On-line detection of porosity change of high temperature blade coating for gas turbine

Shi, Licheng; Long, Yun; Wang, Yuzhang; Chen, Xiaohu; Zhao, Qunfei

doi:10.1016/j.infrared.2020.103415

Cited by 10 publications

(11 citation statements)

References 23 publications

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“…For a certain period of high temperature exposures, TBC experienced degradations such as sintering, hot corrosion, erosion, wear, foreign object damage (FOD) etc. Under real gas turbine operation, TBC will experience the combination of any of these, which will not only affect the thermal insulation performance of TBC, but also the efficiency of the cooling system [6]. In worst situations, premature failure of TBC will occur prior to the actual design life.…”

Section: Tbc Simulation Test Rigmentioning

confidence: 99%

“…The level of the hot gas temperature is now beyond the maximum material temperature of the gas turbine components [4]. For this reason, many technologies have been developed and applied, such as advanced superalloys; advanced thermal barrier coating (TBC); cooling systems, such as cooling air for hot gas path components; and advanced combustion systems [5][6][7][8][9]. TBC application in gas turbine is well-known and has been widely tested and discussed by researchers.…”

Section: Introductionmentioning

confidence: 99%

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Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review

et al. 2021

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Thermal barrier coating (TBC) and cooling air systems are among the technologies that have been introduced and applied in pursuing the extensive development of advanced gas turbine. TBC is used to protect the gas turbine components from the higher operating temperature of advanced gas turbine, whereas cooling air systems are applied to assist TBC in lowering the temperature exposure of protected surfaces. Generally, a gas turbine operates in three main operational modes, which are base load, peak load, and part peak load. TBC performance under these three operational modes has become essential to be studied, as it will provide the gas turbine owners not only with the behaviors and damage mechanism of TBC but also a TBC life prediction in a particular operating condition. For TBC under base load or so called steady-state condition, a number of studies have been reviewed and discussed. However, it has been found that most of the studies have been conducted without the assistance of a cooling air system, which does not simulate the TBC in advanced gas turbine completely. From this review, the studies on TBC-assisted cooling air system to simulate the advanced gas turbine operating conditions have also been summarized, which are limited to test rig simulations under thermal cyclic mode where thermal cyclic represents peak and part peak load conditions. The equipment used to simulate the gas turbine operating condition, test temperatures, and durations are parameters that have been taken into consideration under this review. Finally, a test rig that is capable of simulating both TBC and cooling air effects at a high operating temperature of advanced gas turbines for prolonged exposure under steady-state condition has been proposed to be developed.

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Section: Tbc Simulation Test Rigmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review

et al. 2021

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“…Inlet gas temperature could be raised to 1700°C. 6 Therefore, nickel-based super-alloys are generally selected as blade material. [5][6][7] Moreover, turbine blades are working under extremely corrosive and erosive conditions which is imposed by oxidizing gas and mechanical fatigue.…”

Section: Introductionmentioning

confidence: 99%

Nondestructive inspection of gas turbine blades by active thermography using different fluids

Mohammadian

Akbari

Farahani

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part B:

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Presence of defects in the gas turbine blades’ affects the blade performance and reduces the blade life. One of the common defects in the internal cooling passages of a gas turbine blade, is residual ceramic created in the blade production stage. This types of defects, can be beneficially detected by using active thermography. In this paper, nondestructive testing of internal cooling passages of a gas turbine blade is conducted by active thermography method using different types of excitations. Carbon dioxide (CO2), hot air, and water-vapor were selected as excitation sources. Inspection with water-vapor stimulations were performed at three different pressures flow rates. Results indicated that the IR thermography tests with water-vapor excitation, provide higher detectability compared to the other methods. However, internal passages were revealed by all of the pre-mentioned excitation methods. Residual ceramic in internal passages of the blade were clearly revealed by application of hot air and water-vapor. Results also indicated that application of the maximum pressure and flow rate, offer a better detectability and visibility. Some surface defects on the gas turbine blades were also been detected by application of water-vapor excitation.

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“…Researchers usually start ROIs extraction by either applying a kind of designated threshold, or edge detection by analyzing the local gradients [17,18]. Feature extraction and classification methods of images are also extensively studied [19][20][21][22]. However, traditional image processing methods are used for surface cracks detection.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Internal Cracks in Turbine Blade Thermal Barrier Coating Using Enhanced Multi-Scale Faster R-CNN Model

et al. 2022

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Thermal Barrier Coatings (TBCs) have good performance in heat insulation during service on turbine blades. However, the accumulated residual stress will form cracks, which can easily lead to coating failure. To ensure safe operation, it is necessary to find a method that can evaluate the health of the coating. In this paper, a non-destructive evaluation technique based on Multi-Scale Enhanced-Faster R-CNN (MSE-Faster R-CNN) is proposed. Firstly, the Visual Geometry Group Network19 layer (VGG-19) was adopted as the baseline network to find the candidate crack Region of Interest (ROI). Considering the influence of the crack on the surroundings, the ROI was expanded to obtain the context information. Secondly, a multi-scale Faster R-CNN detector was used to refine the candidate regions, and provided a comprehensive feature for better crack detection. Finally, a fusion lifetime prediction model was proposed to estimate the remaining lifetime of the TBC. Extensive experiments were conducted to evaluate the performance of the proposed method. The results demonstrated that the proposed method can accurately locate (0.898) and detect (0.806) the cracks in different scales, and the lifetime estimation result reached the best level (Root Mean Square Error (RMSE) = 2.7); there wasas also an acceptable time cost (1.63 s), and all detection conditions of the error rates were below 15%, achieving the best results among the state-of-art methods.

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On-line detection of porosity change of high temperature blade coating for gas turbine

Cited by 10 publications

References 23 publications

Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review

Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review

Nondestructive inspection of gas turbine blades by active thermography using different fluids

Evaluation of Internal Cracks in Turbine Blade Thermal Barrier Coating Using Enhanced Multi-Scale Faster R-CNN Model

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