Crack Initiation Strength of Thermal Barrier Coating Layer under Thermal Shock.

Abstract Thermal barrier coatings are used in the aerospace industry for thermal insulation in hot sections of gas turbines. Improved coating reliability is a common goal among jet engine designers. In-service failures, such as coating cracking and spallation, result in decreased engine performance and costly maintenance time. A research program was conducted to evaluate residual stresses, microstructure, and thermal shock life of thermal barrier coatings produced from different powder types and spray parameters. Sixteen coatings were ranked according to their performance relative to the other coatings in each evaluation category. Comparisons of residual stresses, powder morphology, and microstructure to thermal shock life indicate a strong correlation to thermal barrier coating performance. Results from these evaluations will aid in the selection of an optimum thermal barrier coating system for turbine engine applications.

Download Full-text

Development of a Laser Heating Method for Evaluating Thermal Shock/Fatigue Resistance of Ceramic Thermal Barrier Coating for Gas Turbine Blade.

TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series A ◽

10.1299/kikaia.58.15 ◽

1992 ◽

Vol 58 (545) ◽

pp. 15-19 ◽

Cited By ~ 3

Author(s):

Toshiyuki HASHIDA ◽

Tsuyoshi ISHIKAWA ◽

Tsutomu TOBE ◽

Hideaki TAKAHASHI

Keyword(s):

Thermal Shock ◽

Gas Turbine ◽

Thermal Barrier Coating ◽

Turbine Blade ◽

Fatigue Resistance ◽

Laser Heating ◽

Thermal Barrier ◽

Gas Turbine Blade ◽

Heating Method ◽

Barrier Coating

Download Full-text

Effects of interface roughness on the life estimation of a thermal barrier coating layer

International Journal of Surface Science and Engineering ◽

10.1504/ijsurfse.2013.056438 ◽

2013 ◽

Vol 7 (3) ◽

pp. 269 ◽

Cited By ~ 5

Author(s):

R. Ragupathy ◽

S.K. Panigrahi ◽

R.K. Mishra

Keyword(s):

Thermal Barrier Coating ◽

Coating Layer ◽

Interface Roughness ◽

Thermal Barrier ◽

Life Estimation ◽

Barrier Coating

Download Full-text

Study on Thermal Shock Resistance of Nano-CeO2–Y2O3 Co-Stabilized ZrO2 (CYSZ) Ceramic Powders Thermal Barrier Coating of Aircraft Engine

Journal of Nanoelectronics and Optoelectronics ◽

10.1166/jno.2019.2712 ◽

2019 ◽

Vol 14 (11) ◽

pp. 1597-1605

Author(s):

Yang Lyu ◽

Xuan Shao ◽

Wen-Xue Wang ◽

Hui Tang

Keyword(s):

Thermal Shock ◽

Thermal Barrier Coating ◽

Thermal Shock Resistance ◽

Ceramic Coatings ◽

Precipitation Method ◽

Thermal Barrier ◽

Ceramic Powders ◽

Alloy Matrix ◽

Barrier Coating ◽

Shock Resistance

In this paper, nano-CeO2–Y2O3 co-stabilized ZrO2 ceramic powders (CYSZ) were firstly prepared by co-precipitation method, and CYSZ powder was spray-granulated, followed by thermal plasma spraying of nano-CYSZ thermal barrier coating on 35Cr2Ni4 MoA alloy matrix. After XRD and SEM analysis, the five CYSZ ceramic coatings (CeO2 content 0, 1, 5, 10, 15 mol%) prepared were tetragonal phase structures before and after the thermal shock experiment, and the thickness of CYSZ ceramic coating was about 200 μm. Adding appropriate amount of nano CeO2 promoted the formation of micro-cracks in the coating, released the coating stress, slowed down the thermal shock damage process, and prevented the transformation from t-ZrO2 to m-ZrO2. The AFM morphology showed that the coating surface grains grow vertically after thermal shock cycle, which indicated that the entry of Ce4+ into ZrO2 lattice resulted in lattice distortion and made the grains more stable. When the content of CeO2 is 1 mol%, the thermal shock resistance excellent is 84 times. Therefore, the addition of CeO2 can effectively improve the thermal shock resistance performance of CYSZ thermal barrier coating, meeting the requirements of high temperature working conditions of aeroengine and hot-end components.

Download Full-text