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

Zhao, Zhen; Xi, Lei; Gao, Jianmin; Xu, Liang; Li, Yunlong

doi:10.3390/app13116625

Cited by 4 publications

(3 citation statements)

References 30 publications

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“…Therefore, this method is called surrogate-based optimization (SBO). Common surrogate models include the response surface method (RSM) [36], support vector regression (SVR) [37], radial basis function (RBF) [38], and Kriging model (KM) [39]. In these surrogate models, KM takes values from regionalized variables in finite regions and makes optimal and unbiased estimates from the perspective of the correlation and variability of variables.…”

Section: Introductionmentioning

confidence: 99%

Prediction and Optimization of Heat Transfer Performance of Premixed Methane Impinging Flame Jet Using the Kriging Model and Genetic Algorithm

Chen,

2024

Applied Sciences

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In practical applications, rapid prediction and optimization of heat transfer performance are essential for premixed methane impinging flame jets (PMIFJs). This study uses computational fluid dynamics (CFD) combined with a methane detailed chemical reaction mechanism (GRI–Mech 3.0) to study the equivalence ratio (Φ), Reynolds number (Re) of the mixture, and the normalized nozzle–to–plate distance (H/d) on the heat transfer performance of PMIFJs. Moreover, the Kriging model (KM) was used to construct a prediction model of PMIFJ heat transfer performance. A genetic algorithm (GA) was used to determine the maximum likelihood function (MLE) of the model parameters for constructing KM and identify the points with the maximum root mean square error (RMSE) as the new infilled points for surrogate–based optimization (SBO). Combining these methods to analyze the simulation results, the results show that the global heat transfer performance of PMIFJs is enhanced with the increase in Φ, the increase in Re, and the decrease in H/d. Sensitivity analysis points out that Re and Φ significantly affect enhanced heat transfer, while H/d has a relatively small effect. In addition, GA was also used to search for the optimal heat transfer performance, and the global heat transfer performance at specific conditions was significantly enhanced. This study deepens the understanding of the heat transfer mechanism of impinging flame jets and provides an efficient method framework for practical applications.

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Section: Introductionmentioning

confidence: 99%

Prediction and Optimization of Heat Transfer Performance of Premixed Methane Impinging Flame Jet Using the Kriging Model and Genetic Algorithm

Chen,

2024

Applied Sciences

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“…The innovative point of the current study lies in that the effect of size and arrangement parameters of pin-fin cooling structures with steam coolant is comprehensively studied, and these parameters are used to create the correlation fitting of pin-fin-steam cooling channels, which can provide a valuable empirical formula for this type of high-efficiency cooling structure design. The research team to which the author belongs has conducted experimental and numerical investigations on a heavy-duty gas turbine featuring a steam-cooled turbine blade [33,34]. The trailing-edge channel of the above turbine blade in Ref.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Steam Cooling Characteristics in a Isosceles Trapezoidal Channel with Pin-Fin Arrays at Turbine Blade Trailing Edge

Xi,

Gao,

Ruan

et al. 2024

Energies

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Using the SST k-ω turbulence model, a comprehensive numerical investigation was conducted to analyze the flow and heat transfer characteristics of steam within an isosceles trapezoidal cooling channel with pin-fin arrays modeled from the trailing edge of a F-class gas turbine high-temperature blade. The influence laws of various parameters, including the Reynolds number (Re, from 10,000 to 50,000), dimensionless pin-fin diameter (d/H, from 0.4 to 0.8), and dimensionless pin-fin spacing (S/H, from 1.6 to 2.4), on the flow and heat transfer performance of the isosceles trapezoidal cooling channel with pin-fin arrays were examined. Sensitivity analysis was employed to determine the relative significance of these influence parameters on the cooling performance of the isosceles trapezoidal channel with pin-fin arrays. Finally, the corresponding heat transfer and friction correlations within the investigated parameter range were developed. The research findings reveal that under different Reynolds numbers, as the dimensionless pin-fin diameter increases from 0.4 to 0.8, the friction factor within the isosceles trapezoidal cooling channel with pin-fin arrays increases by a factor of 3.25 to 3.41, while the overall average Nusselt number improves by 31.05% to 37.41%. Conversely, when the dimensionless pin-fin spacing increases from 1.6 to 2.4, the friction factor within the isosceles trapezoidal cooling channel with pin-fin arrays decreases by 67.38% to 69.18%, accompanied by a reduction in the overall average Nusselt number by 24.95% to 31.14%. When both the flow performance and heat transfer performance are taken into account, the importance of the influence parameters ranks as follows: Reynolds number, pin-fin diameter, and pin-fin spacing. It also suggests that smaller pin-fin diameters and larger pin-fin spacing should be selected in the design stage based on the variation laws of integrated thermal-hydraulic performance. The results may provide valuable references and insights for the design of steam cooling structures within high-temperature turbine blade trailing edge channels in advanced gas turbines.

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“…Wang et al [16] numerically studied lobe-shaped holes using a large eddy simulation (LES) to track the flow field of film cooling. Zhao et al [17] used the response surface method to analyze the cooling characteristics of a stream-cooled blade.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Endwall Modification with Micro-Scale Ribs in a Turbine Cascade

Liu,

Song,

et al. 2023

Applied Sciences

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A novel modification method, the ‘micro-scale’ rib, is proposed to expand cooling coverage for turbine endwalls. However, the introduction of the rib will inevitably affect the flow in the near-wall region. Therefore, the variation in the flow pattern for the traditional model of secondary flow needs further exploration. In this paper, to gain a clearer understanding of the micro-scale rib, the original endwall and three types of ribbed endwalls were adopted to numerically present the detailed flow, film cooling, and heat transfer information for the endwall surface and phantom cooling on the suction side (SS) of the blade. The Ansys code CFX was utilized to solve the 3D Reynolds-averaged Navier–Stokes (RANS) equations, and the SST k-ω was selected as the turbulence model after the verification. The results show that the rib-like vortex changed the flow of the coolant and had various impacts on the cooling characteristics. Although the cooling performance of the ribbed endwall improved, it also had a negative impact on heat transfer in most cases. Compared with the original, the vertical rib cases provided optimal film cooling, with increases of 26.9% and 17.4% for rib spacing values of 8 mm and 10 mm, respectively, with little difference in heat transfer (less than 1%). In addition, the horizontal rib cases presented the worse performance for both film cooling and heat transfer, which indicates that the rib layout should consider a mainstream flow direction for future designs.

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

Cited by 4 publications

References 30 publications

Prediction and Optimization of Heat Transfer Performance of Premixed Methane Impinging Flame Jet Using the Kriging Model and Genetic Algorithm

Prediction and Optimization of Heat Transfer Performance of Premixed Methane Impinging Flame Jet Using the Kriging Model and Genetic Algorithm

Numerical Study on Steam Cooling Characteristics in a Isosceles Trapezoidal Channel with Pin-Fin Arrays at Turbine Blade Trailing Edge

Numerical Study of Endwall Modification with Micro-Scale Ribs in a Turbine Cascade

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