Journal articles: 'Ceramic Matrix Composite (CMC)'

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HASHIMOTO, R., M. HOJO, A. OGAWA, Y. SOFUE, and F. ZHOU. "CMC-10: Rotational Strength of C/SiC Composite Blisk Model(CMC-II: CERAMICS AND CERAMIC MATRIX COMPOSITE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 37–38. http://dx.doi.org/10.1299/jsmeintmp.2005.37_5.

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ISHII, K., M. KOYAMA, H. HATTA, and I. SHIOTA. "CMC-09: Hybrid Bonding between C/C Composites Using Si Infiltration(CMC-II: CERAMICS AND CERAMIC MATRIX COMPOSITE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 37. http://dx.doi.org/10.1299/jsmeintmp.2005.37_4.

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Rybyanets, A. N., A. V. Nasedkin, N. A. Shvetsova, E. I. Petrova, M. A. Lugovaya, and I. A. Shvetsov. "Ceramic matrix piezocomposites: microstructural features and dielectric properties." Известия Российской академии наук. Серия физическая 87, no. 9 (September 1, 2023): 1301–7. http://dx.doi.org/10.31857/s0367676523702290.

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A new method for the fabrication of ceramic-matrix piezocomposites (CMC) ceramics/ceramics has been developed. Samples of piezoactive PZT/PZT composites with a mass concentration of components from 0 to 50% have been obtained. The study of microstructural and gravimetric features, as well as the dielectric properties of CMC, has been carried out. Finite element modeling and experimental study of CMC properties in the region of dielectric percolation transition have been performed. It is shown that the developed method for manufacturing CMC provides the formation of microhomogeneous composite structures with a uniform distribution of ceramic filler particles in a microporous piezoceramic matrix without the formation of transition regions and additional crystalline phases.

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Konopka, Katarzyna. "Particle-Reinforced Ceramic Matrix Composites—Selected Examples." Journal of Composites Science 6, no. 6 (June 19, 2022): 178. http://dx.doi.org/10.3390/jcs6060178.

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This paper presents some examples of ceramic matrix composites (CMCs) reinforced with metal or intermetallic phases fabricated by powder consolidation without a liquid phase (melted metal). Composites with a complex structure, which are an advanced group of CMCs called hybrid composites, were described in contrast to conventional composites with a ceramic matrix. In advanced CMCs, their complex structures make it possible to achieve the synergistic effect of the micro- and nanoparticles of the metallic, intermetallic, and ceramic phases on the composite properties, which is not possible in conventional materials. Various combinations of substrates in the form of powder as more than one metal and ceramics with different powder sizes that are used to form hybrid composites were analyzed. The types of CMC microstructures, together with their geometrical schemas and some examples of real ceramic matrix composites, were described. The schemas of composite microstructures showed the possible location of the ceramic, metallic, or intermetallic phases in composites. A new concept of an advanced ceramic–intermetallic composite fabricated by the consolidation of pre-composite powder mixed with ceramic powder was also presented. This concept is based on the selection of substrates, two metals in the form of powder, which will form a new compound, intermetallic material, during processing. Metal powders were milled with ceramic powders to obtain a pre-composite powder consisting of intermetallic material and ceramics. In the next step, the consolidation of pre-composite powder with ceramic powder allows the creation of composites with complex microstructures. Selected examples of real particle-reinforced conventional and hybrid microstructures based on our own investigations were presented. In addition to microstructures, the properties and possible applications of CMCs were analyzed.

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Okamura, Kiyohito. "Ceramic matrix composites (CMC)." Advanced Composite Materials 4, no. 3 (January 1995): 247–59. http://dx.doi.org/10.1163/156855195x00050.

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BESSHO, T., T. OGASAWARA, T. AOKI, T. ISHIKAWA, and Y. OCHI. "CMC-05: Transient Creep Behavior of a Plain Woven SiC Fiber/SiC Matrix Composite(CMC-I: CERAMICS AND CERAMECS MATRIX COMPOSITES)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 15. http://dx.doi.org/10.1299/jsmeintmp.2005.15_1.

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SHIBATA, T., J. SUMITA, S. BABA, M. YAMAJI, M. ISHIHARA, K. SAWA, and T. IYOKU. "CMC-11: Tensile Strength of Two-dimensional C/C Composite with its Microstructure for Nuclear Application(CMC-II: CERAMICS AND CERAMIC MATRIX COMPOSITE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 38. http://dx.doi.org/10.1299/jsmeintmp.2005.38_1.

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KOGO, Y., and M. KOMORI. "CMC-12: Fracture Toughness Tests on Carbon Fibers Notched by Focused Ion Beam(CMC-II: CERAMICS AND CERAMIC MATRIX COMPOSITE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 38. http://dx.doi.org/10.1299/jsmeintmp.2005.38_2.

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Gadow, Rainer, and Patrick Weichand. "SiOC Composite Structures for Intermediate Service Temperatures with Increased Friction Properties." Advances in Science and Technology 88 (October 2014): 15–20. http://dx.doi.org/10.4028/www.scientific.net/ast.88.15.

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Polymer Matrix Composites (PMC) are often used in lightweight applications due to their excellent mechanical properties combined with a low density. The manufacturing technologies are fully developed and raw materials are cheap. The limiting factor of these reinforced polymers is the maximum service temperature. Ceramic Matrix Composites (CMC) are suitable for service temperatures up to 1500 °C and more. These composites are composed of ceramic matrices combined with ceramic fibers based on alumina or silicon carbide. This class of composites is handicapped by the high cost of processing and raw materials and therefore only attractive for applications in astronautics and military aviation. Composite materials, bridging the gap between PMC and CMC, are manufactured by the use of polysiloxanes, carbon-and basalt fibers. Such competitive free formable Hybrid-composites are capable for service temperatures up to 800 °C in oxidative atmosphere. In order to make the material attractive also for series applications, manufacturing technologies like filament wet winding, Resin Transfer Moulding (RTM) or pressing techniques are employed. Beside the improved thermal resistivity in comparison to reinforced polymers and light metals, a major benefit of SiOC composites is investigated in the field of friction materials. The excellent properties in wear resistance and an adjustable coefficient of friction make it an interesting alternative for CFC and CMC.

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Shestakov, A. M., N. I. Shvets, and V. A. Rosenenkova. "Study of preceramic compositions based on modified polycarbosilane and polyorganosilazanes." Industrial laboratory. Diagnostics of materials 87, no. 9 (September 24, 2021): 30–37. http://dx.doi.org/10.26896/1028-6861-2021-87-9-30-37.

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Ceramic matrix composites (CMC) exhibit increased crack resistance and resistance to mechanical and thermal shock impacts retaining at the same time the valuable properties of monolithic ceramics. Therefore, they are widely used as parts of heat-loaded elements of aviation and rocket technology, in nuclear power industry, etc. LPI-method (liquid polymer infiltration) of CMC production is based on the impregnation of a skeleton of ceramic fibers with an organosilicon polymer, formation of a preceramic matrix by polymer technology, and subsequent high-temperature pyrolysis resulting in formation of a reinforced ceramic matrix. Ceramics obtained from polymer precursors have a predominantly amorphous structure which determines its high thermal stability. Moreover, introduction of the nanosized particles of carbides, borides and nitrides of refractory metals (Zr, Ti, Hf) into the matrix of a ceramic composite stabilizes its amorphous structure up to temperatures of 1500 - 1600°C. We present the results of studying the preceramic compositions based on polycarbosilane and polyorganosilazanes modified with Hf and Ta atoms. It is shown that introduction of the modifying additives Hf and Ta into the polyorganosilazane composition shifts the curing interval of the compositions towards lower temperatures. The yield of the gel fraction is 73.3 and 82.7 wt.%, respectively. The weight loss of pyrolysate samples heated to 1400°C in air does not exceed 0.5%. The physical and mechanical properties, as well as the thermal oxidative stability of novel ceramic composite materials obtained on the base of the studied compositions and carbon reinforcing filler are analyzed. It is shown that the density of CMC samples increases by 1.5 times with an increase in the number of impregnation cycles and reaches the maximum value of 1950 kg/m3 with five impregnation cycles of the filler with a composition based on polyorganosilazane modified with Ta. The results obtained can be used in the development of new CMCs.

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Song, Chaokun, Fang Ye, Laifei Cheng, Yongsheng Liu, and Qing Zhang. "Long-term ceramic matrix composite for aeroengine." Journal of Advanced Ceramics 11, no. 9 (August 31, 2022): 1343–74. http://dx.doi.org/10.1007/s40145-022-0611-5.

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AbstractThree strategies were proposed to prolong the service life of continuous fiber-reinforced silicon carbide ceramic matrix composite (CMC-SiC), which served as thermal-structure components of aeroengine at thermo-mechanical-oxygenic coupling environment. As for some thermal-structure components with low working stress, improving the degree of densification was crucial to prolong the service life, and the related process approaches were recited. If the thermal-structure components worked under moderate stress, the matrix cracking stress (σmc) should be improved as far as possible. The fiber preform architecture, interface shear strength, residual thermal stress, and matrix strengthening were associated with σmc in this review. Introducing self-healing components was quite significant with the appearance of matrix microcracks when CMC-SiC worked at more severe environment for hundreds of hours. The damage can be sealed by glass phase originating from the reaction between self-healing components and oxygen. The effective self-healing temperature range of different self-healing components was first summarized and distinguished. The structure, composition, and preparation process of CMC-SiC should be systematically designed and optimized to achieve long duration target.

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Izumi, Takao, and Hiroshi Kaya. "Ceramic Matrix Composites Application in Automotive Gas Turbines." Journal of Engineering for Gas Turbines and Power 119, no. 4 (October 1, 1997): 790–98. http://dx.doi.org/10.1115/1.2817056.

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We are conducting the development of ceramic matrix composites (CMC) and components made of CMC for a 100 kW automotive ceramic gas turbine (CGT) as shown in Fig. 1. When compared to monolithic ceramics (MC), CMC that we have developed demonstrate superior strength characteristics in terms of resistance to particle impact and thermal shock. We have conducted evaluation tests on the strength of CMC components in which MC such as silicon nitride and silicon carbide were used as a reference for comparison with CMC in the same testing process as employed for components made of MC such as silicon nitride and silicon carbide. It was confirmed that actual components made of CMC realized approximately the same strength as the test pieces. Furthermore, some CMC components have already passed screening tests that evaluated the strength of the components. It was therefore confirmed that the potential exists for the possibility of testing these components in high-temperature assembly tests and engine tests.

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Lee, Sea-Hoon, Feng Lun, and Kyeongwoon Chung. "Ultra-high Temperature Ceramics-Ceramic Matrix Composites (UHTC-CMC)." Composites Research 30, no. 2 (April 30, 2017): 94–101. http://dx.doi.org/10.7234/composres.2017.30.2.094.

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DiCarlo, J. A., and H. M. Yun. "Modeling the Thermostructural Capability of Continuous Fiber-Reinforced Ceramic Composites." Journal of Engineering for Gas Turbines and Power 124, no. 3 (June 19, 2002): 465–70. http://dx.doi.org/10.1115/1.1470480.

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There exists today considerable interest in developing continuous fiber-reinforced ceramic matrix composites (CMC) that can operate as hot-section components in advanced gas turbine engines. The objective of this paper is to present simple analytical and empirical models for predicting the effects of time and temperature on CMC tensile rupture under various composite and engine conditions. These models are based on the average rupture behavior measured in air for oxide and SiC-based fibers of current technical interest. For example, assuming a cracked matrix and Larson-Miller rupture curves for single fibers, it is shown that model predictions agree quite well with high-temperature stress-rupture data for SiC/SiC CMC. Rupture models, yet to be validated, are also presented for three other relevant conditions: (a) SiC fibers become oxidatively bonded to each other in a cracked CMC, (b) applied CMC stresses are low enough to avoid matrix cracking, and (c) Si-based CMC are subjected to surface recession in high-temperature combustion gases. The practical implications of the modeling results are discussed, particularly in regard to the optimum fibers and matrices for CMC engine applications and the thermostructural capability of SiC/SiC CMC in comparison to nickel-based superalloys, monolithic ceramics, and oxide/oxide CMC.

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OKABE, Nagatoshi. "Ceramic Matrix Composite with Multi-Functional Properties." Journal of the Society of Mechanical Engineers 99, no. 929 (1996): 275–80. http://dx.doi.org/10.1299/jsmemag.99.929_275.

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Nandakumar, A., and D. Dinakaran. "Effect of Nanoparticles in Reinforced Metal Matrix Composite on the Machinability Characteristics - A Review." Applied Mechanics and Materials 813-814 (November 2015): 625–28. http://dx.doi.org/10.4028/www.scientific.net/amm.813-814.625.

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Metal Matrix nanoComposites (MMNC) refer to materials consisting of a ductile metal or alloy matrix in which some nanosized reinforcement materials is implanted. These materials combine metal and ceramic features, i.e., ductility and toughness with high strength. Thus, metal matrix nanocomposites are suitable for production of materials with high strength in shear/compression processes and high service temperature capabilities. Both Metal Matrix Composite (MMC) and Ceramic Matrix Composites (CMC) with Carbon nanoTubes (CNT) nanocomposites hold promise, but also pose challenges for real success. In the present paper deals an inclusive review of literature in effect of nanoparticles in reinforced metal matrix composites on the machinability characteristics of the composite materials.

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Ruggles-Wrenn, Marina, and Joshua Schmidt. "Tension–Compression Fatigue of a Hybrid Polymer-Matrix/Ceramic-Matrix Composite at Elevated Temperature." Journal of Composites Science 8, no. 8 (July 29, 2024): 291. http://dx.doi.org/10.3390/jcs8080291.

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Fully reversed tension–compression fatigue of a hybrid material comprising polymer matrix composite (PMC) co-cured with a ceramic matrix composite (CMC) was investigated. The PMC portion had a polyimide matrix reinforced with 15 plies of carbon fibers woven in an eight-harness satin weave (8HSW). The CMC portion had three plies of a quartz-fiber 8HSW fabric in a zirconia-based ceramic matrix. The hybrid PMC/CMC was developed for use in aerospace thermal protection systems (TPS). Hence, the experimental setup aimed to simulate the TPS service environment—the CMC side was kept at 329 °C, whereas the PMC side was open to laboratory air. Compression stress–strain response was studied, and compressive properties were measured at room and elevated temperature. Tension–compression fatigue tests were conducted at elevated temperature at 1.0 Hz. The evolution of tensile and compressive strains with fatigue cycles, as well as changes in the stress–strain hysteresis behavior and stiffness were examined. The tension–compression fatigue of a PMC with the same constituents and fiber architecture as the PMC portion of the PMC/CMC was studied for comparison. Tension–compression fatigue was found to be more damaging than tension–tension fatigue for both materials. The PMC outperformed the PMC/CMC in tension–compression fatigue. Post-test examination showed widespread delamination and striking non-uniform deformation modes of the PMC/CMC.

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MYLVAGANAM, K., and L. C. ZHANG. "CMC-13: The Shape Effects of Silicon Nanowires : A Molecular Dynamics and Density Functional Theory Study(CMC-II: CERAMICS AND CERAMIC MATRIX COMPOSITE)." Proceedings of the JSME Materials and Processing Conference (M&P) 2005 (2005): 38. http://dx.doi.org/10.1299/jsmeintmp.2005.38_3.

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Kedward, Keith T., and Peter W. R. Beaumont. "On the Notch-Sensitivity and toughness of A Ceramic Composite." Advanced Composites Letters 1, no. 2 (March 1992): 096369359200100. http://dx.doi.org/10.1177/096369359200100204.

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A Nicalon TM/SiC fabric (8-harness satin) reinforced alumina matrix (CMC) was loaded in tension to fracture. A coating on the surface of the fibre reduced the strength of the fibre-matrix bond, increased the toughness of the CMC by more than 3 times, and raised the unnotched strength by more than 2 times.

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Gu, Jian, Sea-Hoon Lee, Daejong Kim, Hee-Soo Lee, and Jun-Seop Kim. "Improved thermal stability of SiCf/SiC ceramic matrix composites fabricated by PIP process." Processing and Application of Ceramics 15, no. 2 (2021): 164–69. http://dx.doi.org/10.2298/pac2102164g.

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Improvement of the thermal stability of continuous SiC fiber reinforced SiC ceramic matrix composites (SiCf/SiC CMC) by the pre-treatment of SiC fillers and the suppression of oxidation during polymer impregnation and pyrolysis (PIP) process were investigated. Dense SiCf/SiC CMCs were fabricated using the slurry infiltration and PIP process under a purified argon atmosphere. Structure and mechanical properties of the SiCf/SiC CMC heated at different temperatures were evaluated. The flexural strength of the SiCf/SiC CMC decreased only 15.3%after heating at 1400 ?C, which exhibited a clear improvement compared with the literature data (49.5% loss), where severe thermal deterioration of SiCf/SiC composite occurred at high temperatures by the crystallization and decomposition of the precursor-derived ceramic matrix. The thermal stability of the SiCf/SiC CMC fabricated by PIP process was improved by the pre-treatment of SiC fillers for removing oxides and the strict atmosphere control to prevent oxidation.

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Igashira, Ken-ichiroh, Hyoe Ono, Naohumi Akikawa, and Yoshihiro Matsuda. "133 Development of the Ceramic Matrix Composite(CMC) for Gas Turbine." Proceedings of the Materials and processing conference 2001.9 (2001): 283–84. http://dx.doi.org/10.1299/jsmemp.2001.9.283.

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van Roode, Mark, Jeff Price, Josh Kimmel, Naren Miriyala, Don Leroux, Anthony Fahme, and Kenneth Smith. "Ceramic Matrix Composite Combustor Liners: A Summary of Field Evaluations." Journal of Engineering for Gas Turbines and Power 129, no. 1 (March 1, 2005): 21–30. http://dx.doi.org/10.1115/1.2181182.

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Solar Turbines Incorporated, under U.S. government sponsored programs, has been evaluating ceramic matrix composite combustor liners in test rigs and Solar’s Centaur® 50S gas turbine engines since 1992. The objective is to evaluate and improve the performance and durability of CMCs as high-temperature materials for advanced low emissions combustors. Field testing of CMC combustor liners started in May of 1997 and by the end of 2004, over 67,000 operating hours had been accumulated on SiC∕SiC and oxide∕oxide CMC liners. NOx and CO emissions have been consistently <15ppmv and <10ppmv, respectively. Maximum test durations of 15,144h and 13,937h have been logged for SiC∕SiC liners with protective environmental barrier coatings. An oxide∕oxide CMC liner with a Friable Graded Insulation coating has been tested for 12,582h. EBCs significantly improve SiC∕SiC CMC liner life. The basic three-layer EBC consists of consecutive layers of Si, mullite, and BSAS. The durability of the baseline EBC can be improved by mixing BSAS with mullite in the intermediate coating layer. The efficacy of replacing BSAS with SAS has not been demonstrated yet. Heavy degradation was observed for two-layer Si∕BSAS and Si∕SAS EBCs, indicating that the elimination of the intermediate layer is detrimental to EBC durability. Equivalent performance was observed when the Hi-Nicalon fiber reinforcement was replaced with Tyranno ZM or ZMI fiber. Melt infiltrated SiC∕SiC CMCs have improved durability compared to SiC∕SiC CMCs fabricated by Chemical Vapor Infiltration of the matrix, in the absence of an EBC. However, the presence of an EBC results in roughly equivalent service life for MI and CVI CMCs. Results to date indicate that oxide∕oxide CMCs with protective FGI show minor degradation under Centaur® 50S gas turbine engine operating conditions. The results of, and lessons learned from CMC combustor liner engine field testing, conducted through 2004, have been summarized.

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Nishio, K., K. I. Igashira, K. Take, and T. Suemitsu. "Development of a Combustor Liner Composed of Ceramic Matrix Composite (CMC)." Journal of Engineering for Gas Turbines and Power 121, no. 1 (January 1, 1999): 12–17. http://dx.doi.org/10.1115/1.2816300.

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The Research Institute of Advanced Materials Gas-Generator (AMG), which is a joint effort by the Japan Key Technology Center and 14 firms in Japan, has, since fiscal year 1992, been conducting technological studies on an innovative gas generator that will use 20 percent less fuel, weigh 50 percent less, and emit 70 percent less NOx than the conventional gas generator through the use of advanced materials. Within this project, there is an R&D program for applying ceramic matrix composite (CMC) liners to the combustor, which is a major component of the gas generator. In the course of R&D, continuous SiC fiber-reinforced SiC composite (SiCF/SiC) was selected as the most suitable CMC for the combustor liner because of its thermal stability and formability. An evaluation of the applicability of the SiCF/SiC composite to the combustor liner on the basis of an evaluation of its mechanical properties and stress analysis of a SiCF/SiC combustor liner was carried out, and trial SiCF/SiC combustor liners, the largest of which was 500-mm in diameter, were fabricated by the filament winding and PIP (polymer impregnation and pyrolysis) method. Using a SiCF/SiC liner built to the actual dimensions, a noncooling combustion test was carried out and even when the gas temperature was raised to 1873K at outlet of the liner, no damage was observed after the test. Through our studies we have confirmed the applicability of the selected SiCF/SiC composite as a combustor liner. In this paper, we describe the present state of the R&D of a CMC combustor liner.

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Shrivastava, Shriya, Dipen Kumar Rajak, Tilak Joshi, Dwesh K. Singh, and D. P. Mondal. "Ceramic Matrix Composites: Classifications, Manufacturing, Properties, and Applications." Ceramics 7, no. 2 (May 10, 2024): 652–79. http://dx.doi.org/10.3390/ceramics7020043.

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Ceramic matrix composites (CMCs) are a significant advancement in materials science and engineering because they combine the remarkable characteristics of ceramics with the strength and toughness of fibers. With their unique properties, which offer better performance and endurance in severe settings, these advanced composites have attracted significant attention in various industries. At the same time, lightweight ceramic matrix composites (LCMCs) provide an appealing alternative for a wide range of industries that require materials with excellent qualities such as high-temperature stability, low density, corrosion resistance, and excellent mechanical performance. CMC uses will expand as production techniques and material research improve, revolutionizing aerospace, automotive, and other industries. The effectiveness of CMCs primarily relies on the composition of their constituent elements and the methods employed in their manufacturing. Therefore, it is crucial to explore the functional properties of various global ceramic matrix reinforcements, their classifications, and the manufacturing techniques used in CMC fabrication. This study aims to overview a diverse range of CMCs reinforced with primary fibers, including their classifications, manufacturing techniques, functional properties, significant applications, and global market size.

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Hirschmann, Ana Coh O., Maria do Carmo de Andrade Nono, R. R. Riehl, and C. R. M. Silva. "Processing and Microstructural Characterization of Porous Alumina-Zirconia Ceramic Using CMC and PVC." Materials Science Forum 591-593 (August 2008): 510–13. http://dx.doi.org/10.4028/www.scientific.net/msf.591-593.510.

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Porous materials are of significant interest due to their wide application in catalysis, separation, lightweight structural materials, biomaterials and other areas. Porous ceramics are produced within a wide range of porosities and pore sizes depending on the application intended. Porosity and pore size distribution can be carefully controlled by the choice of organic composite and the amount added. The material may have two types of pores: open and closed pores. The open pores, also called interconnected pores, are those which are in contact with the external surface of the material, being very useful for the manufacture of ceramic filters. A high number of closed pores are important for the manufacturing of materials used in thermal applications. There are many methods for obtaining porous ceramics, in general consisting in adding to the ceramic matrix organic particles, which volatilize during the first heat-up. The objective of this study was to produce ceramic composite nanostructure of alumina and yttria stabilized zirconia (Y-TZP) with micrometric pore sizes. The effects of ZrO2 additions in the mechanical properties of Al2O3 have been intensively investigated, due to the possible increase of the mechanical strength of this material. The organic particles used to create the pores were CMC and PVC. The microstructure of the porous ceramic samples obtained was evaluated considering the degree of sinterization of the nanoparticles, pores formation, porosity, specific surface of the pores and the distribution of the interconnecting pores.

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Langston, Lee S. "Hot Plates." Mechanical Engineering 138, no. 03 (March 1, 2016): 42–47. http://dx.doi.org/10.1115/1.2016-mar-3.

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This article presents an overview of use, advantages, and challenges related to ceramic gas turbines. The research shows that if these ceramic parts perform as promised, both operationally and economically, it could radically alter the jet engine industry. The promise of ceramics is that by taking advantage of their lower weight and superior high temperature properties, one could replace the complex air-cooled metal components with simpler ceramic components more tolerant of high temperatures. However, one difficulty engineers have had in developing ceramic components is the inability to put promising designs in production gas turbines for a true ‘beta’ test. GE plans to expand its application of ceramic matrix composites use in its 100,000-pound thrust GE9X engine, now under development for Boeing’s 777X airframe and scheduled to enter service in 2020. It will feature CMC combustion liners, high-pressure turbine stators, and first-stage shrouds. The jet engine industry has since developed successful composite fans; however, the inaugurating company got off to a rocky start.

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Piotter, Volker, Metin Tueluemen, Thomas Hanemann, Michael J. Hoffmann, and Benjamin Ehreiser. "Powder Injection Molding of Oxide Ceramic CMC." Key Engineering Materials 809 (June 2019): 148–52. http://dx.doi.org/10.4028/www.scientific.net/kem.809.148.

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Ceramic Matrix Composites (CMC) offer improved mechanical properties, especially higher toughness, preferably at elevated temperatures. Fields of application are, for example, highly hot stressed components of aero engines.Processing of Ceramic Matrix Composites by powder injection molding offers attractive economic benefits, however, it represents a considerable challenge. Development of a process chain for the ceramic injection molding of Al2O3 short fiber CMC had started by feedstock preparation and characterization. Fiber content varied between 10 to 50 vol.% whereas for binder a well-examined system from KIT was chosen. The fiber content showed a minor effect on the rheological properties but fiber orientation depended strongly on the apparent shear profile. The sintering behavior was affected as well, i.e. higher densities were achieved.

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Gadow, Rainer. "Lightweight Engineering with Advanced Composite Materials - Ceramic and Metal Matrix Composites." Advances in Science and Technology 50 (October 2006): 163–73. http://dx.doi.org/10.4028/www.scientific.net/ast.50.163.

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Light weight engineering by materials and by design are central challenges in modern product development for automotive applications. High strength structural ceramics and components were in the focus of R & D in automobile development since the 1970's and CMC have dominated advanced materials engineering in aerospace applications. The limiting factor for their market acceptance was the high processing and manufacturing cost. The automotive industry requires technical performance and high economic competitiveness with tough cost targets. The potential of ceramic matrix composites can be enhanced, if new fast and cost effective manufacturing technologies are applied. This is demonstrated in the case of SiC composites for high-performance disk brake rotors for passenger cars. Light metal composites are promising candidates to realize safety relevant lightweight components because of their high specific strength and strain to failure values, if their stiffness and their thermal and fatigue stability is appropriate for the application, i.e. in power train and wheel suspension of cars. Tailor-made fiber reinforcements in light metal matrices can solve this problem, but the integration of fibers with conventional manufacturing techniques like squeeze casting or diffusion bonding leads to restrictions in the component's geometry and results in elevated process cost mainly caused by long cyc1e times and the need of special tools and additional fiber coatings. A new manufacturing method for metal matrix composites (MMC) made by fast thixoforging is introduced. Thereby, prepregs consisting of laminated fiber woven fabrics and metal sheets or, alternatively, thermally sprayed metal coatings on ceramic fiber fabrics are used as preforms for an advanced thixoforging process for the manufacturing of Al-Si MMC components in mechanical engineering.

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Huo, Shiyu, Qun Yan, Xiang Gao, and Yu You. "Ceramic Matrix Composite Turbine Vane Thermal Simulation Test and Evaluation." International Journal of Turbo & Jet-Engines 37, no. 3 (August 27, 2020): 285–93. http://dx.doi.org/10.1515/tjj-2017-0048.

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AbstractCeramic Matrix Composites (CMCs) are primary candidates for advanced gas turbine engine application that require intense high temperature tests and validations. Before CMCs used in engine hot sections, a lot of tests need to be done, especially thermal test. A thermal test rig has been set up to simulate the engine turbine thermal environment. Propane gas is used to simulate the practical aviation fuel and compressed air with flow regulator is used as cooling media. The capabilities and limitations of the test facility have been calibrated and discussed in this paper. A CMC turbine vane with internal cooling path was tested on this burning rig. The results showed that the CMC vane could withstand the 1200 ℃ thermal cycling test but the coating was disappeared. It has been proved that such test rig and method could simulate the thermal boundary conditions of turbine vanes and blades.

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Silvestre, J., N. Silvestre, and J. de Brito. "An Overview on the Improvement of Mechanical Properties of Ceramics Nanocomposites." Journal of Nanomaterials 2015 (2015): 1–13. http://dx.doi.org/10.1155/2015/106494.

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Due to their prominent properties (mechanical, stiffness, strength, thermal stability), ceramic composite materials (CMC) have been widely applied in automotive, industrial and aerospace engineering, as well as in biomedical and electronic devices. Because monolithic ceramics exhibit brittle behaviour and low electrical conductivity, CMCs have been greatly improved in the last decade. CMCs are produced from ceramic fibres embedded in a ceramic matrix, for which several ceramic materials (oxide or non-oxide) are used for the fibres and the matrix. Due to the large diversity of available fibres, the properties of CMCs can be adapted to achieve structural targets. They are especially valuable for structural components with demanding mechanical and thermal requirements. However, with the advent of nanoparticles in this century, the research interests in CMCs are now changing from classical reinforcement (e.g., microscale fibres) to new types of reinforcement at nanoscale. This review paper presents the current state of knowledge on processing and mechanical properties of a new generation of CMCs: Ceramics Nanocomposites (CNCs).

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Zhao, Shuyuan, Qian Sun, Yumin Zhang, and Jin Jia. "Parametric Influences of Geometric Dimensions on High Temperature Mechanical Behaviors and Damage Mechanisms of Ceramic Matrix Composite and Superalloy Double Bolted Joints." International Journal of Aerospace Engineering 2022 (August 31, 2022): 1–16. http://dx.doi.org/10.1155/2022/7169123.

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Given multiple material performance advantages, ceramic matrix composite (CMC) material has become one of the most promising hot structural materials used for thermal protection system in hypersonic vehicles. Under harsh thermal exposure of vehicles in flight, the design of connection structure would be a critical issue in improving load-carrying efficiency and ensuring service safety of aircraft structures in service environments. However, little attention was paid on mechanical behavior and its factors affecting the mechanical property of CMC joining at elevated temperature. To address this concern, a 3D finite element model coupled with progressive damage analysis is carried out to predict high temperature tensile properties and failure behavior of single-lap, double-bolt CMC/superalloy joints assembled by two serial protruding-head bolts. In the implementation of progressive damage analysis of 2D plain-woven C/SiC composites, a user-defined subroutine UMAT including a nonlinear constitutive model, 3D Alvaro failure criterion and Tan’s material degradation rule were embedded into the general package ABAQUS® through Fortran program interface. A parametric study considering geometries of joints was performed to evaluate their resultant influence on high temperature tensile behavior and the associated damage mechanisms for the CMC/superalloy double-bolt joint. New findings were provided for full exploitation of high performance through geometric design of ceramic matrix composite hot structure for hypersonic aircraft.

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Irazu, Edgardo, Borja Izquierdo, Unai Alonso, and Franck Girot. "Influence of Cutting Parameters on Abrasive Machining of C/SiC Ceramic Matrix Composite." Key Engineering Materials 957 (October 2, 2023): 13–20. http://dx.doi.org/10.4028/p-7eoftk.

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Ceramic Matrix Composites (CMC) are becoming increasingly important in aeronautical and space applications due to their excellent mechanical properties and wear resistance at high temperatures. Abrasive processes are commonly used for CMC machining due to its high hardness. In this work, an experimental analysis of the influence of grinding parameters has been carried out. Namely, the effect of the variation of cutting speed and feed speed have been studied when grinding a Cf/SiC composite with diamond wheels. Forces were registered during the tests and workpiece quality was analyzed by means of optical techniques. Results show that higher feed rates increase normal force values, while higher cutting speeds lead to lower normal machining forces. Moreover, a relationship between grain aggressiveness and specific grinding energy was observed. Decreasing machining forces also helped to preserve surface integrity of the machined parts.

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Licciulli, Antonio, Antonio Chiechi, Daniela Diso, and Alfonso Maffezzoli. "Ceramic Composites for Automotive Friction Devices." Advances in Science and Technology 45 (October 2006): 1394–98. http://dx.doi.org/10.4028/www.scientific.net/ast.45.1394.

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Advanced braking devices can represent a promising application for ceramic matrix composites (CMC) with functional and structural properties. If the actual advanced braking materials could be at least partially replaced by CMCs, it might become the first consumer market for these materials. CMC containing three main phases, silicon carbide, graphite and carbon fibers were prepared. A systematic analysis of the processing-structure-properties relationship of the composite is carried out. In particular, silicon carbide provides the necessary hardness, whereas graphite is used for its lubricating properties, and carbon fibers are used as reinforcement. The samples, prepared using a reactive bonding technique, exhibited adequate mechanical properties, high resistance to thermal shocks and good stability after many thermal cycles. Morphological and structural investigations have been performed to optimize the content of each component. Preliminary tribological investigations are presented.

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Li, Baokuo, Sheng Huang, Huaixu Yan, Xiaobo Zhang, Kun Du, and Zhanxue Wang. "Modeling and Performance Analysis of Variable Cycle Engine with Ceramic Matrix Composite Turbine Blades." Aerospace 11, no. 11 (October 28, 2024): 886. http://dx.doi.org/10.3390/aerospace11110886.

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To meet the requirements of future aircraft for power systems, the turbine inlet temperatures of aero engines are gradually increasing. Ceramic matrix composite (CMC), with its higher thermal limit, has become the preferred material for the turbine blades of variable cycle engines (VCEs). However, the impact of CMC turbine blades on the performance of a VCE is still unknown. In this research project, the comprehensive cooling-efficiency characteristics of CMC are determined through a fluid–solid coupling calculation; a cooling calculation model for turbine blades is established, and cooling airflow solution and control technology (CSCT) for an air system is developed. Additionally, a VCE simulation model is established to analyze the influence of CMC turbine blades on the cooling airflow of the air system and the overall performance of the engine. The results show that, for the design condition, the CMC turbine blade can reduce the cooling airflow of the air system by approximately 10%, and the net thrust is increased by 6.07–7.98%. For the off-design conditions, with the CSCT, the specific fuel consumption can be reduced by 3.06–5.73% while ensuring that the engine net thrust remains unchanged. A comprehensive analysis of the performance for both the design point and off-design points indicates that the use of CMC for high-pressure turbine (HPT) guide vanes and rotor blades yields significant performance benefits, while the performance improvement from the use of CMC for low-pressure turbine (LPT) rotor blades is minimal.

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Bach, Christian, Frank Wehner, and Jan Sieder-Katzmann. "Investigations on an All-Oxide Ceramic Composites Based on Al2O3 Fibres and Alumina–Zirconia Matrix for Application in Liquid Rocket Engines." Aerospace 9, no. 11 (November 3, 2022): 684. http://dx.doi.org/10.3390/aerospace9110684.

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High performance ceramics, particularly Ceramic Matrix Composite (CMC) materials found their way into liquid rocket engines. Yet, so far, mainly carbide or nonoxide CMCs have been of interest. This paper explores the potential and challenges of oxide–oxide ceramic matrix composites (OCMCs) for application in rocket thrust chambers. Therefore, strength, leakage and hot gas tests are conducted with material samples. A particular focus lies on the application of coatings to seal the permeability inherent to the material. Furthermore, prototypes in the form of flame tubes, ceramic chambers with nozzles and ceramic chambers with graphite inlays are developed and investigated experimentally in test firings. The results show that a recrystallised glass of a Y-Al-Si-O compound can successfully create an impermeable coating of the OCMC without affecting its damag-tolerant behaviour. However, the prototype developments show that it is still very challenging to manufacture even slightly complex structures without critical failures. Nevertheless, OCMC structures of relatively simple geometries showed promising results in hot firings and could be used as a lightweight housing, while the inner contour of the chamber and nozzle are realised, e.g., by a graphite inlay of appropriate quality.

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Dimitrijevic, M. M., N. Tomic, B. Medjo, R. Jancic-Heinemann, M. Rakin, and T. Volkov-Husovic. "Modeling of the mechanical behavior of fiber-reinforced ceramic composites using finite element method (FEM)." Science of Sintering 46, no. 3 (2014): 385–90. http://dx.doi.org/10.2298/sos1403385d.

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Modeling of the mechanical behavior of fiber-reinforced ceramic matrix composites (CMC) is presented by the example of Al2O3 fibers in an alumina based matrix. The starting point of the modeling is a substructure (elementary cell) which includes on a micromechanical scale the statistical properties of the fiber, matrix and fiber-matrix interface and their interactions. The numerical evaluation of the model is accomplished by means of the finite element method. The numerical results of calculating the elastic modulus of the composite dependance on the quantity of the fibers added and porosity was compared to experimental values of specimens having the same composition.

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Karadimas, George, and Konstantinos Salonitis. "Ceramic Matrix Composites for Aero Engine Applications—A Review." Applied Sciences 13, no. 5 (February 26, 2023): 3017. http://dx.doi.org/10.3390/app13053017.

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Ceramic matrix materials have attracted great attention from researchers and industry due to their material properties. When used in engineering systems, and especially in aero-engine applications, they can result in reduced weight, higher temperature capability, and/or reduced cooling needs, each of which increases efficiency. This is where high-temperature ceramics have made considerable progress, and ceramic matrix composites (CMCs) are in the foreground. CMCs are classified into non-oxide and oxide-based ones. Both families have material types that have a high potential for use in high-temperature propulsion applications. The oxide materials discussed will focus on alumina and aluminosilicate/mullite base material families, whereas for non-oxides, carbon, silicon carbide, titanium carbide, and tungsten carbide CMC material families will be discussed and analyzed. Typical oxide-based ones are composed of an oxide fiber and oxide matrix (Ox-Ox). Some of the most common oxide subcategories are alumina, beryllia, ceria, and zirconia ceramics. On the other hand, the largest number of non-oxides are technical ceramics that are classified as inorganic, non-metallic materials. The most well-known non-oxide subcategories are carbides, borides, nitrides, and silicides. These matrix composites are used, for example, in combustion liners of gas turbine engines and exhaust nozzles. Until now, a thorough study on the available oxide and non-oxide-based CMCs for such applications has not been presented. This paper will focus on assessing a literature survey of the available oxide and non-oxide ceramic matrix composite materials in terms of mechanical and thermal properties, as well as the classification and fabrication methods of those CMCs. The available manufacturing and fabrication processes are reviewed and compared. Finally, the paper presents a research and development roadmap for increasing the maturity of these materials allowing for the wider adoption of aero-engine applications.

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Chou, Ke Ju, Hatsuhiko Usami, and Kazuki Enomoto. "Micro Abrasive Jet Machining of Silicon Carbide (SiC) Fiber Reinforced Ceramic Matrix Composite." Advanced Materials Research 126-128 (August 2010): 946–51. http://dx.doi.org/10.4028/www.scientific.net/amr.126-128.946.

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Abesive jet machining (AJM) of silicon carbide fiber reinforced silicon carbide ceramic composite (SiC/SiC CMC) was carried out with various size of silicon carbide fine abresives. A micro indentation experiment was connected to evaluate of maerial removal mechanism by the particle impact. Results showed that the machine rate was different depending on the particle size and that inteface fracture (debonding) has influenced on the material removal mechanim. Relationship between structure scale of the SiC/SiC CMC and the impact media size was discussed.

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Dhanasekar, S., Arul Thayammal Ganesan, Taneti Lilly Rani, Venkata Kamesh Vinjamuri, Medikondu Nageswara Rao, E. Shankar, Dharamvir, P. Suresh Kumar, and Wondalem Misganaw Golie. "A Comprehensive Study of Ceramic Matrix Composites for Space Applications." Advances in Materials Science and Engineering 2022 (September 8, 2022): 1–9. http://dx.doi.org/10.1155/2022/6160591.

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Ceramic matrix composites (CMCs) have grown in popularity as a material for a range of high as well as protection components, increasing the need to better understand the impacts of multiple machining methods. It is primarily composed of ceramic fibers embedded in the matrix. Ceramic materials, especially carbon fibers and carbon were used to create the matrix and fibers. These ceramics include a huge variety of non-metallic inorganic materials that are regularly utilized under high temperatures. The aircraft industry became revolutionized by this unique combination of materials, which made parts better resistant under extreme conditions as well as lighter than the earlier technology. The development, properties, and production of ceramic matrix composites, as well as space applications, are discussed in this article. Ceramic materials have an interesting set of properties, including great strength and stiffness under extremely high temperatures, chemical inertness, low density, etc. In CMC, ceramics are used in the matrix as well as reinforcement. The matrix material keeps things running smoothly while the reinforcement delivers unique special properties. Ceramic matrix composites are developed for applications that required high thermal and mechanical characteristics, which include nuclear power plants, aircraft, chemical plants, space structures, and transportation services. Even though advanced aircraft relies on high-performance propulsion systems, improving the total impulses over the total mass ratio for rocket engines becomes essential for improving their performance that demands reduced engine structural weight as well as higher component heat resistance. The evolution of new ultra-high-temperature composites having high-temperature resistance as well as low density that a substitute super alloy and refractory metal material has become so essential and laid the foundation for high-performance engine design. The benefits of continuous fiber- reinforced CMC with high-temperature engine designs have long been recognized as a better measure of a country’s ability to design and produce spacecraft, modern aircraft, and weapons. Ceramic matrix composites materials are used in various aircraft type engines, aircraft brake disks, high-temperature gas turbines components, slide bearing components, hot gas duct, flame holders and components for burners are made by using oxide CMCs.

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Zhang, Quan Ming. "Research on Ceramic Matrix Composites (CMC) for Aerospace Aplications." Advanced Materials Research 284-286 (July 2011): 324–29. http://dx.doi.org/10.4028/www.scientific.net/amr.284-286.324.

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The research on ceramic matrix composites and their applications in aerospace field were discussed in terms of their advantages and features, fabrication methods, domestic and foreign research progress, difficulties and key technologies to be solved, and future development trends and directions.

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Duffy, S. F., J. L. Palko, and J. P. Gyekenyesi. "Structural Reliability Analysis of Laminated CMC Components." Journal of Engineering for Gas Turbines and Power 115, no. 1 (January 1, 1993): 103–8. http://dx.doi.org/10.1115/1.2906663.

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For laminated ceramic matrix composite (CMC) materials to realize their full potential in aerospace applications design, methods and protocols are a necessity. This paper focuses on the time-independent failure response of these materials and presents a reliability analysis associated with the initiation of matrix cracking. It highlights a public domain computer algorithm that has been coupled with the laminate analysis of a finite element code and which serves as a design aid to analyze structural components made from laminated CMC materials. Issues relevant to the effect of the size of the component are discussed, and a parameter estimation procedure is presented. The estimation procedure allows three parameters to be calculated from a failure population that has an underlying Weibull distribution.

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Hackert, Alexander, Jonas H. M. Stiller, Johannes Winhard, Václav Kotlan, and Daisy Nestler. "Inductive Heating of Ceramic Matrix Composites (CMC) for High-Temperature Applications." Materials 17, no. 10 (May 7, 2024): 2175. http://dx.doi.org/10.3390/ma17102175.

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The inductive heating of a CMC susceptor for industrial applications can generate very high process temperatures. Thus, the behavior of a silicon carbide-based matrix with carbon-fiber-reinforced carbon (C/C-SiC) as a susceptor is investigated. Specifically, the influence of fiber length and the distribution of carbon fibers in the composite were investigated to find out the best parameters for the most efficient heating. For a multi-factorial set of requirements with a combination of filling levels and fiber lengths, a theoretical correlation of the material structure can be used as part of a digital model. Multi-physical simulation was performed to study the behavior of an alternating magnetic field generated by an inducing coil. The simulation results were verified by practical tests. It is shown that the inductive heating of a C/C-SiC susceptor can reach very high temperatures in a particularly fast and efficient way without oxidizing if it is ensured that a silicon carbide-based matrix completely encloses the fibers.

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43

Weiss, Roland. "CMC and C/C-SiC-Fabrication." Advances in Science and Technology 50 (October 2006): 130–40. http://dx.doi.org/10.4028/www.scientific.net/ast.50.130.

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Ceramic Matrix Composites (CMC) have a wide interest for high temperature applications. The materials can be modified by the selection of the matrix precursor as well as of the reinforcing materials. C/C-composites can be easily modified by post-treatments with silicon in order to acquire different tribological properties from good sliding behaviour up to braking systems only depending on the manufacturing technique of these materials. It will be demonstrated during the presentation that the manufacturing depends on one hand side on the material which has to be manufactured and on the other side on the structural component and the number of parts which are required. Furthermore, it will also be shown, that silicon treatments can be performed up to a full conversion of C/C materials creating a new family of monolithic ceramic materials. Within the presentation detailed information will be given on possible processing routes as well as the resulting physical and mechanical properties of the materials.

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Bonora, N., and G. Newaz. "Modeling Damage Evolution in a Hybrid Ceramic Matrix Composite Under Static Tensile Load." Journal of Engineering Materials and Technology 119, no. 4 (October 1, 1997): 401–7. http://dx.doi.org/10.1115/1.2812276.

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In this investigation, damage evolution in a unidirectional hybrid ceramic composite made from Nicalon and SiC fibers in a Lithium Aluminosilicate (LAS) glass matrix was studied. The static stress-strain response of the composite exhibited a linear response followed by load drop in a progressive manner. Careful experiments were conducted stopping the tests at various strain levels and using replication technique, scanning and optical microscopy to monitor the evolution of damage in these composites. It was observed that the constituents of the composite failed in a sequential manner at increasing strain levels. The matrix cracks were followed by SiC fiber failures near ultimate tensile stress. After that, the load drop was associated with progressive failure of the Nicalon fibers. Identification of these failure modes were critical to the development of a concentric cylinder model representing all three constituent phases to predict the constitutive response of the CMC computationally. The strain-to-failure of the matrix and fibers were used to progressively fail the constituents in the model and the overall experimental constitutive response of the CMC was recovered. A strain based analytical representation was developed relating stiffness loss to applied strain. Based on this formulation, damage evolution and its consequence on tensile stress-strain response was predicted for room temperature behavior of hybrid CMCs. The contribution of the current work is that the proposed strain-damage phenomenological model can capture the damage evolution and the corresponding material response for continuous fiber-reinforced CMCs. The modeling approach shows much promise for the complex damage processes observed in hybrid CMCs.

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Sun, Qian, Huifeng Zhang, Chuanbing Huang, and Weigang Zhang. "Fabrication of C/C–SiC–ZrB2 Ultra-High Temperature Composites through Liquid–Solid Chemical Reaction." Crystals 11, no. 11 (November 7, 2021): 1352. http://dx.doi.org/10.3390/cryst11111352.

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In this paper, we aimed to improve the oxidation and ablation resistance of carbon fiber-reinforced carbon (CFC) composites at temperatures above 2000 °C. C/C–SiC–ZrB2 ultra-high temperature ceramic composites were fabricated through a complicated liquid–solid reactive process combining slurry infiltration (SI) and reactive melt infiltration (RMI). A liquid Si–Zr10 eutectic alloy was introduced, at 1600 °C, into porous CFC composites containing two kinds of boride particles (B4C and ZrB2, respectively) to form a SiC–ZrB2 matrix. The effects and mechanism of the introduced B4C and ZrB2 particles on the formation reaction and microstructure of the final C/C–SiC–ZrB2 composites were investigated in detail. It was found that the composite obtained from a C/C–B4C preform displayed a porous and loose structure, and the formed SiC–ZrB2 matrix distributed heterogeneously in the composite due to the asynchronous generation of the SiC and ZrB2 ceramics. However, the C/C–SiC–ZrB2 composite, prepared from a C/C–ZrB2 preform, showed a very dense matrix between the fiber bundles, and elongated plate-like ZrB2 ceramics appeared in the matrix, which were derived from the dissolution–diffusion–precipitation mechanism of the ZrB2 clusters. The latter composite exhibited a relatively higher ZrB2 content (9.51%) and bulk density (2.82 g/cm3), along with lower open porosity (3.43%), which endowed this novel composite with good mechanical properties, including pseudo-plastic fracture behavior.

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Kaya, Cengiz, and Figen Kaya. "Processing and Characterization of Ultra-High Temperature Oxide Fiber-Reinforced Oxide Ceramic Matrix Composites with Improved Thermomechanical Properties." Key Engineering Materials 368-372 (February 2008): 1778–81. http://dx.doi.org/10.4028/www.scientific.net/kem.368-372.1778.

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A combined technique comprising electrophoretic deposition (EPD) and low-pressure infiltration was used for the fabrication of multi-layer woven mullite ceramic fabric reinforced alumina ceramic matrix composites (CMCs) for high temperature applications. Two different interface materials, NdPO4 and ZrO2 were synthesised and used for coating the woven ceramic fibres by EPD. The manufactured CMC components with suitable interface material are targeted for use at 1300-1400 oC in an oxidising atmosphere and have shown very good mechanical properties in multi-layer plate forms. Damage mechanisms, such as debonding, fibre fracture, delamination and matrix cracking within the composite plates subjected to flexural loading are analysed. It is shown that the composites with NdPO4 interface and 40 vol.% fibre loading have better mechanical properties in terms of strength and damage-tolerant behaviour. The final components produced are considered to be suitable for use as shroud seals and insulating layers for combustor chambers in aircraft engines.

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Ahmadi, Majid, Seyed Hadi Seyedin, and Seyed Vahid Seyedin. "Investigation of the mechanical performance of fiber-modified ceramic composites using finite element method." Tehnički glasnik 13, no. 3 (September 24, 2019): 173–79. http://dx.doi.org/10.31803/tg-20181006143504.

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Ceramic materials are widely used in impact safekeeping systems. Ceramic is a heterogeneous material; its characteristics depend considerably both on specifications of its ingredients and the material structure completely. The finite element method (FEM) can be a useful tool for strength computation of these materials. In this paper, the mechanical properties of the ceramic composites are investigated, and the mechanical performance modeling of fiber-fortified ceramic matrix composites (CMC) is expressed by the instance of aluminum oxide fibers in a matrix composite based on alumina. The starting point of the modeling is an infrastructure (primary cell) that contains a micromechanical size, the statistical analysis characteristics of the matrix, fiber-matrix interface, fiber, and their reciprocal influences. The numeral assessment of the model is done using the FEM. The numerical results of composite elastic modulus were computed based on the amount of the added fibers and the porosity was evaluated for empirical data of samples with a similar composition. Various scanning electron microscope (SEM) images were used for each sample to specify the porosity. Also, the unit cell method presumed that the porous ceramic substance is manufactured from an array of fundamental units, each with the same composition, material characteristic, and cell geometry. The results showed that when the material consists of different pores and fibers, the amount of Young’s modulus reduces with the increment of porosity. The linear correlation model of elasticity versus porosity value from experimental data was derived by MATLAB curve fitting. The experimental data from the mechanical test and numerical values were in good agreement.

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Mital, Subodh, Steven Arnold, Brett Bednarcyk, and Evan Pineda. "Micromechanics-Based Modeling of SiC/SiC Ceramic Matrix Composites and Structures." Recent Progress in Materials 05, no. 02 (June 20, 2023): 1–41. http://dx.doi.org/10.21926/rpm.2302025.

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The behavior and response of ceramic matrix composites (CMCs), in particular silicon carbide fiber reinforced silicon carbide matrix (SiC/SiC), is affected by many factors such as variation of fiber volume fraction, residual stresses resulting from processing of the composites at high temperature, random microstructures, and the presence of matrix flaws (e.g., voids, pores, cracks etc.) as well as general material nonlinearity and heterogeneity that occurs randomly in a composite. Residual stresses arising from the phase change of constituents are evaluated in this paper and it is shown that they do influence composite strength and need to be properly accounted for. Additionally, the microstructures (location of fiber centers, coating thickness etc.) of advanced CMCs are usually disordered (or random) and fiber diameter and strength typically have a distribution. They rarely resemble the ordered fiber packing (square, rectangular, or hexagonal) that is generally assumed in micromechanics-based models with periodic boundary conditions for computational expediency. These issues raise the question of how should one model such systems effectively? Can an ordered hexagonal packed repeating unit cell (RUC) accurately represent the random microstructure behavior? How many fibers need to be included to enable accurate representation? Clearly, the number of fibers within an RUC must be limited to insure a balance between accuracy and efficiency. NASA’s in-house micromechanics-based code MAC/GMC provides a framework to analyze such RUCs for the overall composite behavior and the FEAMAC computer code provides linkage of MAC/GMC to the commercial FEA code, ABAQUS. The appropriate level of discretization of the RUC as well as the analysis method employed, i.e., Generalized Method of Cells (GMC) or High Fidelity Generalized Method of Cells (HFGMC), is investigated in this paper in the context of a unidirectional as well as a cross-ply laminated CMC. Results including effective composite properties, proportional limit stress (an important design parameter) and fatigue are shown utilizing both GMC as well as HFGMC. Finally, a few multiscale analyses are performed on smooth bar test coupons as well as test coupons with features such as open-hole and double notches using FEAMAC. Best practices and guidance are provided to take these phenomena into account and keep a proper balance between fidelity (accuracy) and efficiency. Following these guidelines can account for important physics of the problem and provide significant advantages when performing large multiscale composite structural analyses. Finally, to demonstrate the multiscale analysis framework, a CMC gas turbine engine vane structure is analyzed involving a progressive damage model.

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Paknahad, Elham, and Andrew P. Grosvenor. "Investigation of CeTi2O6- and CaZrTi2O7-containing glass–ceramic composite materials." Canadian Journal of Chemistry 95, no. 11 (November 2017): 1110–21. http://dx.doi.org/10.1139/cjc-2016-0633.

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Glass–ceramic composite materials are being investigated for numerous applications (i.e., textile, energy storage, nuclear waste immobilization applications, etc.) due to the chemical durability and flexibility of these materials. Borosilicate and Fe–Al–borosilicate glass–ceramic composites containing brannerite (CeTi2O6) or zirconolite (CaZrTi2O7) crystallites were synthesized at different annealing temperatures. The objective of this study was to understand the interaction of brannerite or zirconolite-type crystallites within the glass matrix and to investigate how the local structure of these composite materials changed with changing synthesis conditions. Powder X-ray diffraction (XRD) and Backscattered electron (BSE) microprobe images have been used to study how the ceramic crystallites dispersed in the glass matrix. X-ray absorption near edge spectroscopy (XANES) spectra were also collected from all glass–ceramic composite materials. Examination of Ti K-, Ce L3-, Zr K-, Si L2,3-, Fe K-, and Al L2,3-edge XANES spectra from the glass–ceramic composites have shown that the annealing temperature, glass composition, and the loading of the ceramic crystallites in the glass matrix can affect the local environment of the glass–ceramic composite materials. A comparison of the glass–ceramic composites containing brannerite or zirconolite crystallites has shown that similar changes in the long range and local structure of these composite materials occur when the synthesis conditions to form these materials or the composition are changed.

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Thompson Odion Igunma, Adeoye Taofik Aderamo, and Henry Chukwuemeka, Olisakwe. "Ceramic matrix composites for corrosion-resistant next-generation nuclear reactor systems: A conceptual review of enhancements in durability against molten salt attack." Open Access Research Journal of Engineering and Technology 7, no. 2 (October 30, 2024): 001–15. http://dx.doi.org/10.53022/oarjet.2024.7.2.0055.

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Ceramic matrix composites (CMCs) are emerging as a key material class for enhancing corrosion resistance in next-generation nuclear reactor systems, particularly in high-temperature molten salt environments. These environments, critical for advanced nuclear reactors such as molten salt reactors (MSRs), present severe challenges, including aggressive chemical attacks that degrade traditional structural materials over time. This conceptual review explores the development and application of CMCs to improve the durability and corrosion resistance of nuclear reactors exposed to molten salt attacks. CMCs, which consist of ceramic fibers embedded in a ceramic matrix, offer significant advantages, such as high thermal stability, mechanical strength, and improved corrosion resistance compared to conventional materials. This review examines how CMCs can be tailored to withstand harsh operational conditions, with a focus on the selection of ceramic phases, fiber-matrix interactions, and innovative fabrication techniques that enhance their protective capabilities. Key challenges addressed include the optimization of composite design to resist molten salt corrosion, the effects of temperature on the material properties, and the long-term stability of CMCs under extreme conditions. Advances in surface treatments, coatings, and the development of hybrid CMC systems are also discussed, highlighting their potential to further enhance durability. The review outlines the use of advanced characterization techniques, such as high-temperature corrosion testing and in situ microscopy, to evaluate CMC performance in molten salt environments. Additionally, it identifies knowledge gaps in current research, emphasizing the need for long-term studies on CMC behavior under realistic reactor conditions. This review concludes by proposing future research directions and technological advancements required to integrate CMCs into next-generation nuclear reactor designs, aiming to improve system reliability and operational safety.

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Journal articles on the topic 'Ceramic Matrix Composite (CMC)'

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