Conjugate Heat Transfer Analysis for Gas Turbine Film-Cooled Blade

Ho, Kuo-San; Liu, Jong S.; Elliott, Thomas J.; Aguilar, Bruno

doi:10.1115/gt2016-56688

Cited by 12 publications

(5 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…According to the actual turbine operating conditions and the research results from Menter et al [26] and Ho et al [27], compared with SA, RNG, k-ε turbulence models, the shear stress transport (SST) model was selected because it has better performance in the solid-fluid coupling simulation.…”

Section: Thermal-fluid-solid Coupling Numerical Methodsmentioning

confidence: 99%

Thermal-Fluid-Solid Coupling Analysis on the Temperature and Thermal Stress Field of a Nickel-Base Superalloy Turbine Blade

Cai

Wang

et al. 2021

Materials

View full text Add to dashboard Cite

Based on the establishment of the original and improved models of the turbine blade, a thermal–fluid–solid coupling method and a finite element method were employed to analyze the internal and external flow, temperature, and thermal stress of the turbine blade. The uneven temperature field, the thermal stress distribution characteristics of the composite cooling turbine blade under the service conditions, and the effect of the thickness of the thermal barrier coating (TBC) on the temperature and thermal stress distributions were obtained. The results show that the method proposed in this paper can better predict the ablation and thermal stress damage of turbine blades. The thermal stress of the blade is closely related to the temperature gradient and local geometric structure of the blade. The inlet area of the pressure side-platform of the blade, the large curvature region of the pressure tip of the blade, and the rounding between the blade body and the platform on the back of the blade are easily damaged by thermal stress. Cooling structure optimization and thicker TBC thickness can effectively reduce the high temperature and temperature gradient on the surface and inside of the turbine blade, thereby reducing the local high thermal stress.

show abstract

Section: Thermal-fluid-solid Coupling Numerical Methodsmentioning

confidence: 99%

Thermal-Fluid-Solid Coupling Analysis on the Temperature and Thermal Stress Field of a Nickel-Base Superalloy Turbine Blade

Cai

Wang

et al. 2021

Materials

View full text Add to dashboard Cite

show abstract

“…The shear stress transport (SST) model is selected as the turbulence model. According to the actual operating conditions of the turbine and the results of Menter [30] and Ho et al [31], the SST model has a better performance compared to SA, RNG, k-ε turbulence models. The calculation method adopts the couple algorithm, and the research state is steady state.…”

Section: Boundary Conditions and Calculation Methodsmentioning

confidence: 96%

Thermal Analysis of Turbine Blades with Thermal Barrier Coatings Using燰irtual Wall Thickness Method

Liu¹,

Wu²,

Huang³

et al. 2023

Computer Modeling in Engineering &Amp; Sciences

View full text Add to dashboard Cite

A virtual wall thickness method is developed to simulate the temperature field of turbine blades with thermal barrier coatings (TBCs), to simplify the modeling process and improve the calculation efficiency. The results show that the virtual wall thickness method can improve the mesh quality by 20%, reduce the number of meshes by 76.7% and save the calculation time by 35.5%, compared with the traditional real wall thickness method. The average calculation error of the two methods is between 0.21% and 0.93%. Furthermore, the temperature at the blade leading edge is the highest and the average temperature of the blade pressure surface is higher than that of the suction surface under a certain service condition. The blade surface temperature presents a high temperature at both ends and a low temperature in the middle height when the temperature of incoming gas is uniform and constant. The thermal insulation effect of TBCs is the worst near the air film hole, and the best at the blade leading edge. According to the calculated temperature field of the substrate-coating system, the highest thermal insulation temperature of the TC layer is 172.01 K, and the thermal insulation proportions of TC, TGO and BC are 93.55%, 1.54% and 4.91%, respectively.

show abstract

“…In order to simplify the calculation, it is assumed that the turbine blade endures three stages: take-off, cruising, and landing [26]. According to the actual working conditions of the gas turbine and the results of Menter et al [27] and Ho et al [28], the SST k-ω model is more consistent with the experimental results in the fluid-solid coupling calculations; thus, it was chosen for numerical simulation. This calculation is considered to have converged when the residual values for all variables fall below 10 −4 [11].…”

Section: Boundary Conditionsmentioning

confidence: 99%

Thermal–Fluid–Solid Coupling Analysis on the Effect of Cooling Gas Temperature on the Fatigue Life of Turbine Blades with TBCs

Chen,

Zhang,

et al. 2023

Coatings

View full text Add to dashboard Cite

The application of thermal barrier coatings (TBCs) can increase the blade’s operating temperature and fatigue life. Previous studies have neglected the effects of cooling gas temperature variations on the temperature field, stress field, and fatigue life of blades and TBCs. For this reason, this paper considers the inhomogeneity of the high-temperature gas inlet temperature, the internal cooling gas temperature, the periodicity of the external flow field, etc., and establishes a finite element model of the gas turbine blade with TBCs. Then, the life of the blade and the TBCs is predicted based on the Ncode 2020R2. Finally, the effect of the cooling gas temperature on the temperature, stresses, and life of the blade and the TBCs is analyzed. The results show that the fatigue life of the TBCs is lower than that of the blade, and the low-life region of the TBCs is located at the leading edge of the blade, which is consistent with the TBCs shedding region of the real blade and verifies the accuracy of the life prediction method in this paper. The fatigue life of the blade and TBCs firstly increases and then decreases with the increase in the cooling gas temperature, and the trend of the stress changes in the opposite direction. When the cooling gas temperature is increased from 573 K to 873 K, the minimum life of the blade is increased by 358.5%, and that of the TBCs is increased by 138.7%. The conclusions can provide guidance for the design of long-life turbine blades with TBCs.

show abstract

Conjugate Heat Transfer Analysis for Gas Turbine Film-Cooled Blade

Cited by 12 publications

References 0 publications

Thermal-Fluid-Solid Coupling Analysis on the Temperature and Thermal Stress Field of a Nickel-Base Superalloy Turbine Blade

Thermal-Fluid-Solid Coupling Analysis on the Temperature and Thermal Stress Field of a Nickel-Base Superalloy Turbine Blade

Thermal Analysis of Turbine Blades with Thermal Barrier Coatings Using燰irtual Wall Thickness Method

Thermal–Fluid–Solid Coupling Analysis on the Effect of Cooling Gas Temperature on the Fatigue Life of Turbine Blades with TBCs

Contact Info

Product

Resources

About