Готові списки джерел за темами / Oxide Ceramic Matrix Composite

Добірка наукової літератури з теми "Oxide Ceramic Matrix Composite"

Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "Oxide Ceramic Matrix Composite"

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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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Анотація:
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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2

Kaya, Cengiz. "Current Status of Oxide Fibre-Reinforced Oxide Ceramic Matrix Composites for Gas Turbine Applications." Key Engineering Materials 434-435 (March 2010): 1–4. http://dx.doi.org/10.4028/www.scientific.net/kem.434-435.1.

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Recent developments in the processing, understanding and mechanical/thermomechanical properties of oxide fibre reinforced oxide ceramic matrix composites for high temperature applications are reported. Two dimensional composite plates and uni-directional tubular composite (so called mini-composite) specimens are successfully manufactured and their microstructure, matrix/ fiber interface as well as mechanical properties are examined. It is shown that the microstructural variations, such as porosity size and interface between fibre and matrix determine the fracture behaviour and high temperature performance of the composites. The optimised components produced are considered to be suitable for gas turbine applications.
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3

Balazsi, Katalin, Mónika Furkó, Piotr Klimczyk, and Csaba Balázsi. "Influence of Graphene and Graphene Oxide on Properties of Spark Plasma Sintered Si3N4 Ceramic Matrix." Ceramics 3, no. 1 (February 5, 2020): 40–50. http://dx.doi.org/10.3390/ceramics3010005.

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The sintering of ceramic matrix composites is usually carried out by raising the sintering temperature below the melting point of components. Spark plasma sintering (SPS) has the capability to densify ceramics at a relatively low temperature in a very short time. Two different additions, multilayered graphene (MLG) and graphene oxide (GrO), were added to Si3N4 ceramic matrix in various amount; 5 wt% and 30 wt%. The influence of reinforcing phase on final properties of spark plasma sintered Si3N4 composite was studied. The uniaxial-pressure-assisted SPS sintering resulted in a preferential alignment of both type of graphene in the Si3N4 ceramic matrix, leading to highly anisotropic properties with lower mechanical behavior but better tribological and electrical properties.
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Kaya, Figen. "Damage Detection in Fibre Reinforced Ceramic and Metal Matrix Composites by Acoustic Emission." Key Engineering Materials 434-435 (March 2010): 57–60. http://dx.doi.org/10.4028/www.scientific.net/kem.434-435.57.

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In this work damage micro-mechanisms of two different types of fibre reinforced composites are investigated by acoustic emission, AE. Ceramic based oxide fibre reinforced mullite matrix composite and metallic based SiC fibre reinforced titanium matrix composites exhibit different fracture mechanisms during loading and AE technique could pinpoint these damage mechanisms based on the AE responses detected simultaneously. The results show that in a ceramic matrix composite, the identification of fibre fracture and matrix cracking requires careful analysis of the AE data as both fibres and matrix break in brittle manner. Whereas the separation of fibre fracture from the ductile tearing of matrix ligaments could be easier in metallic based composites, such as titanium matrix composites.
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Guglielmi, P. O., G. F. Nunes, M. Hablitzel, Dachamir Hotza, and Rolf Janssen. "Production of Oxide Ceramic Matrix Composites by a Prepreg Technique." Materials Science Forum 727-728 (August 2012): 556–61. http://dx.doi.org/10.4028/www.scientific.net/msf.727-728.556.

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Анотація:
Ceramic matrix composites (CMCs) were developed to overcome the intrinsic brittleness and lack of reliability of monolithic ceramics. Their major advantages include high temperature capability, light weight, corrosion resistance and adequate damage tolerance. All-oxide Ceramic Matrix Composites (OCMCs) offer essential advantages with respect to long time stability in oxidizing atmospheres, when compared to their non-oxide counterparts. Nevertheless, there is at present almost no production concept which meets the requirements in view of cost and performance for these materials. This work aims at producing OCMCs by means of a more flexible production route. This is achieved by integrating well-known powder metallurgy routes with the prepreg technique, used at present for producing commercial high performance polymer matrix composites. The processing consists of the following steps: (a) infiltration of commercial alumina fiber fabrics (3M NextelTM610) with a liquid suspension of the matrix material; (b) lamination of the pre-infiltrated fiber textiles with a paraffin-based suspension for the formation of prepregs; (c) layup of prepregs; (d) warm-pressing for the consolidation of the green body; (e) debinding and (f) reaction bonding and/or sintering for synthesis of the oxide matrix. Pure alumina or Reaction Bonded Aluminum Oxide (RBAO) can be used as matrix materials and damage tolerance is achieved by the porous, weak-matrix approach. Microstructural analysis of a pure alumina composite fabricated by this route show good infiltration of fiber bundles and proves the good adhesion of prepregs during processing. Average strength value of 199 MPa in fiber direction is in good agreement with values presented in the literature for OCMCs produced by other techniques.
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Böttcher, Maike, Daisy Nestler, Jonas Stiller, and Lothar Kroll. "Injection Moulding of Oxide Ceramic Matrix Composites: Comparing Two Feedstocks." Key Engineering Materials 809 (June 2019): 140–47. http://dx.doi.org/10.4028/www.scientific.net/kem.809.140.

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Анотація:
Ceramic materials are suitable for use in the high temperature range. Oxide ceramics, in particular, have a high potential for long-term applications under thermal cycling and oxidising atmosphere. However, monolithic oxide ceramics are unsuitable for use in high-temperature technical applications because of their brittleness. Thin-walled, oxidation resistant, and high-temperature resistant materials can be developed by reinforcing oxide ceramics with ceramic fibres such as alumina fibres. The increase of the mechanical stability of the composites in comparison to the non-fibre reinforced material is of outstanding importance. Possible stresses or cracks can be derived along the fibre under mechanical stress or deformation. Components made of fibre-reinforced ceramic composites with oxide ceramic matrix (OCMC) are currently produced in manual and price-intensive processes for small series. Therefore, the manufacturing should be improved. The ceramic injection moulding (CIM) process is established in the production of monolithic oxide ceramics. This process is characterised by its excellent automation capability. In order to realise large scale production, the CIM-process should be transferred to the production of fibre-reinforced oxide ceramics. The CIM-process enables the production of complicated component shapes and contours without the need for complex mechanical post-treatment. This means that components with complex geometries can be manufactured in large quantities.To investigate the suitability of the injection moulding process for the production of OCMCs, two different feedstocks and alumina fibres (Nextel 610) were compounded in a laboratory-scale compounder. The fibre volume fractions were varied. In a laboratory-scale injection moulding device, microbending specimens were produced from the compounds obtained in this way. To characterise the test specimens, microstructure examinations and mechanical-static tests were done. It is shown that the injection moulding process is suitable for the production of fibre-reinforced oxide ceramics. The investigations show that the feedstocks used have potential for further research work and for future applications as material components for high-temperature applications in oxidising atmospheres.
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Kramb, Victoria A., Reji John, and Larry P. Zawada. "Notched Fracture Behavior of an Oxide/Oxide Ceramic-Matrix Composite." Journal of the American Ceramic Society 82, no. 11 (December 21, 2004): 3087–96. http://dx.doi.org/10.1111/j.1151-2916.1999.tb02207.x.

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Zhong, Jie, Dongling Yang, Shuangquan Guo, Xiaofeng Zhang, Xinghua Liang, and Xi Wu. "Rear Earth Oxide Multilayer Deposited by Plasma Spray-Physical Vapor Deposition for Envisaged Application as Thermal/Environmental Barrier Coating." Coatings 11, no. 8 (July 26, 2021): 889. http://dx.doi.org/10.3390/coatings11080889.

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Анотація:
SiC fiber-reinforced SiC ceramic matrix composites (SiCf/SiC CMCs) are being increasingly used in the hot sections of gas turbines because of their light weight and mechanical properties at high temperatures. The objective of this investigation was the development of a thermal/environmental barrier coating (T/EBC) composite coating system consisting of an environmental barrier coating (EBC) to protect the ceramic matrix composites from chemical attack and a thermal barrier coating (TBC) that insulates and reduces the ceramic matrix composites substrate temperature for increased lifetime. In this paper, a plasma spray-physical vapor deposition (PS-PVD) method was used to prepare multilayer Si–HfO2/Yb2Si2O7/Yb2SiO5/Gd2Zr2O7 composite coatings on the surface of SiCf/SiC ceramic matrix composites. The purpose of this study is to develop a coating with resistance to high temperatures and chemical attack. Different process parameters are adopted, and their influence on the microstructure characteristics of the coating is discussed. The water quenching thermal cycle of the coating at high temperatures was tested. The results show that the structure of the thermal/environmental barrier composite coating changes after water quenching because point defects and dislocations appear in the Gd2Zr2O7 and Yb2SiO5 coatings. A phase transition was found to occur in the Yb2SiO5 and Yb2Si2O7 coatings. The failure mechanism of the T/EBC composite coating is mainly spalling when the top layer penetrates cracks and cracking occurs in the interface of the Si–HfO2/Yb2Si2O7 coating.
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Echeverria Aparicio, Itsaso, David T. Fishpool, Virtudes Rubio Diaz, Robert A. Dorey, and Julie A. Yeomans. "Evaluation of polymer matrix composite manufacturing routes for production of an oxide/oxide ceramic matrix composite." Journal of the European Ceramic Society 42, no. 5 (May 2022): 2420–28. http://dx.doi.org/10.1016/j.jeurceramsoc.2021.12.059.

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Ma, Lian-Hua, Kun Zhang, Xiao-Dong Pan, and Wei Zhou. "A comparative study of the elasto-plastic properties for ceramic nanocomposites filled by graphene or graphene oxide nanoplates." Nanotechnology Reviews 11, no. 1 (January 1, 2022): 2584–94. http://dx.doi.org/10.1515/ntrev-2022-0150.

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Abstract As nanoscale reinforcements, the graphene and graphene oxide nanoplates exhibit distinct mechanical and physical properties. The determination of the effective elasto-plastic behavior of nanoplate/ceramic nanocomposites and the different filling effects of graphene and graphene oxide nanoplate deserve systematic investigation. In this work, we intend to uncover how the graphene and graphene oxide nanoplates affect the macroscopic elasto-plastic characteristics of ceramic matrix nanocomposites and what differences in both nanoplates enhancements. A homogenization model is first utilized for determining the effective elastic parameters of nanoplate/ceramic composite with a perfect interface. Then the slightly weakened interface model is introduced to characterize the sliding effects of nanoplates in a ceramic matrix, and the effective elastic parameters of such nanoplates filled composites incorporating the interfacial sliding effects are explicitly formulated. Furthermore, a nonlinear micromechanics model is developed to investigate the macroscopic elastoplasticity and the yield behavior of graphene and graphene oxide nanoplate-filled ceramic nanocomposites subjected to confining pressure. The filling effects of the two kinds of nanoplates on the mechanical properties of such nanocomposite are comparatively examined. The calculated results demonstrate that types of the nanoplates and the imperfect interfaces between nanoplates and ceramic matrix have significant influences on the effective elasto-plastic behaviors of the nanoplate composites.
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Дисертації з теми "Oxide Ceramic Matrix Composite"

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Antti, Marta-Lena. "All-oxide ceramic matrix composites." Doctoral thesis, Luleå, 2001. http://epubl.luth.se/1402-1544/2001/34/index.html.

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Marriner-Edwards, Cassian. "The development of fibre-reinforced ceramic matrix composites of oxide ceramic electrolyte." Thesis, University of Oxford, 2016. https://ora.ox.ac.uk/objects/uuid:3af11d08-c0d8-429b-8eab-d2befc83ea74.

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Flammable solvents contained in liquid electrolytes pose a serious safety risk when used in lithium batteries. Oxide ceramic electrolytes are a safer alternative, but suffer from inadequate mechanical properties and ionic conductivity. Thin electrolyte layers resolve the issue of conductance, but accentuate the detrimental mechanical properties of oxide ceramics. The presented work has investigated oxide ceramic electrolyte reinforcement in composite electrolytes for all-solid-state batteries. Fabricating oxide ceramic electrolytes with engineered microstructure enabled development of a reinforced composite. This approach is based on the formation of 3D- porous ceramics via stereolithography printing of polymer templates from designed cubic, gyroid, diamond and bijel architectures. The microstructural parameters of templates were analysed and modified using computational techniques. Infiltration of the prepared 3D-porous electrolyte with polymeric-fibre reinforcement created the reinforced composite electrolyte. The prepared ceramic composite showed excellent reproduction of the template microstructure, good retention of ionic conductivity and enhanced mechanical properties. The final composite was composed of NASICON-type Li1.6Al0.6Ge1.4(PO4)3 oxide ceramic electrolyte and epoxy and aramid fibre reinforcement. The gyroid architecture was computationally determined as having the optimal stress transfer efficiency between two phases. The printed gyroid polymer template gave excellent pore microstructure reproduction in ceramic that had 3D-interconnected porosity, high relative density and the most uniform thickness distribution. The ceramic matrix porosity allowed for complete infiltration of reinforcement by aramid and epoxy forming the fibre-reinforced ceramic matrix composite. The interpenetrating composite microstructure with ceramic and epoxy gave a flexural strength increase of 45.65 MPa compared to the ceramic. Unfortunately, the infiltration procedure of aramid-epoxy reinforcement did not realise the full tensile strength potential of aramid fibres.
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Dearn, Sophie Clare. "Development of a novel oxide-oxide ceramic matrix composite for high temperature structural applications." Thesis, University of Birmingham, 2015. http://etheses.bham.ac.uk//id/eprint/5924/.

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The introduction of ceramic matrix composites (CMCs) for structural applications in the hot section of a gas turbine provides many potential benefits over conventional alloy materials, including facilitating elevated operating temperatures. The development of an oxide-oxide CMC composed of commercially available Nextel 720 (3M) fibres within a porous alumina matrix was presented. A simple, low cost processing method involving slurry impregnation and subsequent consolidation and densification was developed, facilitating the production of dried pre-impregnated fabric (‘pre-preg’) that can be stored in ambient conditions. Detailed investigation into the effect of three types of PVA binder, the effect of 0-20wt% additions of an alumina precursor (ACH), the influence of a bimodal particle distribution and the effect of sintering at temperatures between 1100 and 1300°C on processing and mechanical properties was completed in order to optimise the material. The optimised composite material, composed of Nextel 720 fibres within a submicron alumina particle matrix with 10wt% ACH sintered at 1200°C, exhibited mean flexural strength >205MPa, short beam shear strength >12MPa and tensile strength >146MPa. These results were comparable to similar oxide CMCs previously reported, validating this material.
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Ludford, Nicholas Philip. "An investigation into the thermal aging of an all oxide ceramic matrix composite." Thesis, University of Surrey, 2005. http://epubs.surrey.ac.uk/843476/.

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The effect of thermal aging in air on a Nextel(TM) 720 aluminosilicate fibre reinforced alumina matrix material (N72O/AI2O3) has been investigated. Samples were aged at 1100oC for up to 4000 hours as well as for 200 hours at 1100°C, 1200°C, 1300°C, 1400°C and 1480°C. On completion of the thermal aging treatments, the microstructures of the samples were characterised, principally using scanning and transmission electron microscopy. The mechanical properties of the material, flexural strength, Young's modulus and relative toughness, after aging were investigated using three point flexural testing. The as-received material was found to contain many voids and a large quantity of cracking that are believed to arise from in-complete matrix infiltration and green body production, respectively, during manufacture. It was found that the material does not meet the original proposed design criteria for this class of material. Initial results indicate that the 1100°C thermal aging treatment for up to 2000 hours has no detectable effect on the microstructure or properties of the material. After aging at 1100°C for 4000 hours, changes were detected in the material suggesting that prolonged thermal exposure of the material does have an effect on its properties, specifically a reduction in sample thickness indicating that the matrix may have densified slightly and a small increase in modulus and loss of aluminium from the fibre. In contrast, much shorter exposures to higher temperatures lead to significant changes to the microstructure, principally in terms of the reduction in porosity and grain growth in the matrix regions and an embrittlement of the material from an aging temperature of 1300°C, such that the material behaved as a monolithic ceramic after aging at 1480°C. Aging at 1200°C and above was found to cause a progressive decrease in the material thickness indicating a densification of the material. The fibre architecture was found to restrict densification in the plane of the fibre reinforcement. The mechanical properties of the material aged for 200 hours at 1200°C appear unaffected by the thermal aging. The aging of material at 1300°C was found to increase the Young's modulus to a maximum value after aging at 1400°C. Aging at 1480°C appeared to cause a slight decrease in the Young's modulus of the material. Aging of the material at 1300°C and above was found to cause a continuing reduction in the flexural strength of the material until a minimum value was reached after aging at 1480°C. A change in the microstructure of the fibre was initially observed after aging at 1300°C and was more pronounced after aging at 1400°C and 1480"C. A progressive growth of elongated alumina grains in the fibres was observed to occur as the meta-stable aluminium-rich mullite transformed to a silicon-rich mullite within the fibre. After aging at 1480°C the fibre was also observed to contain significant quantities of porosity. Furthermore, the fibre reinforcement appears to have lost aluminium, possibly to the matrix. The results of this investigation have found that the material is stable for aging periods of 2000 hours at 1100°C and for up to 200 hours at 1200°C. Whilst aging regimes of over 2000 hours at 1100°C may be acceptable, evidence has been found to suggest that the material is changing.
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Mansour, Rabih. "Mode I Interlaminar Fracture Properties of Oxide and Non-Oxide Ceramic Matrix Composites." University of Akron / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=akron1494248628194216.

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Vazquez, Calnacasco Daniel. "All-Oxide Ceramic Matrix Composites : Thermal Stability during Tribological Interactions with Superalloys." Thesis, Luleå tekniska universitet, Materialvetenskap, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-85513.

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The challenges faced in today’s industry require materials capable of working in chemically aggressive environments at elevated temperature, which has fueled the development of oxidation resistant materials. All-Oxide Ceramic Matrix Composites (OCMC) are a promising material family due to their inherent chemical stability, moderate mechanical properties, and low weight. However, limited information exists regarding their behavior when in contact with other high-temperature materials such as superalloys. In this work three sets of tribological tests were performed: two at room temperature and one at elevated temperature (650 °C). The tests were performed in a pin-on-disk configuration testing Inconel 718 (IN-718) pins against disks made with an aluminosilicate geopolymeric matrix composite reinforced with alumina fibers (N610/GP). Two different loads were tested (85 and 425 kPa) to characterize the damage on both materials. Results showed that the pins experienced ~ 100 % wear increase when high temperature was involved, while their microstructure was not noticeably affected near the contact surface. After high temperature testing the OCMC exhibited mass losses two orders of magnitude higher than the pins and a sintering effect under its wear track, that led to brittle behavior. The debris generated consists of alumina and suggests a possible crystallization of the originally amorphous matrix which may destabilize the system. The data suggests that while the composite’s matrix is stable, wear will not develop uncontrollably. However, as soon as a critical load/temperature combination is attained the matrix is the first component to fail exposing the reinforcement to damage which drastically deteriorates the integrity of the component.
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Hunt, Michael Patrick. "Pressureless Densification of Alumina - Titanium Diboride Ceramic Matrix Composites." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/31326.

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The research focus was to determine diffusion mechanisms responsible for densification behavior of SHS produced Al2O3/TiB2 Ceramic Matrix Composites (CMCs). Previous research has shown SHS produced Al2O3/TiB2 composites exhibited unique microstructural properties that contributed to high strength, fracture toughness, and hardness properties. Pressureless densification of SHS produced Al2O3/TiB2 composites would provide a cost savings because the equipment for pressureless densification is less expensive and less complicated than equipment required for densification with pressure. Models for sintering of CMCs and calculation of Sintering Time Constants (STC) were used to predict the densification behavior of the SHS produced Al2O3/TiB2 composite. The Levin, Dirnfeld, Shwam equation was used to determine the Rate Controlling Diffusion Mechanism (RCDM) and activation energy for sintering. X-Ray Diffraction (XRD) analysis of the as-milled reaction product powder revealed the presence of an aluminum borate (Al18B4O33) as a third phase, as well as, in pressureless heat treated samples. Based on experimental results and analysis, it seemed possible the Al18B4O33 compound may have formed by reaction of Al2O3 with TiB2 along their interfaces. Aluminum borates have been observed to form Al18B4O33 (s) + B2O3 (l) at temperatures above 1000°C. The RCDM for densification of SHS produced Al2O3/TiB2 was found to be liquid phase diffusion with volume diffusion also likely being active during densification. In addition, Al18B4O33 seemed to be the preferred compound formed during oxidation. Further research should be performed to control formation of Al18B4O33; as well as, on the oxidation behavior of the SHS produced Al2O3/TiB2.
Master of Science
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8

AKRAM, MUHAMMAD YASIR. "Giunzione di compositi a matrice ceramica a base ossidica." Doctoral thesis, Politecnico di Torino, 2019. http://hdl.handle.net/11583/2751274.

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9

Shamsudin, Roslinda. "Directed melt oxidation of ceramic matrix composites : the effect of oxide dopants and particulate reinforcements." Thesis, University of Sheffield, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.301283.

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Şahin, Erdem Çiftçioğlu Muhsin. "Synthesis and characterization of hydroxyapatite-alumina-zirconia biocomposites/." [s.l.]: [s.n.], 2006. http://library.iyte.edu.tr/tezler/master/malzemebilimivemuh/T000548.pdf.

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Анотація:
Thesis (Master)--İzmir Institute Of Technology, İzmir, 2006.
Keywords: Hydroxiapatites, alumina ceramic, zirconium oxide, urea, precipitations. Includes bibliographical references (leaves. 73-75).
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Книги з теми "Oxide Ceramic Matrix Composite"

1

Pearce, David Henry. Fabrication and evaluation of an oxide-oxide ceramic matrix composite. Birmingham: University of Birmingham, 1996.

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2

Saruhan, Bilge. Oxide-Based Fiber-Reinforced Ceramic-Matrix Composites. Boston, MA: Springer US, 2003. http://dx.doi.org/10.1007/978-1-4615-0319-4.

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3

Oxide-based fiber-reinforced ceramic-matrix composites: Principles and materials. Boston: Kluwer Academic Publishers, 2003.

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4

R, Warren, ed. Ceramic-matrix composites. London: Blackie, 1992.

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5

Ceramic matrix composites. 2nd ed. Boston: Kluwer Academic, 2003.

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6

Ceramic matrix composites. London: Chapman & Hall, 1993.

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7

M, Sheppard Laurel, and Business Communications Co, eds. Ceramic matrix composites. Norwalk, CT: Business Communications Co., 2000.

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8

I, Trefilov V., ed. Ceramic- and carbon-matrix composites. London: Chapman & Hall, 1995.

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9

Hull, David R. Plasma etching a ceramic composite. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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10

R, Shan Ashwin, and Lewis Research Center, eds. Probabilistic modeling of ceramic matrix composite strength. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Частини книг з теми "Oxide Ceramic Matrix Composite"

1

Keller, Kristin A., George Jefferson, and Ronald J. Kerans. "Oxide-Oxide Composites." In Ceramic Matrix Composites, 236–72. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2014. http://dx.doi.org/10.1002/9781118832998.ch8.

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Ruggles-Wrenn, Marina B. "Environmental Effects on Oxide/Oxide Composites." In Ceramic Matrix Composites, 293–333. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2014. http://dx.doi.org/10.1002/9781118832998.ch10.

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Lange, F. F., Timothy C. Radsick, and Magnus Holmquist. "Oxide/Oxide Composites: Control of Microstructure and Properties." In High Temperature Ceramic Matrix Composites, 585–99. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch90.

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Newman, Bronwen, and Wolfgang Schäfer. "Processing and Properties of Oxide/Oxide Composites for Industrial Applications." In High Temperature Ceramic Matrix Composites, 600–609. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch91.

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Frieß, M., and W. Krenkel. "Long Fiber Reinforced Damage-Tolerant Oxide/Oxide CMCs with Polysiloxanes." In High Temperature Ceramic Matrix Composites, 616–21. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch93.

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Lincoln, J., B. Jackson, A. Barnes, A. R. Beaber, and L. Visser. "Oxide-Oxide Ceramic Matrix Composites - Enabling Widespread Industry Adoption." In Ceramic Transactions Series, 401–12. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2017. http://dx.doi.org/10.1002/9781119407270.ch38.

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Wilson, D. M. "New High Temperature Oxide Fibers." In High Temperature Ceramic Matrix Composites, 1–12. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch1.

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Ulyanova, Tatiana, Ludmila Titova, and Nikolai Krut'ko. "Polycomponent Aluminium Oxide-Based Fibres." In High Temperature Ceramic Matrix Composites, 22–28. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch4.

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Mühlratzer, August, and Martin Leuchs. "Applications of Non-Oxide CMCs." In High Temperature Ceramic Matrix Composites, 288–98. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch46.

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Mileiko, S. T., V. M. Kiiko, A. A. Kolchin, and V. N. Kurlov. "Oxide Fibers Produced by Internal Crystallization Method and their Usage in Oxide-Matrix Composites." In High Temperature Ceramic Matrix Composites, 633–38. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch96.

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Тези доповідей конференцій з теми "Oxide Ceramic Matrix Composite"

1

Razzell, Anthony G., Ludovic Molliex, Magnus Holmquist, and Olivier Sudre. "Oxide/Oxide Ceramic Matrix Composites in Gas Turbine Combustors." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-030.

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Анотація:
Gas turbine combustor concepts designed to give improved control of NOx emissions require the usage of hot uncooled walls. The main material properties needed in this application include mechanical and chemical stability at temperatures in excess of 1400°C for long times (>10 000 hours). Composites made from single crystal oxide fibre reinforced oxide with a compatible high temperature stable weak oxide interphase are potential candidate materials to meet these requirements. Alumina was chosen as a model material, unidirectional and 2D composites were processed and a suitable weak zirconia interphase was designed. The process was scaled-up to make production of larger panels and components possible. Mechanical testing was carried out at room temperature to characterise the performance of the material in the as produced and thermally aged condition. Room temperature mechanical properties compared well with other current ceramic composites and excellent high temperature stability was demonstrated. The applicability of the composite as a material for uncooled combustor walls is to be further assessed by evaluation in a combustor test rig. Results from computational fluid dynamics and finite element calculations as well as results from combustor rig tests of monolithic and composite ceramic tiles will be presented.
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2

Go¨ring, Ju¨rgen, Bernd Kanka, Martin Schmu¨cker, and Hartmut Schneider. "A Potential Oxide/Oxide Ceramic Matrix Composite for Gas Turbine Applications." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38836.

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WHIPOX® (Wound Highly Porous Oxide CMCs) are oxide/oxide composites which are composed of highly porous alumino silicate or alumina matrices and of alumino silicate (Nextel 720, 3M) or alumina (Nextel 610, 3M) fibers. The materials are fabricated by a computer-controlled winding technique, developed at DLR. After eventual forming and joining steps, the green prepegs are pressureless sintered in air at 1300°C. The high temperature behavior of the CMCs is mainly controlled by the thermo-mechanical properties of the oxide fibers. For long-term use (>10,000 h) an application limit for the composite of about 1100°C is expected. It can, however, be improved by external thermal barrier coatings up to a maximum surface temperature of 1300°C. Gas burner tests show that the composites are extremely resistant against thermal fatigue. Therefore it is a material with a high potential for the use under the long-term high temperature conditions of gas turbine engines.
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Szweda, Andy, Steve Butner, John Ruffoni, Carlos Bacalski, Jay Lane, Jay Morrison, Gary Merrill, et al. "Development and Evaluation of Hybrid Oxide/Oxide Ceramic Matrix Composite Combustor Liners." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68496.

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Oxide/Oxide Ceramic Matrix Composites (CMCs) are an attractive class of materials for gas turbine hot section applications. The oxide fiber reinforcement and inherent matrix porosity contributes to favorable fracture toughness and thereby enhanced resistance against impact by foreign objects. Also, the oxide composition ensures superior environmental resistance against accelerated attack by corrosive species in the gas turbine hot section and resulting surface recession typically observed in silicon-based ceramic monolithic and composite materials. Under a program sponsored by the US National Institute of Standards and Technology (NIST) a hybrid oxide/oxide CMC system has been developed with potential application for stationary gas turbine hot section components. COI Ceramics, Inc. has fabricated subscale and full scale combustor liners which have been evaluated in rig and engine testing at Solar, and in field testing in a Solar Centaur® 50S engine at a commercial end user site. Following the conclusion of the NIST program in June 2003 the engine field testing is being continued under a Solar-led program sponsored by the US Dept. of Energy (DOE). As of November 2004, a hybrid oxide/oxide CMC outer combustor liner has accumulated 12,582 field test hours with 63 starts and an extensive material experience base has been developed. The paper will summarize the progress to-date for this hybrid CMC combustor liner development and demonstration, including selected fabrication approach, NDE, and rig/engine test experience.
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4

Ruggles-Wrenn, M. B., and S. R. Hilburn. "Creep in Interlaminar Shear of an Oxide/Oxide Ceramic Matrix Composite at Elevated Temperature." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-44034.

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Creep behavior in interlaminar shear of an oxide-oxide ceramic composite was evaluated at 1100°C in laboratory air and in steam environment. The composite (N720/AS) consists of a porous aluminosilicate matrix reinforced with laminated, woven mullite/alumina (Nextel™720) fibers, has no interface between the fiber and matrix, and relies on the porous matrix for flaw tolerance. The interlaminar shear properties were measured. The interlaminar shear strength (ILSS) was determined as 7.6 MPa. The creep behavior was examined for interlaminar shear stresses in the 2–6 MPa range. Primary and secondary creep regimes were observed in all tests conducted in air and in steam. Tertiary creep was noted in tests performed at 6 MPa. Creep run-out defined as 100 h at creep stress was not achieved in any of the tests. Larger creep strains and higher creep strain rates were produced in steam. However, the presence of steam had a beneficial effect on creep lifetimes. Composite microstructure, as well as damage and failure mechanisms were investigated.
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5

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." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68420.

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Solar Turbines Incorporated (Solar) under U.S. government sponsored programs has been evaluating ceramic matrix composite (CMC) combustor liners in test rigs and Solar Centaur® 50S engines since 1992. The objective was 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 1997 and by the end of 2004, over 67,000 operating hours have been accumulated on SiC/SiC and oxide/oxide CMC liners. NOx and CO emissions measured were < 15 ppmv and < 10 ppmv, respectively. Long test durations of 15,144 hrs and 13,937 hrs have been logged for SiC/SiC liners with protective environmental barrier coatings (EBCs). An oxide/oxide CMC liner with a Friable Graded Insulation (FGI) coating has been tested for 12,582 hrs. It was observed that EBCs significantly improve SiC/SiC CMC liner life. The basic three-layer EBC consists of consecutive layers of Si, mullite, and barium strontium aluminum silicate (BSAS). The durability of the baseline EBC can be improved by mixing in 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 (MI) SiC/SiC CMCs have improved durability compared to SiC/SiC CMCs fabricated by Chemical Vapor Infiltration (CVI) 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. Early results indicate that oxide/oxide CMCs with protective FGI show relatively minor degradation under Centaur 50S 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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6

Kedir, Nesredin, David Faucett, Luis Sanchez, and Sung R. Choi. "Foreign Object Damage in an Oxide/Oxide Ceramic Matrix Composite (CMC) Under Prescribed Tensile Loading." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-58058.

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Foreign object damage (FOD) behavior of an N720/alumina oxide/oxide ceramic matrix composite (CMC) was characterized at ambient temperature by using spherical projectiles impacted at velocities ranging from 100 to 350 m/s. The CMC targets were subject to ballistic impact at a normal incidence angle while being loaded under different levels of tensile loading in order to simulate conditions of rotating aeroengine airfoils. The impact damage of frontal and back surfaces was assessed with respect to impact velocity and load factor. Subsequent post-impact residual strength was also estimated to determine quantitatively the severity of impact damage. Impact force was predicted based on the principles of energy conservation.
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Choi, Sung R., Donald J. Alexander, and Robert W. Kowalik. "Foreign Object Damage in an Oxide/Oxide Composite at Ambient Temperature." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50505.

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Foreign object damage (FOD) behavior of an oxide/oxide (N720/AS) ceramic matrix composite (CMC) was determined at ambient temperature using impact velocities ranging from 100 to 400 m/s by 1.59-mm diameter steel-ball projectiles. Two different support configurations of target specimens were used: fully supported and partially supported. The degree of post-impact strength degradation increased with increasing impact velocity, and was greater in a partially supported configuration than in a fully supported one. For the fully supported configuration, frontal contact stress played a major role in generating composite damage, while for the partially supported case both frontal contact and backside flexure stresses were the combined sources of damage generation. The oxide/oxide composite was able to survive high energy (∼1.3 J) impacts without complete structural failure. The degree of relative post-impact strength degradation of the oxide/oxide composite was similar to that of an advanced SiC/SiC composite observed from a previous study, regardless of the type of specimen support. Like the SiC/SiC composite, impact-damage tolerance was greater in the oxide/oxide than in monolithic silicon nitride ceramics for impact velocities >300 m/s.
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8

Holmquist, Magnus, Robert Lundberg, Tony Razzell, Olivier Sudre, Ludovic Molliex, and Jan Adlerborn. "Development of Ultra High Temperature Ceramic Composites for Gas Turbine Combustors." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-413.

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All-oxide ceramic composites as a material with potential for long life-time applications at temperatures in the 1400–1600°C range in combustion environments were studied. The properties of available polycrystalline and single crystal oxide fibres were summarised. The literature on stable weak interfaces in all-oxide composites was reviewed. Composites with single crystal fibres, a polycrystalline matrix of the same material as the fibres, and a compatible high temperature stable weak oxide interphase was suggested to be the most promising approach. Recent progress in an ongoing European project aiming at development, scale-up and property evaluation of all-oxide composites is reported. The composite will be applied to a simple prototype combustor tile and tested in a combustor rig.
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Bao, Y., D. T. Gawne, and T. Zhang. "The Influence of Matrix Phase Viscosity on the Plasma-Spray Deposition of Silicon-Nitride Composite Coatings." In ITSC2003, edited by Basil R. Marple and Christian Moreau. ASM International, 2003. http://dx.doi.org/10.31399/asm.cp.itsc2003p0263.

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Abstract Non-oxide ceramics, such as silicon nitride, have a unique combination of high strength, toughness, wear resistance, thermal and chemical stability. However, the use of these materials as thick protective coatings on engineering components has been severely restricted by their decomposition behavior. Silicon nitride, for instance, does not melt but decomposes at ~1900oC and so thermal spraying of pure silicon nitride powder is impracticable. A limited amount of research has been carried out on depositing silicon nitride in various metallic or ceramic matrix materials but none have produced adequate coating microstructures or coating properties. This paper concerns the design of oxide matrix systems for silicon nitride composite coatings. A quantitative model is developed for the viscous flow of two-phase feedstock particles on impact with the substrate and is applied to the deposition of silicon nitride – ceramic matrix coatings. A number of matrix systems are investigated including a series of yttria-alumina and yttria-alumina -silica compositions. The research shows that the oxide matrices successfully protect the silicon nitride from decomposition but that the matrix composition and particle loading have a critical influence on splat flow and coating quality.
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10

Kibsey, Mitch, and Xiao Huang. "Development and Oxidation Test of Metal Mesh Reinforced Ceramic Composite Material." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36827.

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As part of an ongoing research development at Carleton University in ceramic matrix composites (CMCs) for high-temperature gas turbine applications, it was recognized that the performance of an oxide matrix could be improved by incorporating a metal reinforcement material. For this reason, a low cost CMC was created by reinforcing a yttria-stabilized zirconia (7YSZ) ceramic matrix with a Hastelloy X (HX) wire mesh. The CMC was manufactured by coating the HX mesh with a NiCrAlY bond coat, and then 7YSZ ceramic matrix, both using plasma spraying. The bond coat was employed to improve bonding and also to act as an oxygen diffusion barrier. In order to evaluate the performance of the HX/7YSZ composite at high temperatures, isothermal and cyclic oxidation tests were carried out for 1000 hours at 1050°C. The results showed that oxidation resistance was improved by vacuum heat treatment prior to testing due to the formation of stable thermally grown oxides (TGO) on the NiCrAlY bond coat. In the cyclic oxidation test, differences in thermal expansion coefficients caused cracking at interfaces between mesh/bond coat and bond coat/7YSZ. Minimizing the effect of thermal expansion by better material combination, as well as modifying manufacturing methods will allow for improved performance of metal mesh reinforced CMCs.
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Звіти організацій з теми "Oxide Ceramic Matrix Composite"

1

Bonnell, Dawn A. Interface Chemical Modification for Property Control of Oxide Reinforced Ceramic Matrix Composites. Fort Belvoir, VA: Defense Technical Information Center, October 2000. http://dx.doi.org/10.21236/ada383580.

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2

Chen, I.-Wei. Final technical report to Department of Energy, Basic Energy Sciences. ''Oxide ceramic alloys and microlaminates'' (1996-1999) and ''Low temperature processing and kinetics of ceramics and ceramic matrix composites with large interfacial areas'' (1999-2000). Office of Scientific and Technical Information (OSTI), March 2001. http://dx.doi.org/10.2172/808312.

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3

Sankar, J., and A. D. Kelkar. 'Mechanical Behavior Investigation of Advanced Ceramic Matrix Composite Materials'. Fort Belvoir, VA: Defense Technical Information Center, February 1995. http://dx.doi.org/10.21236/ada319913.

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4

R.G. Quinn. Thermal Diffusivity and Conductivity in Ceramic Matrix Fiber Composite Materials - Literature Study. Office of Scientific and Technical Information (OSTI), May 2000. http://dx.doi.org/10.2172/821297.

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5

Morrison, Jay. Ceramic Matrix Composite Advanced Transition for 65% Combined Cycle Efficiency Turbines - Final Report. Office of Scientific and Technical Information (OSTI), August 2018. http://dx.doi.org/10.2172/1492685.

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6

White, Kenneth W. Modeling of Failure in Monolithic and Ceramic Matrix Composite Under Static and Cyclic Loading. Fort Belvoir, VA: Defense Technical Information Center, July 2004. http://dx.doi.org/10.21236/ada430835.

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7

Choi, Sung R., and Donald J. Alexander. Foreign Object Damage by Steel Ball Projectiles in a SiC/SiC Ceramic Matrix Composite at Ambient and Elevated Temperatures. Fort Belvoir, VA: Defense Technical Information Center, April 2008. http://dx.doi.org/10.21236/ada481757.

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"A New Class of Creep Resistant Oxide/Oxide Ceramic Matrix Composites". Office of Scientific and Technical Information (OSTI), March 2007. http://dx.doi.org/10.2172/927776.

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