Two-Dimensional Thermal Performance Analysis of a Semi-Transparent Spectral Zirconia Thermal Barrier Coating

2004 ◽  
Author(s):  
Nalini Uppu ◽  
Patrick F. Mensah ◽  
Ravinder Diwan
Keyword(s):  
Heat Transfer ◽  
Thermal Barrier Coating ◽  
Thermal Performance ◽  
Operating Temperature ◽  
Turbine Blades ◽  
The Other ◽  
Ceramic Layer ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Super Alloy

The performance of an aero engine can be increased in two ways: one by reducing the air requirement for the cooling of the turbine blades and secondly by increasing the turbine inlet temperature (TIT) that is operating temperature of the turbine blades. Taking into account the latter approach the blade material must withstand high temperatures of above 1350°C. For this enhancing purpose, protective coatings called the thermal barrier coatings (TBC) are being employed. The thermal barrier coating mainly consists of two layers; one is the metallic coating MCrAlY, which is the premiere layer over the substrate Ni based super alloy. The other is the ceramic layer made of Yttria Stabilized Zirconia (YSZ). Apart from these two layers, an intermediate layer of Al2O3 is formed by the oxidation of the aluminum in MCrAlY called the diffusion layer which also enhances the adhesion between the two layers. M stands for Nickel or Cobalt. The present study is an investigation on the in-situ thermal performance of TBCs by considering the ceramic layer as a semi-transparent media and varying its thickness and simultaneously increasing the operating temperature on its other boundary surface. The above thermal boundary value problem is modeled in 2-dimensions and solved numerically using the discrete ordinate model for radiative heat transfer in a commercial computational fluid dynamics and heat transfer software. Two samples of Ni based super alloy substrate with dimensions 40 × 100 × 3mm are considered; one sample with a thickness of 0.25 mm ceramic layer and the other sample with 1 mm coating thickness for transient thermal analysis. Simulated transient temperature histories are presented for use in a thermo-mechanical analysis in order to predict the failure modes in the TBC. The temperature distribution in TBC coating mainly depends on the radiative effects combined with heat conduction and convection and radiation at the material boundaries.

scholarly journals Stress and Displacement Distribution of the Thermal Barrier Coatings in the Turbine Engine Combustion Chamber

Coatings ◽  
2020 ◽  
Vol 10 (9) ◽  
pp. 842
Author(s):  
Jianxin Wang ◽  
Zhenzhe Li ◽  
Fengxun Li
Keyword(s):  
Combustion Chamber ◽  
Thermal Barrier Coating ◽  
Thermal Barrier Coatings ◽  
Operating Temperature ◽  
Turbine Blades ◽  
Thermally Grown Oxide ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Barrier Coating ◽  
Thermally Grown

A thermal barrier coating forms a high temperature resistant metal by the spraying of ceramics or other materials. Thermal barrier coatings are mainly used in the aviation field because they can significantly improve the thermal resistance of the aircraft engine turbine blades, combustion chamber and the other hot parts. In this paper, a thermal barrier coating model of the combustion chamber is established by using the finite element method. The stress field and displacement field of thermal barrier coatings under different thicknesses of the thermally grown oxide layer and thermal barrier coating layer, and the maximum operating temperature were studied. The results show that stress and deformation under the three thermal cycles increase with the increase in operating temperature and the thickness of thermally grown oxide (TGO) and thermal barrier coat (TBC), except for the case of TGO thickness of 2 μm.

Optimized Thermal Barrier Coating for Gas Turbine Blades

2019 ◽  
Vol 11 ◽  
pp. 912-919 ◽  
Author(s):  
Vishnu Sankar ◽  
PB. Ramkumar ◽  
Deepak Sebastian ◽  
Doyel Joseph ◽  
Jithu Jose ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Turbine Blades ◽  
Thermal Barrier ◽  
Gas Turbine Blades ◽  
Barrier Coating

Preliminary Testing of Metal-Based Thermal Barrier Coating in a Spark-Ignition Engine

2009 ◽  
Author(s):  
Michael Marr ◽  
James S. Wallace ◽  
Larry Pershin ◽  
Sanjeev Chandra ◽  
Javad Mostaghimi
Keyword(s):  
Heat Transfer ◽  
Thermal Barrier Coating ◽  
Substrate Surface ◽  
Temperature Fluctuations ◽  
Spark Ignition ◽  
Spark Ignition Engine ◽  
Thermal Barrier ◽  
Cylinder Wall ◽  
Test Results ◽  
Barrier Coating

A novel metal-based thermal barrier coating was tested in a spark-ignition engine. The coating was applied to the surface of aluminum plugs and exposed to in-cylinder conditions through ports in the cylinder wall. Temperatures were measured directly behind the coating and within the plug 3 and 11 mm from the surface. In-cylinder pressures were measured and analyzed to identify and quantify knock. Test results suggest the coating does not significantly reduce overall heat transfer, but it does reduce the magnitude of temperature fluctuations at the substrate surface. It was found that heat transfer can be reduced by reducing the surface roughness of the coating. The presence of the coating did not promote knock.

scholarly journals Investigation of Cooling Performances of a Non-Film-Cooled Turbine Vane Coated with a Thermal Barrier Coating Using Conjugate Heat Transfer

Energies ◽  
2018 ◽  
Vol 11 (4) ◽  
pp. 1000 ◽  
Author(s):  
Prasert Prapamonthon ◽  
Soemsak Yooyen ◽  
Suwin Sleesongsom ◽  
Daniele Dipasquale ◽  
Huazhao Xu ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Thermal Barrier Coating ◽  
Conjugate Heat Transfer ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Turbine Vane

Thermal Shock Experiment and Simulation of Ceramic/Metal Gradient Thermal Barrier Coating

2007 ◽  
Vol 336-338 ◽  
pp. 1818-1822
Author(s):  
Jin Sheng Xiao ◽  
Kun Liu ◽  
Wen Hua Zhao ◽  
Wei Biao Fu
Keyword(s):  
Heat Transfer ◽  
Thermal Shock ◽  
Thermal Barrier Coating ◽  
Thermal Stresses ◽  
Initial Temperature ◽  
Thermal Barrier ◽  
Water Spray ◽  
Barrier Coating ◽  
Shock Experiment ◽  
Two Stages

A thermal shock experiment is designed to explore the thermal shock properties of ceramic/metal gradient thermal barrier coating. The specimens are heated up by oxygen-acetylene flame and cooled by water spray. The experiment procedure includes two stages, heating the specimen from the initial temperature 30°C for 40s, and then cooling for 20s. The heat transfer and the associated thermal stresses produced during the thermal shock procedure are simulated by finite element method. Experimental results indicated that the specimen of gradient coating behaves better in thermal shock experiments, which agree with the results of simulation.

Preliminary Testing of Metal-Based Thermal Barrier Coating in a Spark-Ignition Engine

2010 ◽  
Vol 132 (7) ◽  
Author(s):  
Michael A. Marr ◽  
James S. Wallace ◽  
Larry Pershin ◽  
Sanjeev Chandra ◽  
Javad Mostaghimi
Keyword(s):  
Heat Transfer ◽  
Thermal Barrier Coating ◽  
Substrate Surface ◽  
Temperature Fluctuations ◽  
Spark Ignition ◽  
Spark Ignition Engine ◽  
Thermal Barrier ◽  
Cylinder Wall ◽  
Test Results ◽  
Barrier Coating

A novel metal-based thermal barrier coating was tested in a spark-ignition engine. The coating was applied to the surface of aluminum plugs and exposed to in-cylinder conditions through ports in the cylinder wall. Temperatures were measured directly behind the coating and within the plug 3 and 11 mm from the surface. In-cylinder pressures were measured and analyzed to identify and quantify knock. Test results suggest the coating does not significantly reduce overall heat transfer, but it does reduce the magnitude of temperature fluctuations at the substrate surface. It was found that heat transfer can be reduced by reducing the surface roughness of the coating. The presence of the coating did not promote knock.

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