Failure Mode of Thermal Barrier Coatings for Gas Turbine Vanes Under Bending

2000 ◽  
Vol 17 (1) ◽  
pp. 1-24 ◽  
Author(s):  
Ashok Κ. Ray
Keyword(s):  
Gas Turbine ◽  
Failure Mode ◽  
Thermal Barrier Coatings ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Turbine Vanes

Field Evaluation of 2CaO-SiO2-CaO-ZrO2 Thermal Barrier Coating on Gas Turbine Vanes

1997 ◽  
Author(s):  
N. Mifune ◽  
Y. Harada ◽  
H. Taira ◽  
S. Mishima
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Thermal Barrier Coatings ◽  
Field Evaluation ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Thermal Change ◽  
Barrier Coating ◽  
Turbine Vanes ◽  
Higher Temperature

Abstract Higher-temperature operation in a gas turbine has urged development of heat-resistant coatings and thermal barrier coatings. We have developed a 2CaO-SiO2-CaO-ZrO2 based thermal barrier coating. This coating should effectively prevent separation of the coating by relieving the shear stress generated due to thermal change of environment between layers with dissimilar properties. The coating was applied to stationary vanes of an actual gas turbine in a 25,000-hour test. This paper describes the results of the field test.

scholarly journals Analysis of the energetic/environmental performances of gas turbine plant: Effect of thermal barrier coatings and mass of cooling air

2009 ◽  
Vol 13 (1) ◽  
pp. 147-164 ◽  
Author(s):  
Ion Ion ◽  
Anibal Portinha ◽  
Jorge Martins ◽  
Vasco Teixeira ◽  
Joaquim Carneiro
Keyword(s):  
Thermal Conductivity ◽  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Turbine Blades ◽  
Heat Transfer Analysis ◽  
Thermal Barrier ◽  
Inlet Temperature ◽  
Barrier Coatings ◽  
Cooling Air Flow ◽  
Cooling Air

Zirconia stabilized with 8 wt.% Y2O3 is the most common material to be applied in thermal barrier coatings owing to its excellent properties: low thermal conductivity, high toughness and thermal expansion coefficient as ceramic material. Calculation has been made to evaluate the gains of thermal barrier coatings applied on gas turbine blades. The study considers a top ceramic coating Zirconia stabilized with 8 wt.% Y2O3 on a NiCoCrAlY bond coat and Inconel 738LC as substrate. For different thickness and different cooling air flow rates, a thermodynamic analysis has been performed and pollutants emissions (CO, NOx) have been estimated to analyze the effect of rising the gas inlet temperature. The effect of thickness and thermal conductivity of top coating and the mass flow rate of cooling air have been analyzed. The model for heat transfer analysis gives the temperature reduction through the wall blade for the considered conditions and the results presented in this contribution are restricted to a two considered limits: (1) maximum allowable temperature for top layer (1200?C) and (2) for blade material (1000?C). The model can be used to analyze other materials that support higher temperatures helping in the development of new materials for thermal barrier coatings.

scholarly journals Thermal-barrier coatings for more efficient gas-turbine engines

MRS Bulletin ◽  
2012 ◽  
Vol 37 (10) ◽  
pp. 891-898 ◽  
Author(s):  
David R. Clarke ◽  
Matthias Oechsner ◽  
Nitin P. Padture
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Image Position

Abstract

scholarly journals Failure Analysis of Multilayered Suspension Plasma-Sprayed Thermal Barrier Coatings for Gas Turbine Applications

2018 ◽  
Vol 27 (3) ◽  
pp. 402-411 ◽  
Author(s):  
M. Gupta ◽  
N. Markocsan ◽  
R. Rocchio-Heller ◽  
J. Liu ◽  
X.-H. Li ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Plasma Sprayed

Next Generation Thermal Barrier Coatings for the Gas Turbine Industry

2010 ◽  
Vol 20 (1-2) ◽  
pp. 108-115 ◽  
Author(s):  
Nicholas Curry ◽  
Nicolaie Markocsan ◽  
Xin-Hai Li ◽  
Aurélien Tricoire ◽  
Mitch Dorfman
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Barrier ◽  
Next Generation ◽  
Barrier Coatings

scholarly journals Thermal Stress Mitigating Properties for Graded Thermal Barrier Coatings of Gas Turbine.

1995 ◽  
Vol 61 (583) ◽  
pp. 614-619 ◽  
Author(s):  
Yoshiyasu Itoh ◽  
Masashi Takahashi ◽  
Takanari Okamura ◽  
Masao Toyoda
Keyword(s):  
Thermal Stress ◽  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Barrier ◽  
Barrier Coatings

Development of Thermal Barrier Coatings for 1700℃-class Gas Turbine

2002 ◽  
Vol 2002.2 (0) ◽  
pp. 217-218
Author(s):  
Tohru HISAMATSU ◽  
Akito NITTA ◽  
Taiji TORIGOE ◽  
Tsuneji KAMEDA ◽  
Hideyuki ARIKAWA ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Barrier ◽  
Barrier Coatings

scholarly journals Impact of Cooling with Thermal Barrier Coatings on Flow Passage in a Gas Turbine

Energies ◽  
2021 ◽  
Vol 15 (1) ◽  
pp. 85
Author(s):  
Yuanzhe Zhang ◽  
Pei Liu ◽  
Zheng Li
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Thermal Barrier ◽  
Power Sources ◽  
Barrier Coatings ◽  
Flow Passage ◽  
Blade Cooling ◽  
The Impact

Inlet temperature is vital to the thermal efficiency of gas turbines, which is becoming increasingly important in the context of structural changes in power supplies with more intermittent renewable power sources. Blade cooling is a key method for gas turbines to maintain high inlet temperatures whilst also meeting material temperature limits. However, the implementation of blade cooling within a gas turbine—for instance, thermal barrier coatings (TBCs)—might also change its heat transfer characteristics and lead to challenges in calculating its internal temperature and thermal efficiency. Existing studies have mainly focused on the materials and mechanisms of TBCs and the impact of TBCs on turbine blades. However, these analyses are insufficient for measuring the overall impact of TBCs on turbines. In this study, the impact of TBC thickness on the performance of gas turbines is analyzed. An improved mathematical model for turbine flow passage is proposed, considering the impact of cooling with TBCs. This model has the function of analyzing the impact of TBCs on turbine geometry. By changing the TBCs’ thickness from 0.0005 m to 0.0013 m, its effects on turbine flow passage are quantitatively analyzed using the proposed model. The variation rules of the cooling air ratio, turbine inlet mass flow rate, and turbine flow passage structure within the range of 0.0005 m to 0.0013 m of TBC thicknesses are given.

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