Conjugate Heat Transfer Simulation of Overall Cooling Performance for Cratered Film Cooling Holes

Zhang, Chao; Wang, Wenzhuang; Wang, Zhan; Tong, Zhiting

doi:10.3390/machines10050395

Cited by 10 publications

(4 citation statements)

References 30 publications

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“…The continuity equation discretization uses the Rhie-Chow scheme. The numerical works [20][21][22]29] for cylindrical holes with or without the crescentshaped block in flat-plate conditions have already shown that the predicted results of laterally averaged cooling effectiveness agree well with the experimental data in [19]. The predicted total pressure loss coefficient profile along the spanwise direction at M = 2.2 is further provided in this study compared with the experimental data in [30], demonstrated in Figure 7.…”

Section: Computational Mesh and Numerical Methodssupporting

confidence: 70%

Film Cooling Performance of a Cylindrical Hole with an Upstream Crescent-Shaped Block in Linear Cascade

et al. 2023

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Recent works have already demonstrated that placing a crescent-shaped block upstream of a cylindrical hole could enhance the cooling performance of flat-plate films. The flow and cooling performance of the crescent-shaped block applied over the pressure and suction sides of the blade is investigated in this article. The Reynolds-averaged Navier-Stokes equations are solved with the Shear Stress Transport model for turbulence closure. Two optimized blocks are obtained from the flat-plate film cooling in our previous work, and two positions on the pressure and suction sides are tested. The blowing ratio varies from 0.5 to 2.0. The results show that when the block is applied on the blade surface, it yields a different cooling performance compared with the flat plate due to different geometry curvature and pressure gradient. The cooling performance on the suction side is slightly higher than on that on the pressure side, while the aerodynamic loss on the suction side is much higher. For the different blocks, the qualitative change of cooling performance vs. blowing ratios held on turbine blades is quite close to that of flat plates. The optimized smaller block in the flat plate provides better cooling performance at lower blowing ratios, while the larger block is superior when the blowing ratios are higher.

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Section: Computational Mesh and Numerical Methodssupporting

confidence: 70%

Film Cooling Performance of a Cylindrical Hole with an Upstream Crescent-Shaped Block in Linear Cascade

et al. 2023

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“…The boundary conditions of the computation domain are shown Figure 1a. The temperature of the mainstream and coolant were set at 1500 K and 750 K, respectively, to meet the density ratio under real engine operating conditions [28,29]. The mainstream Reynolds number (Re) based on D was set at 3326, from which the mainstream mass flow rate was determined.…”

Section: Conjugate Heat Transfer Analysismentioning

confidence: 99%

Numerical Investigation of the Effects of the Hole Inclination Angle and Blowing Ratio on the Characteristics of Cooling and Stress in an Impingement/Effusion Cooling System

Zhang

You

et al. 2023

Energies

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Due to the uneven temperature field and temperature gradient introduced by an efficient cooling structure, the analysis of the stress field is necessary. In this study, the cooling characteristics and stress characteristics such as the thermal stress and thermomechanical stress of an impingement/effusion cooling system were investigated by employing a fluid–thermal-structure coupling simulation method. The effects of film hole injection angle (30°–90°) and blowing ratio (0.5–2.0) were studied. The results showed that the film hole shape and the non-uniform temperature field introduced by the cooling structure had a great influence on the stress field distribution. With the increase in the blowing ratio, not only the overall cooling effectiveness of the cooling system increased, but the maximum thermal stress and thermomechanical stress near film holes also increased. The cases with a smaller inclination angle could provide a better cooling performance, but caused a more serious stress concentration of the film hole. However, the thermal stress difference at the leading and trailing edges of the film hole increased with a decreasing inclination angle. The cases with a = 30° and 45° showed serious thermal stress concentration near the hole’s acute region.

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“…As summarized by Goldstein et al [4], horseshoe vortex, passage vortex, and corner vortex all have a significant contribution to the thermal performance of the endwall. For the gas turbine, the compressor delivers a relatively high-pressure coolant at the interface between the turbine and the combustor to provide sealing and prevent the mainstream ingestion [5]. As a result, a film cooling layer is created, which effectively protects the endwall surface covered by the coolant injection.…”

Section: Introductionmentioning

confidence: 99%

Influence of the Slot Fillet and Vane Root Fillet on the Turbine Vane Endwall Cooling Performance

Pei

Shan³

et al. 2023

Machines

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Due to machining techniques and dust deposition, gas turbine upstream slots and vane roots are always filleted, significantly affecting the cooling performance of the endwall. The effects of upstream slot fillet and vane root fillet on the cooling performance of the gas turbine endwall were investigated by solving the three-dimensional Reynolds-averaged Navier–Stokes (RANS) equations with the shear stress transport (SST) k–ω turbulence model. The results indicate that the velocity distribution of the slot coolant is effectively changed by introducing the upstream slot fillets. Among the four cases, the largest adiabatic cooling effectiveness was obtained for the case with two similar fillets, with a 42% increase in effective cooling area compared to the traditional slot. At MFR = 0.75%, the horseshoe vortex is weakened by the introduction of the vane fillet with a small radius, with a 53% increase in effective cooling area compared to the baseline. However, the vane fillet with a large radius makes the boundary layer flow separately prematurely, decreasing the cooling performance. The lateral coverage of the coolant jet from the filmhole embedded in the vane root fillet is greatly enhanced by increasing the vane root fillet radius. However, the streamwise coverage is decreased and the thermodynamic loss is increased.

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Conjugate Heat Transfer Simulation of Overall Cooling Performance for Cratered Film Cooling Holes

Cited by 10 publications

References 30 publications

Film Cooling Performance of a Cylindrical Hole with an Upstream Crescent-Shaped Block in Linear Cascade

Film Cooling Performance of a Cylindrical Hole with an Upstream Crescent-Shaped Block in Linear Cascade

Numerical Investigation of the Effects of the Hole Inclination Angle and Blowing Ratio on the Characteristics of Cooling and Stress in an Impingement/Effusion Cooling System

Influence of the Slot Fillet and Vane Root Fillet on the Turbine Vane Endwall Cooling Performance

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