in the crack length is faster than its depth and also, the crack growths more toward attack edge (instead of trailing edge) [33]. The reason that this behavior is not observed in the first stage of growth is explained in [34] as follows: generally, semi elliptical cracks tend to change to semicircular cracks during the initial growth stages.…”

Section: Calculations Of Crack Growth On the Suction Sidementioning

confidence: 99%

Crack growth simulation in 13th row of compressor blades under foreign object damage and resonant vibration condition

Moradi¹,

Rafi²,

Muslim³

2020

J. vibroeng.

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In this study, the cracks growth rate in the 13th row of the T56 compressor blades was studied to investigate their fatigue life. For this purpose, the centrifugal and aerodynamic forces on the blade were calculated and then the resulting stress field was obtained by using finite element method. Then, the critical points of stress were determined and the initial semi-elliptical cracks were modeled at these points. After modeling of the initial crack, the stress intensity factor on the crack front was calculated by ANSYS software. Furthermore, the number of required cycles for the crack growth and blade fracture were calculated by applying Paris law to a certain value. After crack growth at this stage, a crack with new length was also modeled at the same point and all the mentioned stages for its growth, were repeated. In this paper, the modal analysis of the blade was conducted and normal frequencies with possible stimulation on compressor velocity were determined by Campbell Diagram. After determining the stress field at resonant frequency, all stages of crack growth were repeated under these conditions to calculate the fatigue life.

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Failure Analysis of a Compressor Blade of Gas Turbine Engine

Cited by 15 publications

References 9 publications

A hybrid modeling method of fatigue crack growth for gas turbine blades under combined high and low cycle fatigue loadings

A hybrid modeling method of fatigue crack growth for gas turbine blades under combined high and low cycle fatigue loadings

Dry-Low Emission Gas Turbine Technology: Recent Trends and Challenges

Crack growth simulation in 13th row of compressor blades under foreign object damage and resonant vibration condition

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