Stress analysis of a second stage gas turbine blade under asymmetric thermal gradient

Rahimi, Javad; Poursaeidi, Esmaeil; Khavasi, Ehsan

doi:10.1051/meca/2019041

Cited by 9 publications

(5 citation statements)

References 15 publications

(20 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Due to the effect of substrate material on the results, the substrate material with the specifications mentioned in Table (1) was considered according to the real samples used in gas turbines. For this purpose, flake specimens with a diameter of 25 mm and a thickness of 3 mm were extracted from the first row turbine blade specimen by wire cut method.…”

Section: Manufacturing Specimensmentioning

confidence: 99%

See 1 more Smart Citation

Analytical and Experimental Study of Residual Stresses in Thermal Barrier Coatings Deposited on Gas Turbine Blades in Laboratory Dimensions by APS and HVOF Methods to Calculate the Optimal Thickness

Poursaeidi¹,

Montakhabi²,

Rahimi³

2021

JTSE

Self Cite

View full text Add to dashboard Cite

The constant need to use gas turbines has led to the need to increase turbines' inlet temperature. When the temperature reaches a level higher than the material's tolerance, phenomena such as creep, changes in mechanical properties, oxidation, and corrosion occur at high speeds, which affects the life of the metal material. Nowadays, operation at high temperatures is made possible by proceedings such as cooling and thermal insulation by thermal barrier coatings (TBCs). The method of applying thermal barrier coatings on the turbine blade creates residual stresses. In this study, residual stresses in thermal barrier coatings applied by APS and HVOF methods are compared by Tsui–Clyne analytical model and XRD test. The analytical model results are in good agreement with the experimental results (between 2 and 8% error), and the HVOF spray method creates less residual stress than APS. In the end, an optimal thickness for the coating is calculated to minimize residual stress at the interface between the bond coat and top coat layers.

show abstract

Section: Manufacturing Specimensmentioning

confidence: 99%

“…There are two ways to reduce the temperature of gas turbine blades. The first method is cooling and the second method is using thermal barrier coatings [1]. Thermal barrier coatings are usually made of a combination of different layers, each layer having a specific function.…”

Section: Introductionmentioning

confidence: 99%

Analytical and Experimental Study of Residual Stresses in Thermal Barrier Coatings Deposited on Gas Turbine Blades in Laboratory Dimensions by APS and HVOF Methods to Calculate the Optimal Thickness

Poursaeidi¹,

Montakhabi²,

Rahimi³

2021

JTSE

Self Cite

View full text Add to dashboard Cite

show abstract

“…Thermal barrier coatings (TBCs) are multilayered systems applied to gas turbine engine components to increase their operating temperature and lifetime. 1,2 TBC systems usually consist of four different layers. These layers include the superalloy substrate, metal bond coat (BC) layer, thermally grown oxide (TGO), and ceramic top coat (TC) layer.…”

Section: Introductionmentioning

confidence: 99%

“…Thermal barrier coatings (TBCs) are multilayered systems applied to gas turbine engine components to increase their operating temperature and lifetime 1,2 . TBC systems usually consist of four different layers.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical life evaluation of TBCs with different BC and diffusion coating under cyclic thermal loading

Rahimi

Montakhabi

Sigaroodi

et al. 2023

Int J Applied Ceramic Tech

Self Cite

View full text Add to dashboard Cite

This paper experimentally and numerically investigates the thermally grown oxide (TGO), lifetime, and stress values in thermal barrier coatings with different bond coat (BC), without top coat (TC), and diffusion coating under cyclic thermal loading. Scanning electron microscope (SEM) analysis shows that the atmospheric plasma spraying (APS) and high‐velocity oxygen fuel (HVOF) fabricated sample has the highest and lowest TGO thickness and growth rate, respectively. The new coating with two BCs has a maximum lifetime of 102 cycles. After that, the lifetime of the coatings with HVOF‐BC, diffusion coating, and APS‐BC reach 84, 56, and 44 cycles, respectively. The diffusion coating does not have much effect on the TGO thickness; however, it delays the Al interdiffusion to the substrate. In the sample without the TC layer, oxygen contact with the BC layer has increased, leading to a rise in the BC oxidation rate. The numerical analysis of the stress values based on SEM images shows that the more intense TGO layer growth in APS coating caused an increase in TC layer stress values. Furthermore, the results show that the new coating with two‐layer BC has the lowest stress values. The TC absence causes the loss of compressive stresses caused by TC on TGO and increases the tensile stress values in this layer.

show abstract

“…Main CO 2 studies cover the application of various heat exchange intensifiers [15] or analysis of gas dynamic properties of the working fluid in inter-blade baffles of the carbon dioxide turbine [16]. There are many papers on the study of various topologies of convective blade cooling systems, but air [17,18]or steam is considered as a refrigerant [19,20].…”

Section: Introductionmentioning

confidence: 99%

Development and Research of the Topology of Cooling Baffles for Blades of the Axial Carbon Dioxide Turbines

Komarov¹

2022

Eurasian phys. tech. j.

View full text Add to dashboard Cite

Currently, there is an increase in average annual temperature and climate change across the various continents. Carbon dioxide emissions from energy facilities contributed to this condition. Implementation of oxy-fuel cycles is a promising solution for reducing carbon dioxide emissions from the energy sector. To date, the most efficient oxy-fuel cycle is the Allam cycle. In this cycle supercritical carbon dioxide acts as a working fluid of the cycle, wherein СО2’s temperature upstream of the turbine is 1,150 °С and the pressure is 30 MPa. Due to the high temperature of the working fluid, it is necessary to cool first stages of the carbon dioxide turbine. The feature of considered cooling system in this turbine is that carbon dioxide being used as a refrigerant too. This paper investigated two topologies of convective cooling systems in the carbon dioxide turbine’s nozzle blade as well as considers an option for increasing the intensity of heatexchange through the use of helical ribbing in the cylindrical cooling baffle. Numerical simulation involving the ANSYS software package was performed for two topologies of the cooling baffles arrangement in the nozzle blade body: configuration 1 -with 17 baffles of 1 mm diameter, configuration 2 -with three baffles of the blade profile shape. Configuration 1 proved to be more efficient: the Nusselt number has a value of 117, and average value of the heat transfer coefficient on the refrigerant side is 6,413 W/m2∙K. The effect of using helical ribbing in the cooling cylindrical baffle of the blade under study was investigated, which enabled to reduce the metal temperature by 54 °С on average and doubled the heat transfer coefficient.

show abstract

Stress analysis of a second stage gas turbine blade under asymmetric thermal gradient

Cited by 9 publications

References 15 publications

Analytical and Experimental Study of Residual Stresses in Thermal Barrier Coatings Deposited on Gas Turbine Blades in Laboratory Dimensions by APS and HVOF Methods to Calculate the Optimal Thickness

Analytical and Experimental Study of Residual Stresses in Thermal Barrier Coatings Deposited on Gas Turbine Blades in Laboratory Dimensions by APS and HVOF Methods to Calculate the Optimal Thickness

Experimental and numerical life evaluation of TBCs with different BC and diffusion coating under cyclic thermal loading

Development and Research of the Topology of Cooling Baffles for Blades of the Axial Carbon Dioxide Turbines

Contact Info

Product

Resources

About