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

Cai, Liuxi; He, Yao; Wang, Shunsen; Li, Yun; Li, Fang

doi:10.3390/ma14123315

Cited by 31 publications

(13 citation statements)

References 22 publications

(25 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Under both conditions, the rotor blade's highest temperature is located at the blade tip near the leading-edge region (C and C1) on the suction surface (Figure 7c,d). The locations of the high-temperature areas (A,D,G,F;A1,D1,G1,F1) are similar to those found from the actual service moving blade (Figure 7e) with similar boundary conditions and geometric shape under the rotating condition [32]. Because of the mainstream entrainment effect of the complex end-wall vortices, the film cooling on the blade tip and root is destroyed without adequate coolant coverage.…”

Section: Heat Transfer Analysissupporting

confidence: 62%

Numerical Analysis of Conjugated Heat Transfer and Thermal Stress Distributions in a High-Temperature Ni-Based Superalloy Turbine Rotor Blade

et al. 2022

View full text Add to dashboard Cite

This paper establishes a multidisciplinary method combining conjugate heat transfer (CHT) and thermal stress for a high-temperature Ni-based superalloy turbine rotor blade with integrated cooling structures. A conjugate calculation is performed to investigate the coolant flow characteristics, heat transfer, and thermal stress of the rotor blade under rotating and stationary conditions to understand the effects of rotation on the multidisciplinary design of the blade. Furthermore, the maximum resolved shear stress among the 30-slip systems and the corresponding dominant slip system are obtained to predict the deformation tendency of the blade by employing the crystal plasticity finite element method (CPFEM) and considering the specified anisotropic blade material (GTD-111). The results show that the forces of rotation, including centrifugal and Coriolis forces, and their induced buoyancy force, alter the coolant flow field and thus affect the rotor blade’s heat transfer distribution compared with the stationary condition. The maximum temperature and thermal stress of the rotor blade under rotating conditions are reduced by 5% and 21% compared with that under the stationary condition, respectively. Compared with the stationary condition, the temperature and thermal stress distribution on the blade under the rotating condition are more uniform, especially on the suction side. In addition, the blade root connecting with the hub, the film holes near the leading-edge region at the blade root, the mid-chord of the suction surface, and the grooved blade tip are easily damaged by the enormous resolved shear stress and the interface effect of different types of dominant slip system under the two conditions. In this work, it was feasible to use the cascade cooling effect test to analyze the dynamic test results for the rotor blade. Furthermore, the thermal stress analysis based on the CPFEM can provide a superior level of blade cooling design than CHT by considering the anisotropic material characteristics of a turbine blade.

show abstract

Section: Heat Transfer Analysissupporting

confidence: 62%

Numerical Analysis of Conjugated Heat Transfer and Thermal Stress Distributions in a High-Temperature Ni-Based Superalloy Turbine Rotor Blade

et al. 2022

View full text Add to dashboard Cite

show abstract

“…In the presented case, three-dimensional temperature distribution will lead to the thermal fight between hot and cold regions. Validated thermal map of nozzle guide vane is also extremely important [ 39 ] to predict thermal loads between vane and adjacent components made from other materials characterized with higher or lower thermal expansion coefficients.…”

Section: Discussionmentioning

confidence: 99%

Thermal-Fluid–Solid Coupling—Parametrical Numerical Analysis of Hot Turbine Nozzle Guide Vane

Froissart

Ochrymiuk

2021

Materials

View full text Add to dashboard Cite

The cooling technology of hot turbine components has been a subject of continuous improvement for decades. In high-pressure turbine blades, the regions most affected by the excessive corrosion are the leading and trailing edges. In addition, high Kt regions at the hot gas path are exposed to cracking due to the low and high cycle fatigue failure modes. Especially in the case of a nozzle guide vane, the ability to predict thermally driven loads is crucial to assess its life and robustness. The difficulties in measuring thermal properties in hot conditions considerably limit the number of experimental results available in the literature. One of the most popular test cases is a NASA C3X vane, but coolant temperature is not explicitly revealed in the test report. As a result of that, numerous scientific works validated against that vane are potentially inconsistent. To address that ambiguity, the presented work was performed on a fully structural and a very fine mesh assuming room inlet temperature on every cooling channel. Special attention was paid to the options of the k−ω SST (shear-stress transport) viscosity model, such as Viscous heating (VH), Curvature correction (CC), Production Kato-Launder (KT), and Production limiter (PL). The strongest impact was from the Viscous heating, as it increases local vane temperature by as much as 40 deg. The significance of turbulent Prandtl number impact was also investigated. The default option used in the commercial CFD code is set to 0.85. Presented study modifies that value using equations proposed by Wassel/Catton and Kays/Crawford. Additionally, the comparison between four, two, and one-equation viscosity models was performed.

show abstract

“…The calculation method adopts the couple algorithm, and the research state is steady state. When the residuals of each item are lower than 10 −4 and the temperature of the monitoring point no longer changes, the calculation is considered to be converged [32]. Under the same computing power, the real wall thickness method takes 307 min to complete the calculation, while the virtual wall thickness method takes 198 min, saving 35.5% of the calculation time.…”

Section: Boundary Conditions and Calculation Methodsmentioning

confidence: 99%

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

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

Cited by 31 publications

References 22 publications

Numerical Analysis of Conjugated Heat Transfer and Thermal Stress Distributions in a High-Temperature Ni-Based Superalloy Turbine Rotor Blade

Numerical Analysis of Conjugated Heat Transfer and Thermal Stress Distributions in a High-Temperature Ni-Based Superalloy Turbine Rotor Blade

Thermal-Fluid–Solid Coupling—Parametrical Numerical Analysis of Hot Turbine Nozzle Guide Vane

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

Contact Info

Product

Resources

About