Heat transfer in the trailing region of gas turbines – A state-of-the-art review

Du, Wei; Li, Luo; Jiao, Yu; Wang, Songtao; Li, Xingchen; Sundén, Bengt

doi:10.1016/j.applthermaleng.2021.117614

Cited by 64 publications

(6 citation statements)

References 194 publications

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“…The increasing turbine inlet temperature will pose a greater challenge to the life and safety of turbine blades [2]. Therefore, many experts and scholars have conducted comprehensive research on the cooling technology of high temperature turbine blades of advanced gas turbines [3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Cooling Performance of a Steam-Cooled Blade Based on Response Surface Method

Zhao

Gao

et al. 2023

Applied Sciences

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In order to investigate the cooling mechanism of the turbine blade and to enrich and supplement the experimental study of the blade, a numerical study of a steam-cooled blade with five cooling channels was carried out based on the response surface model. The surface cooling efficiency and dimensionless temperature distribution of the steam-cooled blade were obtained with different mainstream inlet temperature, outlet pressure, pressure ratio of inlet to outlet, temperature ratio and flow ratio of steam to mainstream by using the flow-solid coupling numerical method. The influence of the working parameters on the cooling performance of air-cooled blade and steam-cooled blade, including the average cooling efficiency, temperature non-uniformity, and average dimensionless temperature, was comparatively investigated; the correlation equation of the working parameters on the cooling performance of the steam-cooled blade was obtained. The results show that the influence of mainstream inlet temperature and outlet pressure on the cooling performance of the steam-cooled blade is not significant; the cooling efficiency of the steam-cooled blade increases by 5.92%, 7.35% and 26.51% respectively as the mainstream inlet to outlet pressure ratio, the temperature ratio and the flow ratio of steam to mainstream increase; the dimensionless temperature increases by 3.74% as the temperature ratio increases and decreases by 0.93% and 4.09% as mainstream inlet to outlet pressure ratio and flow ratio increase; the temperature non-uniformity decreases by 4.09% and 30.08% respectively, as the mainstream inlet to outlet pressure ratio and temperature ratio increase and increases by 37.99% as the flow ratio increases; the effect of working parameters on air-cooled blade and steam-cooled blade is the same, but the steam-cooled blade has 14.06–17.81% higher cooling efficiency, 18.47–29.01% higher temperature non-uniformity and 1.86–2.58% lower dimensionless temperature compared to the air-cooled blade under the same working parameters; the correlation equation obtained by fitting the response surface model has higher accuracy.

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Section: Introductionmentioning

confidence: 99%

Numerical Study on Cooling Performance of a Steam-Cooled Blade Based on Response Surface Method

Zhao

Gao

et al. 2023

Applied Sciences

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“…Among the failure modes observed in gas turbine blades, the recurring loss of the trailing edge tip in the first-stage blades of industrial GTs has been a persistent concern [7,8].…”

Section: Introductionmentioning

confidence: 99%

Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

Bayro-Lazcano,

Piedra-Gonzalez,

García-Moreno

et al. 2023

Metals

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This paper investigates the root cause of a recurring failure observed in the first-stage blades of an industrial gas turbine. The failure involves the loss of the trailing edge tip of the blades. The study employs a combination of metallographic analysis and computational simulations utilizing the finite element method and computational fluid dynamics. The metallographic analysis reveals significant degradation in the GTD-111 nickel-based superalloy within the region where the failure occurs. This degradation is characterized by the coarsening and coalescence of the gamma prime phase, which can be attributed to localized overheating. Additionally, the computational study enables the calculation of the trajectory, pressure, and temperature profiles of the hot gases, as well as the distribution of temperatures within the blade. These findings demonstrate that the cooling airflow is influenced by the hot gas flow, particularly in the vicinity of the fault location, owing to the orientation of the cooling ducts, which results in overheating in this area. Ultimately, the temperatures derived from the microstructural analysis using the Ostwald-ripening theory align remarkably well with the results obtained from the simulation, validating the accuracy of the computational model. By combining metallographic analysis and computational simulations, this study provides crucial insights into the failure mechanism of the first-stage blades.

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“…The internal cooling strategies of modern gas turbines include jet impingement, rib turbulators, and pin fin, dimple/protrusion, latticework, etc. Most of the prior research indicates the trailing edge region suffers a higher temperature than other sections, and the narrow geometry of this region is the primary cause of the high-temperature distribution [9]. Pin fin elements are commonly used in trailing edge internal cooling, providing additional maintenance in this region.…”

Section: Introductionmentioning

confidence: 99%

Turbulent Flow Heat Transfer and Thermal Stress Improvement of Gas Turbine Blade Trailing Edge Cooling with Diamond-Type TPMS Structure

Yeranee,

Rao,

et al. 2023

Aerospace

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Additive manufacturing allows the fabrication of relatively complex cooling structures, such as triply periodic minimal surface (TPMS), which offers high heat transfer per unit volume. This study shows the turbulent flow heat transfer and thermal stress of the Diamond-TPMS topology in the gas turbine blade trailing edge channel. The thermal-fluid-solid analysis of the Diamond-TPMS structure, made of directionally solidified GTD111, at the nearly realistic gas turbine condition is executed, and the results are compared with the conventional pin fin array at the Reynolds number of 30,000. Compared to the baseline pin fin structure, the Diamond-TPMS model distributes flow characteristics more uniformly throughout the channel. The overall heat transfer enhancement, friction factor ratio, and thermal performance are increased by 145.3%, 200.9%, and 32.5%, respectively. The temperature, displacement, and thermal stress in the Diamond-TPMS model are also distributed more evenly. The average temperature on the external surface in the Diamond-TPMS model is lower than the baseline pin fin array by 19.9%. The Diamond-TPMS network in the wedge-shaped cooling channel helps reduce the volume displacement due to the material thermal expansion by 29.3%. Moreover, the volume-averaged von Mises stress in the Diamond-TPMS structure is decreased by 28.8%.

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Heat transfer in the trailing region of gas turbines – A state-of-the-art review

Cited by 64 publications

References 194 publications

Numerical Study on Cooling Performance of a Steam-Cooled Blade Based on Response Surface Method

Numerical Study on Cooling Performance of a Steam-Cooled Blade Based on Response Surface Method

Computational and Experimental Study on Failure Mechanism of a GTD-111 First-Stage Blade of an Industrial Gas Turbine

Turbulent Flow Heat Transfer and Thermal Stress Improvement of Gas Turbine Blade Trailing Edge Cooling with Diamond-Type TPMS Structure

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