SEM Gamma Prime Observation in a Thermal and Stress Analysis of a First-stage Rene’ 80H gas Turbine Blade: Numerical and Experimental Investigation

Khalesi, Javad; Modaresahmadi, Sina; Atefi, Gholamali

doi:10.1007/s40997-018-0235-0

Cited by 12 publications

(4 citation statements)

References 37 publications

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“…Combined with the Coulomb-Mohr and von Mises theory, it indicated that the UHTC can be used to manufacture the turbine vanes. Javad Khalesi et al [12] used an improved conjugate heat transfer (CHT) method to analyze the structural and thermal stresses on the first-stage turbine blade. It is found that the minimum stress obtained by using a material with temperature-dependent properties is higher than that by using temperature-independent material properties, and the predicted service life of the turbine blades is more accurate by the former method.…”

Section: Introductionmentioning

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

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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.

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Section: Introductionmentioning

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

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“…The multi-field environmental loads on turbine rotors deserve focused attention in turbine failure analysis, including centrifugal load, aerodynamic load, and thermal load [19]. The performance of the turbine rotor significantly degrades in operation under high temperatures [16,20,39]. The large temperature gradient causes higher thermal stresses in vital sites [33].…”

Section: Introductionmentioning

confidence: 99%

Reliability analysis of multi-site damage with failure dependency of the turbine based on flow-thermal-solid coupling analysis and the Monte Carlo validated simulations

Qian¹,

Zeng²,

Huang³

et al. 2023

Eksploatacja i Niezawodność – Maintenance and Reliability

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The harsh environmental loads may lead to strength failure in the turbine in an aero-engine. To accurately assess the strength reliability of the turbine under multiple loads, the stress distributions of 41 danger sites of a turbine under thermal, centrifugal, and pneumatic loads were determined by the flow-thermal-solid coupling analysis using ANSYS. Second, based on the flow-thermal-solid coupling analysis and response surface method, the probabilistic analysis model of stress at the danger site was established. And the probabilistic distribution of stress was determined by sampling and hypothesis testing. Finally, the reliability model of the turbine with multi-site damage and failure dependency was established, by which a reliability of 0.99802 was calculated. And the actual reliability of the turbine was 0.99626 determined by the Monte Carlo simulations, which verified the model in precision. The results indicated that the reliability model has a high efficiency and higher precision than the traditional reliability model with failure independence.

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“…It was found that the point of risk of blade fatigue failure (maximum equivalent stress) is located in the fir-tree region of the blade. Javad et al [10] used the modified conjugate heat transfer (CHT) method to numerically analyze the structure and thermal stresses of the first-stage turbine blade. The results show that temperature-dependent materials are more accurate in predicting the fatigue life of turbine blades.…”

Section: Introductionmentioning

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

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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.

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SEM Gamma Prime Observation in a Thermal and Stress Analysis of a First-stage Rene’ 80H gas Turbine Blade: Numerical and Experimental Investigation

Cited by 12 publications

References 37 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

Reliability analysis of multi-site damage with failure dependency of the turbine based on flow-thermal-solid coupling analysis and the Monte Carlo validated simulations

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

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