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Experimental Study on the Overall Cooling Effectiveness of Effusion-Cooling ceramic matrix composite Platform

Journal of Thermal Science 2023年第3期32卷 1034-1048页

作者： DU Kun CHEN Qihao HUANG Xiaoyang LIANG Tingrui LIU Cunliang School Power and Energy Northwestern Polytechnical UniversityXi'an 710072China Yangtze River Delta Research Institute of NPU Northwestern Polytechnical UniversityTaicang 215400China Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System Northwestern Polytechnical UniversityXi'an 710129China NPU-KAI International Joint Laboratory of Advanced Aero-Engine Thermal Structure Northwestern Polytechnical UniversityXi'an 710129China AECC Sichuan Gas Turbine Establishment Chengdu 610500China

ceramic matrix composite(CMC),with higher thermal limit and lower density relative to the superalloy,is regarded as the most important structural material for modern gas turbine engines.However,the anisotropic thermal conductivities caused by the weave patterns totally change the thermal conduction performance inside the solid domain.Therefore,the present study aims to use the infrared thermographic to measure the SiC/SiC composite platform with staggered effusion holes along with the superalloy platform.CMC platform is prepared by 2-D plain weave braid structure with chemical vapor infiltration(CVI)process.The temperature of mainstream is 900 K to match the real mainstream to coolant temperature ratio(T_(g)/T_(c)=1.5,2.1).The experimental was conducted with seven mass flow ratios(MFR=1.5%-4.5%).The results indicate that the thermal conductivity along the thickness direction is of great importance for the CMC platform.The superalloy platform obtains higher level of overall cooling effectiveness than CMC at T_(g)/T_(c)=1.5.However,the CMC platform achieves greater overall cooling effectiveness relative to superalloy at T_(g)/T_(c)=2.1.In addition,CMC platform presents enhanced uniformity of overall cooling effectiveness due to the larger in-plane thermal conductivity.

关键词： conjugate heat transfer effusion cooling ceramic matrix composite temperature ratio

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Multi-scale collaborative design method for macroscopic thermal optimization and mesoscopic woven structure of hypersonic vehicle's TOCMC leading edge

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Chinese Journal of Aeronautics 2024年第4期37卷 524-541页

作者： Chenwei ZHAO Zecan TU Junkui MAO Jian HUI Pingting CHEN College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 21016China Integrated Energy Institute Nanjing University of Aeronautics and AstronauticsNanjing 210016China

A new thermal protection design method for hypersonic vehicle's leading edge is proposed, which can effectively reduce temperature of the leading edge without additional cooling measures. This method reduces the leading-edge's temperature by the multi-scale collaborative design of the macroscopic thermal optimization and the mesoscopic woven structures of Three-dimensional Orthogonal Woven ceramic matrix composites(TOCMC). The macroscopic thermal optimization is achieved by designing different mesoscopic woven structures in different regions to create combined heat transfer channels to dredge the heat. The combined heat transfer channel is macroscopically represented by the anisotropic thermal conductivity of TOCMC. The thermal optimization multiple linear regression model is established to optimize the heat transport channel, which predicts Theoretical Optimal Thermal Conductivity Configuration(TOTCC) in different regions to achieve the lowest leading-edge temperature. The function-oriented mesostructure design method is invented to design the corresponding mesostructure of TOCMC according to the TOTCC, which consists of universal thermal conductivity prediction formulas for TOCMC. These universal formulas are firstly derived based on the thermal resistance network method, which is verified by experiments with an error of 6.25%. The results show that the collaborative design method can effectively reduce the leading edge temperature by about 12.8% without adding cooling measures.

关键词： Multi-scale collaborative design Thermal optimization ceramic matrix composite Hypersonic vehicle Thermal protection Intelligent optimization

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STUDY ON PREPARATION OF ceramic matrix composite OF WC-Co ULTRAFINE POWDERS

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Journal of Wuhan University of Technology(Materials Science) 1995年第2期10卷 40-46页

作者：曹立宏时东霞欧阳世翕关波

The W -Co compound precursor powders with an average particle sife of 60 nm were prepared by the chemical coprecipitation as the raw materials of Na2WO1 and CoCl2 and as the reagents of HCI and NH3 ?H2O. After re-ducing and carburizing the precursor powders by hydrogen gas and CO-CO 2 mixture gas. the WC-Co composite povvders ivith an average particle size of 0. 18/wi can be obtained. The purity and particle size of powders -were analysed by XRD and TEM. respectively. Meanwhile, the key factors to influ-ence the reducing and carburizing process of powders were also studied.

关键词： WC-Co ceramic matrix composite ul-trafine powders

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Preparation and Mechanical Properties of Al_2O_3/Al Laminated ceramic matrix composites

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Journal of Wuhan University of Technology(Materials Science) 2011年第5期26卷 891-896页

作者：黄康明吴建青 College of Materials Science and Engineering South China University of Technology

Three series of Al2O3/Al laminated ceramic matrix composites,named SPA,SPV and HP,were fabricated by different methods.SPA and SPV were prepared using Al2O3 slices and Al slurry via screen printing and subsequent heat treatment in air or vacuum.HP samples were made by hot pressing the layered stack of Al foils and Al2O3 slices.SEM and XRD were applied to analyze the microstructure and the interlayer crystal phase.The bending strength,fracture toughness and fracture work of the samples made by the three methods were measured and compared.The results show that the composites have much better toughness and higher fracture work than the Al2O3 slice.Among the samples made by the three methods,the samples made by hot pressing have the optimum mechanical performance.The displacement-load curves and fracture mechanism were analyzed.

关键词： laminated ceramic matrix composite mechanical properties

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Cutting force and specific energy for rotary ultrasonic drilling based on kinematics analysis of vibration effectiveness

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Chinese Journal of Aeronautics 2022年第1期35卷 376-387页

作者： Zhen LI Songmei YUAN Jiang MA Jun SHEN Andre D.L.BATAKO College of Mechatronics and Control Engineering.Shenzhen University Shenzhen 518060China College of Physics and Optoelectronic Engineering Shenzhen UniversityShenzhen 518060China School of Mechanical Engineering and Automation Beihang UniversityBeijing 100083China The General Engineering&Techmology Research Institute Liverpool John Moores UniversitLiverpool L33AF.UK

Rotary ultrasonic drilling(RUD)has become an effective approach for machining advanced composites which are widely using in the field of aeronautics.The cutting kinematics and the corresponding material removal mechanisms are distinct in different drilling areas during RUD.However,these fundamentals have not been fully considered in the existing studies.In this research,two distinct forms of interaction induced by ultrasonic vibration were considered as impact-separation and vibratory lapping between the abrasives and workpiece.And the conditions to guarantee the effectiveness of these interactions were obtained to eliminate diminishing effects of ultrasonic vibration.Based on indentation fracture theory,the penetration depth of abrasives and the axial drilling force model was derived for RUD.The verification tests of C/SiC composites resulted in a prediction error within 15%.Due to the minimal volume of material removed during each vibration cycle,the drilling force was more stable in vibration assisted mode.The specific drilling energy of RUD was firstly calculated based on the measured drilling load.It was found the drilling parameters should be matched with vibration frequency and amplitude to make better usage of the advantages of ultrasonic vibration,which is critical in the vibration assisted processing of advanced materials.

关键词： ceramic matrix composite Drilling force modelling Kinematics analysis Rotary ultrasonic drilling Specific drilling energy Vibration diminishing effect

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Dynamic oxidation mechanism of carbon fiber reinforced SiC matrix composite in high-enthalpy and high-speed plasmas

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Journal of Advanced ceramics 2022年第2期11卷 365-377页

作者： Lingwei YANG Xueren XIAO Liping LIU Jie LUO Kai JIANG Xinxing HAN Changhao ZHAO Jun ZHANG Guolin WANG Hypervelocity Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 621000China Science and Technology on Thermostructural composite Materials Laboratory Northwestern Polytechnical UniversityXi’an 710072China Shandong Research and Design Institute of Industrial ceramics Co.Ltd.Zibo 255000China

This work employed an inductively coupled plasma wind tunnel to study the dynamic oxidation mechanisms of carbon fiber reinforced SiC matrix composite(C_(f)/SiC)in high-enthalpy and high-speed plasmas.The results highlighted a transition of passive/active oxidations of SiC at 800–1600℃and 1–5 kPa.Specially,the active oxidation led to the corrosion of the SiC coating and interruption of the SiO_(2) growth.The transition borders of active/passive oxidations were thus defined with respect to oxidation temperature and partial pressure of atomic O in the high-enthalpy and high-speed plasmas.In the transition and passive domains,the SiC dissipation was negligible.By multiple dynamic oxidations of C_(f)/SiC in the domains,the SiO_(2) thickness was not monotonously increased due to the competing mechanisms of passive oxidation of SiC and dissipation of SiO_(2).In addition,the mechanical properties of the SiC coating/matrix and the C_(f)/SiC were maintained after long-term dynamic oxidations,which suggested an excellent thermal stability of C_(f)/SiC serving in thermal protection systems(TPSs)of reusable hypersonic vehicles.

关键词： thermal protection system(TPS) ceramic matrix composite oxidation mechanism plasma wind tunnel mechanical property

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Environmental Effects on Microstructural Stability of SiC/SiC composites

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International Journal of Minerals,Metallurgy and Materials 1999年第2期13卷 125-128页

作者： Shibayama T. He G.W. Takahashi H. Katoh Y. Kohyama A. Center for Advanced Research of Energy Technology Hokkaido University Sapporo 060-8628 Japan Institute of Advanced Energy Kyoto University Gokasho Uji 611-0011 Japan

LowZmaterialshavemanyadvantagesinnuclearenvirOInnellts,suchaslessProductionofradioactivewastesduetosubstantiallylowactivation,andhigherconVergentefficiencyduetothecapabilityofhightemp;Peration.HopkinhasdiscussedSiC-ba... 详细信息

关键词： ceramic matrix composite SiC oxidation crystallization interface

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Frictional response of a novel C/C-ZrB_(2)-ZrC-SiC composite under simulated braking

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Journal of Advanced ceramics 2013年第2期2卷 157-161页

作者： Yangbao QIAN Weigang ZHANG Min GE Xi WEI State Key Laboratory of Multiphase Complex Systems Institute of Process EngineeringChinese Academy of SciencesNo.1 BeiertiaoBeijing 100190China

A novel braking material,C/C-ZrB_(2)-ZrC-SiC carbon fibre-reinforced hybrid ceramic matrix composite,was prepared by chemical vapour infiltration and polymeric precursor infiltration and pyrolysis.Investigation of the microstructure of C/C-ZrB_(2)-ZrC-SiC composite showed the homogenous dispersion of three-phase ceramic as the matrix.The frictional properties of the hybrid C/C-ZrB_(2)-ZrC-SiC ceramic matrix composite were measured by a disk-on-disk type dynamometer under dry and wet conditions to simulate the normal landing state of aircraft brake disk friction pairs.C/C-ZrB_(2)-ZrC-SiC ceramic matrix composite has a higher and more stable friction coefficient under wet condition than under dry condition,indicating that the composite has better performance compared with C/C or C/C-SiC braking materials.

关键词： ceramic matrix composite brake materials abrasion braking testing

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Influences of Mechanical Vibration on Rapidly Solidified Al_2O_3/YSZ ceramics Prepared by Combustion Synthesis

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Chinese Journal of Aeronautics 2006年第B12期19卷 27-30页

作者： ZHAO Zhong-min ZHANG Long WANG Wei-guo ZHANG Shi-yue Institute of Advanced Materials Mechanical Engineering College Shijiazhuang 050003 China Science Research Department Mechanical Engineering College Shijiazhuang 050003 China Foreign Training Department Mechanical Engineering College Shijiazhuang 050003 China

Al2O3/YSZ composite ceramics was fabricated with combustion synthesis technology, and the influences of mechanical vibration on its microstructures and properties were investigated. It is found that under the mechanical vibration of ever-increasing frequency, increasing combustion temperature, accelerating ceramics/metal liquid-liquid separation and quickening ceramic solidification could not only reduce the average diameter and the size distribution of aligned ZrO2 nano-micron fibers in rod-shaped Al 2O3 matrix grains, but also make the randomly-oriented rod-shaped grains finer and increase their aspect ratios. As a result, a remarkable increase in fiexural strength and fracture toughness of the ceramics can be observed.

关键词： ceramic matrix composite combustion synthesis rapid solidification nanocrystalline microstructure mechanical vibration

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Thermal Stress and Assembling Parameters Evolution of CMC Bolted Joint under Transient Thermal Loads

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Journal of Harbin Institute of Technology(New Series) 2021年第3期28卷 1-8页

作者： Shuyuan Zhao Zhengyu Li Zeliang Pu Xinyang Sun Wenjiao Zhang National Key Laboratory of Science and Technology for National Defense on Advanced composites in Special Environments Harbin Institute of TechnologyHarbin 150080China School of Aeronautics and Astronautics Harbin Institute of TechnologyHarbin 150001China Engineering College Northeast Agricultural UniversityHarbin 150030China

ceramic matrix composite(CMC) and superalloy bolted joints have exhibited great potential for high temperature hot structure application in hypersonic aircraft. In service conditions, the thermal expansion mismatch between CMC and superalloy plates will cause complex thermal stress and strain distributions at hole-edge areas and assembly parameters changes of the joints under elevated temperatures. These effects might lead to early damage of joint structure, which will endanger the structural integrity and load carrying capacity of aircraft components. In the present study, transient heat transfer and thermo-structural analysis of C/SiC composite and superalloy bolted joint were carried out by using a commercial FEA software ABAQUS. The stress distributions at hole-edge areas, pre-load loosening, and variation of bolt-hole clearance of CMC bolted joints under transient temperature rises were discussed for better understanding of high temperature structural behaviors. Results showed that pre-load declined with the increase of imposed hot side temperature, due to the thermal expansion mismatch between CMC and superalloy. The bolt-hole clearance for the composite plate decreased, whereas the clearance for the superalloy plate increased with the rise of temperature.

关键词： ceramic matrix composite heat transfer thermal stress pre-load bolt-hole clearance

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