scholarly journals Development of Evaluation Method for Damage of Oxidation CoNiCrAlY Coating

2019 ◽  
Vol 804 ◽  
pp. 47-51
Author(s):  
Mo Chen ◽  
Kodai Yoshikawa ◽  
Zhen Qiang Song ◽  
Shijie Zhu
Keyword(s):  
Cross Sections ◽  
Gas Turbines ◽  
Evaluation Method ◽  
Thermal Spraying ◽  
Optical Microscope ◽  
Thermally Grown Oxide ◽  
Interfacial Damage ◽  
Barrier Coating ◽  
Plasma Sprayed ◽  
Conicraly Coating

The bond coat plays an important role in the failure of the thermal barrier coating (TBC) system used for gas turbines [1,2]. In this research, the CoNiCrAlY coated Ni-base superalloy specimens were used for developing evaluation method for interfacial damage in the coat. Samples were exposed at 1000°C and 1100°C for up to 1000 hours. The morphology and residual stress in the thermally grown oxide (TGO) layer on the CoNiCrAlY coating were characterized by microscopic observation and luminescence spectroscope, respectively. The microstructure and damage o\n both the coating surfaces and the cross sections were observed by optical microscope and scanning electron microscope. According to the results, the low pressure plasma sprayed CoNiCrAlY coating (LPPS) showed the thinnest TGO layer and lowest residual stress.Residual stress decreased with an increase in exposure time, depending on the morphology of TGO layer. The effects of thermal spraying methods on the oxidation of yttrium in TGO layer and BC layer and its influence on interfacial damage were discussed.

The High Temperature Creep Properties of a Thermally Sprayed CoNiCrAlY Coating via Small Punch Creep Testing

2017 ◽  
Vol 734 ◽  
pp. 37-48 ◽  
Author(s):  
G.A. Jackson ◽  
Hao Chen ◽  
Wei Sun ◽  
D. Graham McCartney
Keyword(s):  
Bond Coat ◽  
Gas Turbines ◽  
Creep Behaviour ◽  
Thermal Spraying ◽  
Thermally Grown Oxide ◽  
Creep Properties ◽  
Small Punch ◽  
Hvof Thermal Spraying ◽  
Conicraly Coating ◽  
Thermally Sprayed

Thermal barrier coatings (TBC’s) protect superalloy components from excessively high temperatures in gas turbines. TBC’s comprise of a ceramic top coat, a metallic bond coat and a thermally grown oxide (TGO). The creep behaviour of the MCrAlY bond coat, which is sensitive to the composition and the method of deposition, has a significant effect on the life of the TBC. High velocity oxy-fuel (HVOF) thermal spraying is a popular deposition method for MCrAlY bond coats however the creep properties of HVOF MCrAlY coatings are not well documented. The creep behaviour of a HVOF thermally sprayed CoNiCrAlY coating has been determined by small punch creep (SPC) testing. Tests were conducted between an equivalent uniaxial stress range of 37-80 MPa at 750 °C on two different SPC rigs and between 30-49 MPa at 850 °C on a single SPC rig. The measured steady-state creep deformation rates at 750 °C were consistent across the two rigs. A comparison with previous work demonstrated that the creep behaviour of HVOF CoNiCrAlY coatings is not sensitive to the manufacturing variability associated with HVOF thermal spraying. The CoNiCrAlY coating exhibited typical SPC deformation at 750 °C. At 850 °C the CoNiCrAlY coating showed significantly different creep behaviour which could be attributed to the onset of superplasticity.

R&D Status and Needs for Improved EB-PVD Thermal Barrier Coating Performance

2000 ◽  
Vol 645 ◽  
Author(s):  
C. Leyens ◽  
U. Schulz ◽  
M. Bartsch ◽  
M. Peters
Keyword(s):  
Thermal Barrier Coating ◽  
Bond Coat ◽  
Gas Turbines ◽  
Systems Approach ◽  
Thermally Grown Oxide ◽  
Thermal Barrier ◽  
Factors Affecting ◽  
Performance Improvements ◽  
Barrier Coating ◽  
Temperature Capability

ABSTRACTThe key issues for thermal barrier coating development are high temperature capability and durability under thermal cyclic conditions as experienced in the hot section of gas turbines. Due to the complexity of the system and the interaction of the constituents, performance improvements require a systems approach. However, there are issues closely related to the ceramic top coating and the bond coat, respectively. Reduced thermal conductivity, sintering, and stresses within the ceramic coating are addressed in the paper as well as factors affecting failure of the TBC by spallation. The latter is primarily governed by the formation and growth of the thermally grown oxide scale and therefore related to the bond coat. A strategy for lifetime assessment of TBCs is discussed.

Development of a Thermal Barrier Coating Life Model

2003 ◽  
Author(s):  
K. Chan ◽  
S. Cheruvu ◽  
R. Viswanathan
Keyword(s):  
Gas Turbine ◽  
Bond Coat ◽  
Thermally Grown Oxide ◽  
Experimental Program ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Life Model ◽  
Useful Life ◽  
Plasma Sprayed ◽  
Kinetics Of

Thermal barrier coatings (TBCs) are widely used on the first stage turbine buckets and vanes of land-based (F and G class) gas turbine machines. These coatings normally fail by spallation due to delamination of the ceramic layer along the vicinity of the thermally grown oxide (TGO)/TBC interface. The failure processes involve several mechanisms including oxidation of the bond coat, thermomechanical fatigue, sintering, and spallation of the TBC. This paper describes the development of an analytical tool for predicting the useful life of TBCs for land-based gas turbine applications. The analytical model, called TBCLIFE, has been developed to treat bond coat oxidation, sintering and spallation of the TBC, as well as effects of coating thickness and substrate curvature on TBC spallation. In addition, a parallel experimental program has also been initiated to evaluate the durability of a plasma-sprayed TBC under isothermal and thermal cycling exposures. These results will be used to determine the kinetics of TGO scale growth and the material constants for the TBC life model. The TBC life model will be applied to predicting TBC life as a function of cycle time and the results will be presented as coating life diagrams. The utility of a coating life diagram for estimating the remaining life of TBC will be illustrated and discussed.

Damage mechanisms and lifetime behavior of plasma-sprayed thermal barrier coating systems for gas turbines — Part II: Modeling

2008 ◽  
Vol 202 (24) ◽  
pp. 5901-5908 ◽  
Author(s):  
Tilmann Beck ◽  
Roland Herzog ◽  
Olena Trunova ◽  
Marita Offermann ◽  
Rolf W. Steinbrech ◽  
...  
Keyword(s):  
Thermal Barrier Coating ◽  
Gas Turbines ◽  
Thermal Barrier ◽  
Damage Mechanisms ◽  
Barrier Coating ◽  
Plasma Sprayed

Research on the Stability of Thermal Barrier Coatings under Thermal Cyclic Loading

2017 ◽  
Vol 730 ◽  
pp. 75-80 ◽  
Author(s):  
Jian Sun ◽  
Ying Qiang Xu ◽  
Wan Zhong Li ◽  
Kai Lv
Keyword(s):  
Cyclic Loading ◽  
Stress Field ◽  
Evaluation Method ◽  
Thermally Grown Oxide ◽  
Interfacial Stress ◽  
Thermal Barrier ◽  
Fea Model ◽  
Barrier Coating ◽  
The Stability ◽  
Evolution Behavior

Thermal barrier coating systems (TBCs) are widely used in turbines. However, premature failures have impaired the use of TBCs and cut down their lifetime. The thermally grown oxide layer (TGO) thickening and the material thermal expansion misfit under thermal cyclic loading significantly affect the interfacial stress field and stability of TBCs. In this study, the stability evaluation method of TBCs under thermal cyclic loading based on energy is established using the visco-elastoplastic and shakedown theorem. The semicircular shape interface is used to simplify the complicated interfacial undulations in FEA model. And actual TGO thickness obtained from experiment is used to simulate the bond coat oxidation. Then the effect of TGO thickening on the stability and stress field of TBCs under thermal cyclic loading is analyzed through the numerical simulation. It is concluded that estimating from the stress-strain evolution behavior, the local stability of the TBCs decreases with the TGO thickening, and assessing from energy, TBCs shows instable with TGO thickening.

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