Experimental and computational analysis of thermo‐oxidative‐structural stability of ZrB2–SiC–Ti during arc‐jet testing

Journal of the American Ceramic Society - Tập 100 Số 10 - Trang 4860-4873 - 2017
Anupam Purwar1, T. Venkateswaran2, Bikramjit Basu3
1Centre of Excellence in Hypersonics, Indian Institute of Science, Bangalore, India
2Materials and Metallurgy Group, Vikram Sarabhai Space Centre, Trivandrum, India
3Materials Research Centre, Indian Institute of Science, Bangalore, India

Tóm tắt

Abstract

The development of new ultra‐high temperature ceramics for thermal protection system (TPS) of hypersonic cruise and re‐entry vehicles requires performance‐qualification testing under simulated flight conditions. The present work, encompassing experiments and computational analysis, critically analyzes the thermo‐oxidative‐structural stability of flat surface disks of spark plasma sintered ZrB2–18SiC–xTi composites (x=0, 10, 20; composition in wt%) under arc jet flow with heat flux of 2.5 MW/m2 for 30 seconds. Such testing conditions effectively simulate the aero‐thermal environment in ground facility, as experienced by hypersonic vehicles. Based on the extensive XRD, SEM‐EDS and electron probe microanalyzer based analysis of the surface/sub‐surface of arc jet exposed ceramics, the oxidation mechanisms are qualitatively discussed. Importantly, thick oxide layers (~400‐950 μm) were found to be adherent, thereby providing good structural stability of such ceramics for reusable TPS. The careful finite element (FE) analysis with high quality structural elements, being generated using HyperMesh, was conducted to understand the underlying reasons for observed oxidation. Such analysis allows us to determine the temporal evolution of through‐thickness temperature distribution. FE‐based calculations were subsequently validated using experimentally measured backwall temperatures. The thermodynamic feasibility of competing oxidation reactions at the analytically computed front wall temperatures was thereafter realistically assessed to support the oxidation mechanisms. Taken together, the present work provides guidelines for better understanding of the thermo‐oxidative‐structural stability of ceramics under arc jet testing and also establishes the good stability of ZrB2–18SiC–20Ti composites for potential application in TPS of hypersonic space vehicles.

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Tài liệu tham khảo

2017 Springer Singapore A Purwar Thermo‐Structural Design of Strut Based Flame Holder for Scramjet Combustor Smart Innovation Systems and Technologies

UpadhyaK YangJ HoffmanW.Advanced materials for ultra high temperature structural applications above 2000°C.1997. Accessed in 4 2016.

10.1016/S0955-2219(02)00140-1

10.1021/jp505941g

10.2109/jcersj2.15260

10.1016/j.ijrmhm.2006.04.006

10.1016/j.msea.2011.11.048

10.1016/j.compscitech.2008.02.009

10.1111/j.1551-2916.2012.05226.x

10.1016/j.jeurceramsoc.2007.02.201

10.2174/1874146001003020020

10.1016/j.jeurceramsoc.2010.01.029

Chamberlain A, 2005, Oxidation of ZrB2–SiC ceramics under atmospheric and reentry conditions, Refractories Applications Transactions, 1, 1

10.1023/B:JMSC.0000041693.32531.d1

GagnonS.The Element Titanium.http://education.jlab.org/itselemental/ele022.html. Accessed in September 2015.

10.1023/A:1025681432260

NIST‐JANAF Thermochemical Tables.http://kinetics.nist.gov/janaf/. Accessed in 9 2016.

SiC ‐ Silicon Carbide Thermal properties.http://www.ioffe.ru/SVA/NSM/Semicond/SiC/thermal.html. Accessed in March 2015.

10.1111/j.1551-2916.2008.02268.x

10.1039/C5CP00129C

10.1016/j.net.2015.05.003

SiO2properties AZOM.http://www.azom.com/properties.aspx?ArticleID=1114. Accessed in October 2016.

ZrO2Properties AZOM.http://www.azom.com/properties.aspx?ArticleID=133. Accessed in October 2016.

10.1111/jace.14750

10.1016/j.ceramint.2011.08.003

10.1201/9781482273410

10.1016/j.jeurceramsoc.2007.12.040

10.3891/acta.chem.scand.12-0239

10.1149/1.2427248

Khanna AS, 2002, Introduction to High Temperature Oxidation and Corrosion

10.1007/s11167-005-0040-6

10.1016/j.corsci.2009.07.005

10.1016/j.solidstatesciences.2010.12.022

10.1016/j.ceramint.2014.06.064

2017 Springer International Publishing New York NY A Purwar DR Mahapatra A methodology for coupled thermal structural analysis and structural design of scramjet. 30th International Symposium on Shock Waves (ISSW30)

10.1016/j.jeurceramsoc.2010.02.014

10.1002/9781118037300

10.1016/j.jeurceramsoc.2011.08.004

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Journal of the American Ceramic Society

Tập 100 Số 10

4860-4873

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