Characterization and ablation resistance of ZrB2-xSiC gradient coatings deposited with HPPS

2020 ◽  
Vol 46 (10) ◽  
pp. 14756-14766 ◽  
Author(s):  
Yixin Bai ◽  
Quansheng Wang ◽  
Zhuang Ma ◽  
Yanbo Liu ◽  
Haikun Chen ◽  
...  
Keyword(s):  
Ablation Resistance ◽  
Gradient Coatings

Technology for the production of nanostructured coatings from nanoparticles of tungsten carbide and metal chromium

2020 ◽  
pp. 117-124
Author(s):  
T. I. Bobkova ◽  
R. Yu. Bystrov ◽  
A. A. Grigoriev ◽  
E. A. Samodelkin ◽  
B. V. Farmakovsky
Keyword(s):  
Tungsten Carbide ◽  
Composite Powder ◽  
Nanostructured Coatings ◽  
Powder Materials ◽  
Metallic Chromium ◽  
Complex Processes ◽  
Functionally Gradient ◽  
High Microhardness ◽  
Gradient Coatings ◽  
Technological Methods

This paper presents results of a study of complex processes for producing composite powder materials from tungsten carbide and metallic chromium. Technological methods for the formation of functionally gradient coatings with high microhardness up to 426 HV through microplasma spraying technology are disclosed.

Effect of CrSi2 on the ablation resistance of a ZrSi2-Y2O3/SiC coating prepared by SAPS

2021 ◽  
Vol 47 (11) ◽  
pp. 15030-15038
Author(s):  
Fei Liu ◽  
Hejun Li ◽  
Wei Zhang ◽  
Xiyuan Yao ◽  
Qiangang Fu ◽  
...  
Keyword(s):  
Ablation Resistance

Enhanced ablation resistance of HfB2-HfC/SiBCN ceramics under an oxyacetylene torch environment

2021 ◽  
Vol 187 ◽  
pp. 109509
Author(s):  
Qishuai Zhu ◽  
Xingqi Liao ◽  
Dongfei Ao ◽  
Bin Liang ◽  
Daxin Li ◽  
...  
Keyword(s):  
Ablation Resistance

scholarly journals Fabrication and ablation resistance research of C/ZrC-SiC composites

2020 ◽  
Vol 733 ◽  
pp. 012016
Author(s):  
Yi Yu ◽  
Bai-hong Jiang ◽  
Wei Liu ◽  
Xin Jin ◽  
Bao-peng Zhang ◽  
...  
Keyword(s):  
Ablation Resistance ◽  
Sic Composites

scholarly journals Finite Element Prediction for the Internal Stresses of (Ti,Al)N Coatings

2016 ◽  
Vol 61 (1) ◽  
pp. 149-152 ◽  
Author(s):  
L.W. Żukowska ◽  
A. Śliwa ◽  
J. Mikuła ◽  
M. Bonek ◽  
W. Kwaśny ◽  
...  
Keyword(s):  
Finite Element Method ◽  
Computer Simulation ◽  
Finite Element ◽  
Experimental Studies ◽  
Single Layer ◽  
Internal Stresses ◽  
Pvd Coatings ◽  
Properties Of Coatings ◽  
Gradient Coatings ◽  
Element Method

The general topic of this paper is the computer simulation with use of finite element method (FEM) for determining the internal stresses of selected gradient and single-layer PVD coatings deposited on the sintered tool materials, including cemented carbides, cermets and Al2O3+TiC type oxide tool ceramics by cathodic arc evaporation CAE-PVD method. Developing an appropriate model allows the prediction of properties of PVD coatings, which are also the criterion of their selection for specific items, based on the parameters of technological processes. In addition, developed model can to a large extent eliminate the need for expensive and time-consuming experimental studies for the computer simulation. Developed models of internal stresses were performed with use of finite element method in ANSYS environment. The experimental values of stresses were calculated using the X-ray sin2ψ technique. The computer simulation results were compared with the experimental results. Microhardness and adhesion as well as wear range were measured to investigate the influence of stress distribution on the mechanical and functional properties of coatings. It was stated that occurrence of compressive stresses on the surface of gradient coating has advantageous influence on their mechanical properties, especially on microhardness. Absolute value reduction of internal stresses in the connection zone in case of the gradient coatings takes profitably effects on improvement the adhesion of coatings. It can be one of the most important reasons of increase the wear resistance of gradient coatings in comparison to single-layer coatings.

AERO-THERMO-DYNAMIC STUDY OF ULTRA-HIGH- TEMPERATURE CERAMIC COMPOSITES FOR THERMAL PROTECTION SYSTEMS AND ROCKET NOZZLES

2021 ◽  
Author(s):  
STEFANO MUNGIGUERRA ◽  
ANSELMO CECERE ◽  
RAFFAELE SAVINO
Keyword(s):  
High Temperature ◽  
Thermal Protection ◽  
Ceramic Composites ◽  
Thermal Protection Systems ◽  
Research Activities ◽  
Ablation Resistance ◽  
Protection Systems ◽  
Project Objectives ◽  
Ultra High Temperature

The most extreme aero-thermo-dynamic conditions encountered in aerospace applications include those of atmospheric re-entry, characterized by hypersonic Mach numbers, high temperatures and a chemically reacting environment, and of rocket propulsion, in which a combusting, high-pressure, supersonic flow can severely attack the surfaces of the motor internal components (particularly nozzle throats), leading to thermo-chemical erosion and consequent thrust decrease. For these applications, Ultra-High-Temperature Ceramics (UHTC), namely transition metal borides and carbides, are regarded as promising candidates, due to their excellent high-temperature properties, including oxidation and ablation resistance, which are boosted by the introduction of secondary phases, such as silicon carbide and carbon fibers reinforcement (in the so-called Ultra-High- Temperature Ceramic Matrix Composites, UHTCMC). The recent European H2020 C3HARME research project was devoted to development and characterization of new-class UHTCMCs for near-zero ablation thermal protection systems for re-entry vehicles and near-zero erosion rocket nozzles. Within the frame of the project and in collaboration with several research institutions and private companies, research activities at the University of Naples “Federico II” (UNINA) focused on requirements definition, prototypes design and test conditions identification, with the aim to increase the Technology Readiness Level (TRL) of UHTCMC up to 6. Experimental tests were performed with two facilities: an arc-jet plasma wind tunnel, where small specimens were characterized in a relevant atmospheric re-entry environment (Fig.1a), and a lab-scale hybrid rocket engine, where material testing was performed with different setups, up to complete nozzle tests, in conditions representative of real propulsive applications (Fig.1b). The characterization of the aero-thermo-chemical response and ablation resistance of different UHTCMC formulations was supported by numerical computations of fluiddynamic flowfields and materials thermal behavior. The UNINA activities provided a large database supporting the achievement of the project objectives, with development and testing of full-scale TPS assemblies and a large-size solid rocket nozzle.

A Multilayer SiC/ZrB2/SiC Ablation Resistance Coating for Carbon/Carbon Composites

2018 ◽  
Vol 21 (5) ◽  
pp. 1800774
Author(s):  
Guodong Sun ◽  
Hejun Li ◽  
Dongjia Yao ◽  
Hui Li ◽  
Pengfei Yu ◽  
...  
Keyword(s):  
Carbon Composites ◽  
Ablation Resistance
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