Thermal Analysis of Functional Gradient Materials as Thermal Barrier Coating of Piston

2008 ◽  
Author(s):  
Shuangsong Du ◽  
Xianguo Hu ◽  
Yijian Feng ◽  
Jigui Cheng
Keyword(s):  
Thermal Analysis ◽  
Thermal Barrier Coating ◽  
Thermal Barrier ◽  
Gradient Materials ◽  
Functional Gradient ◽  
Barrier Coating

Thermal Analysis in a Film Cooling Hole with Thermal Barrier Coating

2009 ◽  
Vol 23 (4) ◽  
pp. 843-847 ◽  
Author(s):  
Dong Hyun Lee ◽  
Kyung Min Kim ◽  
Sangwoo Shin ◽  
Hyung Hee Cho
Keyword(s):  
Thermal Analysis ◽  
Thermal Barrier Coating ◽  
Film Cooling ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Cooling Hole

scholarly journals An Advanced BEM for Thermal and Stress Analyses of Components with Thermal Barrier Coating

2007 ◽  
Vol 1 (2) ◽  
Author(s):  
Shan Lu ◽  
Menhong Dong
Keyword(s):  
Thermal Analysis ◽  
Stress Analysis ◽  
Thermal Barrier Coating ◽  
Singular Integrals ◽  
Layer Structure ◽  
Interfacial Stress ◽  
Thin Body ◽  
Thermal Barrier ◽  
Barrier Coating ◽  
Stress Analyses

An advanced boundary element method (BEM) for 2-D steady-state thermal analysis of components with thermal barrier coating (TBC) is presented in this paper. First, a scheme of evaluating the nearly singular integrals in stress analysis of a thin body was extended to the thermal analysis of components with TBC. Then the BEM formulation for thermal analysis of multi-layered structures was developed. Next, an advanced BEM was developed for 2-D interfacial stress analysis of components with TBC. The non-linear transformation scheme in stress analysis of thinbody under traction load by BEM was extended to evaluate the nearly singular integral in BEM for thermal and centrifugal stress analysis. Then BEM formulation for multi-layer structure under thermal, centrifugal and traction loads was presented. Several numerical examples of 2-D thermal analyses and interfacial stress analyses of components with TBC were analyzed with only 32 boundary elements. The accurate numerical results can be obtained even when the ratio of the coating thickness to element length approached 10 9 − . The maximum relative percentage errors of interfacial tangent tension stresses under a complex temperature field, traction and centrifugal loads were 0.08%, 0.13% and 0.23%, respectively,. The present BEM will be an efficient tool for TBC design and TBC peeling-failure analysis.

Steady State Thermal Analysis of an Afterburner Liner

2013 ◽  
Author(s):  
Suresh Batchu ◽  
S. Kishore Kumar
Keyword(s):  
Thermal Analysis ◽  
Steady State ◽  
Thermal Barrier Coating ◽  
Metal Temperature ◽  
Thermal Barrier ◽  
Thermal Loads ◽  
Gas Temperature ◽  
Barrier Coating ◽  
Aero Engine ◽  
Engine Testing

Military aero engines employ afterburner system for increasing the reheat thrust required during combat and takeoff. During reheat the gas temperature in the afterburner is of the order of 2100K.The afterburner liner has to be cooled with the available bypass air to maintain metal temperature within allowable limits. The liner has cooling rings at the rear to cool the liner with tangential film cooling. This paper discusses the methodology of afterburner liner metal temperature prediction and comparison with measured metal temperature during aero engine testing at reheat condition. All the modes of heat transfer are considered for thermal analysis, radiation due to higher level of gas temperature during reheat, conduction due to presence of low conductivity thermal barrier coating and convection due to higher gas velocities are considered. At different steady state reheat conditions metal temperature are predicted and compared with measured data during aero engine testing. The predicted skin temperatures and measured temperatures are in good agreement. Empirical correlations are used for estimating the heat loads coming on the liner and adiabatic film temperature near screech holes and cooling rings. Metal temperature and thermal loads coming onto the liner are predicted with 1D code. The estimated thermal loads are applied on 3D FE model to obtain nodal temperature distribution. The thermal Analysis is carried using ANSYS software in which thermal barrier coating is also modeled. The parameters like gas temperature, thermal barrier coating thickness, coating conductivity, and coolant mass flow distribution are considered for carrying out a sensitivity analysis of liner metal temperature.

Time Dependent High Dimension Model of Functional Gradient Thermal Barrier Coating Material

2016 ◽  
Vol 705 ◽  
pp. 263-267
Author(s):  
Chen Zhao ◽  
Yu Guang Li ◽  
She Sheng Zhang
Keyword(s):  
Thermal Barrier Coating ◽  
High Dimension ◽  
Volume Fraction ◽  
Optimization Theory ◽  
Coating Material ◽  
Time Dependent ◽  
Thermal Barrier ◽  
Functional Gradient ◽  
Barrier Coating ◽  
Inverse Heat Transfer

A high dimension time dependent model of designing functional gradient thermal barrier coating material is built by using optimization theory. The difference algorithms is used to solve inverse heat transfer problems. The heat conduction coefficient is founded by using volume fraction function of ceramic or metal. An example of calculation shows that the gradient thermal barrier coating can improve material function.

HOT CORROSION OF CERIA-YTTRIA STABILIZED ZIRCONIA PLASMA SPRAYED THERMAL BARRIER COATING BY EUTECTIC VANDIUM PENTAOXIDE-SODIUM SULFATE

2018 ◽  
Vol 18 (1) ◽  
pp. 182-192 ◽  
Author(s):  
Mohammed J Kadhim ◽  
Mohammed H Hafiz ◽  
Maryam A Ali Bash
Keyword(s):  
Thermal Barrier Coating ◽  
Hot Corrosion ◽  
Monoclinic Phase ◽  
Volume Fraction ◽  
High Volume ◽  
Thermal Barrier ◽  
Air Plasma ◽  
Plan View ◽  
Barrier Coating ◽  
Plasma Sprayed

The high temperature corrosion behavior of thermal barrier coating (TBC) systemconsisting of IN-738 LC superalloy substrate, air plasma sprayed Ni24.5Cr6Al0.4Y (wt%)bond coat and air plasma sprayed ZrO2-20 wt% ceria-3.6 wt% yttria (CYSZ) ceramic coatwere characterized. The upper surfaces of CYSZ covered with 30 mg/cm2 , mixed 45 wt%Na2SO4-55 wt% V2O5 salt were exposed at different temperatures from 800 to 1000 oC andinteraction times from 1 up to 8 h. The upper surface plan view of the coatings wereidentified for topography, roughness, chemical composition, phases and reaction productsusing scanning electron microscopy, energy dispersive spectroscopy, talysurf, and X-raydiffraction. XRD analyses of the plasma sprayed coatings after hot corrosion confirmed thephase transformation of nontransformable tetragonal (t') into monoclinic phase, presence ofYVO4 and CeVO4 products. Analysis of the hot corrosion CYSZ coating confirmed theformation of high volume fraction of YVO4, with low volume fractions of CeOV4 and CeO2.The formation of these compounds were combined with formation of monoclinic phase (m)from transformation of nontransformable tetragonal phase (t').

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