Relevant bibliographies by topics / Ceramic Matrix Composite (CMC)

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  2. Dissertations / Theses
  3. Books
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Academic literature on the topic 'Ceramic Matrix Composite (CMC)'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 January 2025

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Journal articles on the topic "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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Dissertations / Theses on the topic "Ceramic Matrix Composite (CMC)"

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GIANCHANDANI, PARDEEP KUMAR. "Joining of Ceramics and Ceramic Matrix Composites (CMC) for Aerospace and Energy Applications." Doctoral thesis, Politecnico di Torino, 2018. http://hdl.handle.net/11583/2711092.

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SiC-based ceramics and composites (SiC, C/SiC & SiC/SiC) are more and more extensively used as advanced materials for aerospace and energy applications. Existing applications are expanding continuously and require advanced materials, design and joining technologies. The objective of this thesis was to join SiC-based ceramic matrix composites (CMC), ceramics (SiC, Mullite, Alumina) and SiC-based ceramic foams for aerospace and energy applications. The research was aimed to develop strong, oxidation resistant and high temperature stable joints. A novel joining technique defined “RM-Wrap” (RM=Mo, Nb, Ta, W Refractory Metals) has been developed within this thesis. The developed technique is a novel brazing technology named RM-Wrap after the metal used as a wrap to contain one or more silicon foils (e.g. Mo-Wrap when a Mo wrap is used to contain a Si foil). It is a pressure-less joining technology performed at 1450 oC, under an inert environment (Argon flow). Joining materials are in-situ formed composites made of refractory metals silicides (MoSi2, NbSi2, TaSi2 and WSi2) embedded in a silicon matrix. RM-Wrap is a highly tailorable joining technique: the quantity of each phase can be modified and more than one refractory metals can be used together. RM-Wrap has been very effective in joining both coated and uncoated CMC, porous and non-porous materials: ceramics (oxide and non-oxide), CMC (SiC-based) and highly porous substrates (SiC foams) having porosity higher than 80% have been soundly joined. vii The joint morphology (interphase and interface) and elemental composition of the joining material was investigated in detail using FESEM and EDS which showed uniform, continuous and crack free joints. XRD investigation confirms the formation of metal silicides. Oxidation resistance of joints was carried out at 1100 oC for 30 minutes (for CMC joints) and 6 hours (for monolithic ceramic joints) in the air; prior and post oxidation examination of joint morphology showed no morphological change and joints remained firmly joined. Sandwich structures have been developed by Mo-wrap joining two C/SiC as “skins” to the “core” SiC foam. Sandwich structures were tested for thermal shock resistance from RT to 1100 oC in the air for 2 minutes. Three cycles on a single sandwich structure were performed, which remained joined and the joining material composition unchanged. Joints were mechanically tested in three different modes (i) compression, (ii) tensile and (iii) torsion. Joint strength was higher than the interlaminar shear strength of composites as the fracture was always observed in composites. In case of monolithic ceramic (SiC) a mixed failure (cohesive and adhesive) was found, which suggest that the joint strength is comparable to ceramic one. Micro- and nanoindentation tests were also carried out on joining materials.
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Miller, Ian Timothy. "Probabilistic finite element modeling of aerospace engine components incorporating time-dependent inelastic properties for ceramic matrix composite (CMC) materials." Akron, OH : University of Akron, 2006. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=akron1144941702.

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Thesis (M.S.)--University of Akron, Dept. of Mathematics, 2006.
"May, 2006." Title from electronic thesis title page (viewed 11/29/2007) Advisor, Vinod Arya; Co-Advisor, Ali Hajjafar; Faculty reader, Shantaram S. Pai; Department Chair, Kevin Kreider; Dean of the College, Ronald F. Levant; Dean of the Graduate School, George R. Newkome. Includes bibliographical references.
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Quintero, Badillo Jorge R. "Non-destructive Evaluation of Ceramic Matrix Composites at High Temperature using Laser Ultrasonics." University of Cincinnati / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1511800640467908.

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Mathieu, Sylvain. "Modélisation du comportement mécanique lors du procédé de mise en forme et pyrolyse des interlocks CMC." Thesis, Lyon, INSA, 2014. http://www.theses.fr/2014ISAL0115/document.

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La simulation des procédés de production des composites à renforts tissés est un enjeu majeur pour les industries de pointe, où leur utilisation s’intensifie. La maitrise des procédés d’obtention des composites à matrice et fibres en céramique, notamment les étapes de mise en forme et de pyrolyse, s’avère primordiale. La connaissance et la simulation du comportement mécanique aux différentes étapes est nécessaire pour optimiser les performances des pièces finales. Deux approches de modélisation macroscopique des renforts tissés épais de composite sont détaillées : une approche continue classique et une approche semi-discrète. Pour cela, une loi de comportement hyperélastique initialement orthotrope est développée. Cette loi est basée sur l’observation phénoménologique des modes de déformation privilégiés, à partir desquels sont proposés des invariants physiques de la transformation. L’identification des paramètres matériaux nécessaires est décrite. Une version modifiée de cette loi, sans contribution en tension, est implémentée dans un élément semi-discret, où le travail en tension est alors pris en compte par des barres discrétisant le tissage réel. Les importantes différences de rigidités entre sollicitations en tension et en cisaillements font des renforts tissés épais des matériaux fortement anisotropes. Leur modélisation numérique met en évidence des phénomènes parasites ou des limitations liés à cette spécificité. Le phénomène de verrouillage en tension est tout d’abord mis en évidence. Une solution basée sur une formulation éléments finis enhanced assumed strain est proposée pour des éléments continus classiques ou semi-discrets. Puis des problèmes liés aux simulations numériques dominées par la flexion sont soulevés : l’hourglassing transverse et l’absence de résistance locale à la courbure. Dans le cas de l’hourglassing transverse, deux méthodes de rigidification de ces modes de déplacement sont proposées : par moyennage des dilatations dans l’élément ou par ajout d’une rigidité matérielle tangente supplémentaire. Pour l’introduction d’une résistance à la courbure, une méthode basée sur l’utilisation purement numérique de plaques rotation free est proposée. Celles-ci permettent le calcul de la courbure induisant, par l’intermédiaire d’un moment de flexion, des efforts internes supplémentaires. Finalement, la modélisation du retour élastique après pyrolyse de la matrice organique à précurseurs céramique est réalisée. Le comportement de la matrice pyrolysée est identifié expérimentalement à l’aide d’une loi hyperélastique isotrope transverse. L’addition de cette loi, qui prend comme référence la préforme déformée, à la loi de comportement initiale du renfort tissé permet de visualiser les déformations obtenues en fin de pyrolyse. Cette modélisation est comparée à des résultats expérimentaux
Manufacture processes modeling of woven fabrics composites is a major stake for state-of-the-art industrial parts, where their usage is intensifying. Control of all the manufacturing stages of ceramic matrix composites, particularly the forming and pyrolysis steps, is essential. Understanding and simulation of the mechanical behavior at each stage is required to optimize the final product performances. Two macroscopic modeling approaches of thick woven fabric reinforcements are detailed: a continuous classical one and a semi-discrete one. An initially orthotropic hyperelastic constitutive law is thus established. This law is based on a phenomenological observation of the main fabric deformation modes, from where physical invariants of the deformation are suggested. The required material parameters identification is explained. A modified version of this law, without any tensile energetic contribution, is implemented in a semi-discrete element where the tensile work is taken into account by bars that discretize the real weaving. Thick woven reinforcements are highly anisotropic materials due to the large ratio between the tensile rigidity and the others. Their numerical modeling highlights spurious phenomena and limitations related to this specificity. The tension locking is firstly tackled. A remedy based on an enhanced assumed strain finite element formulation is suggested for classical continuum and semi-discrete elements. Problems linked to bending-dominated numerical simulations are brought to attention : transverse hourglassing and lack of local bending stiffness. For the transverse hourglassing situation, two stiffening technics are proposed : averaging the dilatation through the whole element or adding a supplementary tangent material rigidity in a specific direction. The local bending stiffness problem is solved by calculating the curvature inside the element by using rotation free plates. The induced bending moment leads to supplementary internal loads. Finally, the elastic springback following the pyrolysis of the polymer matrix with ceramic precursors is modeled. The constitutive behavior is experimentally identified with a transverse isotropic hyperelastic law. Added to the initial reinforcements’ hyperelastic law, with the preformed fabric as reference configuration, the pyrolysis induced deformations can be visualized. This final model is compared with experimental results
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Borius, Zoé. "Développement et caractérisation de CMC oxyde/oxyde élaborés par imprégnation de mèches en continu." Electronic Thesis or Diss., Ecole nationale des Mines d'Albi-Carmaux, 2024. http://www.theses.fr/2024EMAC0010.

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L’introduction de composites à matrice céramique (CMC) oxyde/oxyde est envisagée dans les turbomachines de nouvelle génération. Les principaux freins à l’industrialisation de ces matériaux sont la diversité des procédés d’élaboration, leurs coûts, ainsi que l’hétérogénéité des microstructures et des propriétés mécaniques. Ces travaux de thèse en collaboration entre l’Onera, l’IRT Saint-Éxupéry et l’ICA étudient une nouvelle voie d’élaboration de CMC alumine/alumine, par une étape d’imprégnation de mèche en continu. Pour commencer, une étude de formulation de suspensions aqueuses d’alumine compatibles avec l’élaboration de composites par le procédé d’imprégnation en ligne suivi d’une mise en forme en autoclave et d’un frittage a été menée. Deux plastifiants organiques hygroscopiques, le sorbitol et le glycérol, ainsi qu’un gélifiant, la boehmite, ont été évalués. Les cycles thermiques en autoclave ont été adaptés à la composition des suspensions et en particulier aux additifs organiques. Plusieurs compositions de suspensions ont été retenues et les microstructures des CMC résultants ont été caractérisées. Les relations composition de la suspension – adaptabilité au procédé – microstructure du composite ont été investiguées. Enfin, les comportements mécaniques à température ambiante des différentes nuances de CMC ont été examinés en lien avec leurs microstructures, et des scénarios d’endommagement en traction ont été proposés
The use of oxide/oxide ceramic matrix composites (CMCs) is being considered for new generation engines. The main obstacle to the industrialisation of these materials are the diversity of production processes, their costs, and the heterogeneity of the microstructures and mechanical properties. This thesis is a collaboration between Onera, IRT Saint-Éxupéry and ICA. It investigates a new way of producing alumina/alumina CMC by using a continuous tow impregnation process. Firstly, a study was carried out into the formulation of aqueous alumina slurries compatible with the production of composites using a continuous tow impregnation line, followed by autoclave shaping and sintering. Two hygroscopic organic plasticisers, sorbitol and glycerol, as well as a gelling agent, boehmite, were evaluated. Autoclave thermal cycles were adapted to slurries compositions, with particular regard to the organic additives. Several compositions were selected and the microstructures of the resulting CMCs were characterised. The relationships between slurry composition, process adaptability and composite microstructure were investigated. Finally, the mechanical behaviour at ambient temperature of the different CMC grades were examined in relation to their microstructures, and tensile damage scenarios were proposed
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Nowacki, Brenna M. "Verification and Calibration of State-of-the-Art CMC Mechanistic Damage Model." University of Dayton / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1461761780.

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Gordon, Neal A. "Material Health Monitoring of SIC/SIC Laminated Ceramic Matrix Composites With Acoustic Emission And Electrical Resistance." University of Akron / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=akron1414835900.

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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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Ben, Ramdane Camélia. "Etude et modélisation du comportement mécanique de CMC oxyde/oxyde." Thesis, Bordeaux, 2014. http://www.theses.fr/2014BORD0077/document.

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Les CMC oxyde/oxyde sont de bons candidats pour des applications thermostructurales. Le comportement mécanique et les mécanismes d’endommagement de deux composites alumine/alumine à renforts tissés bi- et tridimensionnels ont été étudiés et comparés. La microstructure de ces CMC à matrice faible a été caractérisée à partir de porosimétrie et de CND, tel que thermographie IR, scan ultrasonore et tomographie X, ce qui a permis de mettre en évidence la présence de défauts initiaux. Le comportement mécanique en traction, ainsi qu’en compression dansle cas du CMC à renfort bidimensionnel, dans la direction des fibres ainsi que dans la direction ±45°, aété étudié à température ambiante. Afin d’exploiter pleinement ces essais, nous avons eu recours à plusieurs méthodes d’extensométrie et de suivi d’endommagement, telles que la thermographie IR et l’émission acoustique. Les propriétés mécaniques à rupture ainsi que le module de Young du CMC à renfort bidimensionnel développé à l’Onera se sont avérées supérieures à celles disponibles dans la littérature. Les mécanismes d’endommagement des matériaux ont été déterminés à partir d’observations post mortem au MEB et d’essais in situ dans un MEB, ce qui a permis d’évaluer la nocivité des défauts initiaux. Enfin, l’étude du comportement mécanique de ces composites a permisde proposer un modèle d’endommagement tridimensionnel qui permettra de poursuivre le développement de ces matériaux grâce à du calcul de structure. A l’issue de cette thèse, des pistes d’amélioration des procédés d’élaboration et de choix d’instrumentation à utiliser pour les futures études, notamment en ce qui concerne le suivi d’endommagement, ont également été proposées
Oxide/oxide CMCs are good candidates for thermostructural applications. Themechanical behaviour and damage mechanisms of two alumina/alumina composites with two andthree dimensional woven reinforcements were studied and compared. The microstructure of theseweak matrix CMCs was characterized by porosimetry and NDT methods, such as IR thermography,ultrasound scanning and X-ray tomography, which highlighted initial defects. The mechanicalbehaviour was studied through tensile tests, as well as compression tests in the case of the twodimensionalreinforced CMC. These tests were conducted at room temperature, in the fibres directionsand in the ±45° direction. In order to fully exploit these tests, several extensometry and damagemonitoring methods, such as IR thermography and acoustic emission, were used. Young’s moduli andmaximum stresses and strains of the two-dimensional reinforced CMC developed at Onera appearedto be higher than those available in the literature. The damage mechanisms of the materials weredetermined by post mortem SEM observations and in situ testing in a SEM, which made it possible toassess the nocivity of initial defects. Studying the mechanical behaviour of these composites finallyenabled the development of a three-dimensional damage model that will facilitate the furtherdevelopment of such materials, through finite element analysis. Finally, some improvements regardingthe manufacturing processes and the instrumentation for damage monitoring were suggested forfuture studies
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Nestler, Daisy Julia. "Beitrag zum Thema VERBUNDWERKSTOFFE - WERKSTOFFVERBUNDE." Doctoral thesis, Universitätsbibliothek Chemnitz, 2014. http://nbn-resolving.de/urn:nbn:de:bsz:ch1-qucosa-134459.

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Vielschichtige Eigenschaftsprofile benötigen zunehmend moderne Verbundwerkstoffe und Werkstoffverbunde einschließlich der raschen Entfaltung neuer Fertigungstechnologien, da der monolithische Werkstoff bzw. ein einziger Werkstoff den heutigen komplexen Anforderungen nicht mehr genügen kann. Zukünftige Werkstoffsysteme haben wirtschaftlich eine Schlüsselposition und sind auf den Wachstumsmärkten von grundlegender Bedeutung. Gefragt sind maßgeschneiderte Leichtbauwerkstoffe (tailor-made composites) mit einem adaptierten Design. Dazu müssen Konzepte entwickelt werden, um die Kombination der Komponenten optimal zu gestalten. Das erfordert werkstoffspezifisches Wissen und Korrelationsvermögen sowie die Gestaltung komplexer Technologien, auch unter dem Aspekt der kontinuierlichen Massen- und Großserienfertigung (in-line, in-situ) und damit der Kostenreduzierung bislang teurer Verbundwerkstoffe und Werkstoffverbunde. In der vorliegenden Arbeit wird in vergleichbarer und vergleichender Art und Weise sowie abstrahierter Form ein Bogen über das Gesamtgebiet der Verbundwerkstoffe und Werkstoffverbunde gespannt. Eine zusammenfassende Publikation über dieses noch sehr junge, aber bereits breit aufgestellte Wissenschaftsgebiet fehlt bislang. Das ist der Separierung der einzelnen, fest aufgeteilten Gruppierungen der Verbundwerkstoffe geschuldet. Querverbindungen werden selten hergestellt. Dieses Defizit in einem gewissen Maße auszugleichen, ist Ziel der Arbeit. Besondere Berücksichtigung finden Begriffsbestimmungen und Klassifikationen, Herstellungsverfahren und Eigenschaften der Werkstoffe. Es werden klare Strukturierungen und Übersichten herausgearbeitet. Zuordnungen von etablierten und neuen Technologien sollen zur Begriffsstabilität der Terminologien „Mischbauweise“ und „Hybrider Verbund“ beitragen. Zudem wird die Problematik „Recycling und Recyclingtechnologien“ diskutiert. Zusammenfassend werden Handlungsfelder zukünftiger Forschungs- und Entwicklungsprojekte spezifiziert. Aus dem Blickwinkel der verschiedenen Herstellungsrouten insbesondere für Halbzeuge und Bauteile und der dabei gewonnenen Erkenntnisse werden verallgemeinerte Konzepte für tailor-made Verbundwerkstoffe und Werkstoffverbunde vorgeschlagen („Stellschraubenschema“). Diese allgemeinen Werkstoffkonzepte werden auf eigene aktuelle Forschungsprojekte der Schwerpunktthemen Metallmatrix- und Polymermatrix-Verbundwerkstoffe sowie der hybriden Werkstoffverbunde appliziert. Forschungsfelder für zukünftige Projekte werden abgeleitet. Besonderes Augenmerk gilt den hybriden Verbunden als tragende Säule zukünftiger Entwicklungen im Leichtbau. Hier spielen in-line- und in-situ-Prozesse eine entscheidende Rolle für eine großseriennahe, kosteneffiziente und ressourcenschonende Produktion
Complex property profiles require increasingly advanced composite materials and material compounds, including the rapid deployment of new production technologies, because the monolithic material or a single material can no longer satisfy today's complex requirements. Future material systems are fundamentally important to growth markets, in which they have an economically key position. Tailor-made lightweight materials (tailor-made composites) with an adapted design are needed. These concepts have to be developed to design the optimum combination of components. This requires material-specific knowledge and the ability to make correlations, as well as the design of complex technologies. Continuous large-scale and mass production (in-line, in-situ), thus reducing the costs of previously expensive composite materials and material compounds, is also necessary. The present work spans the entire field of composite materials and material compounds in a comparable and comparative manner and abstract form. A summarizing publication on this still very new, but already broad-based scientific field is not yet available. The separation of the individual, firmly divided groups of the composite materials is the reason for this. Cross-connections are rarely made. The objective of this work is to compensate to some extent for this deficiency. Special consideration is given to definitions and classifications, manufacturing processes and the properties of the materials. Clear structures and overviews are presented. Mapping established and new technologies will contribute to the stability of the terms "mixed material compounds" and "hybrid material compounds". In addition, the problem of recycling and recycling technologies is discussed. In summary, areas for future research and development projects will be specified. Generalized concepts for tailor-made composite materials and material compounds are proposed ("adjusting screw scheme") with an eye toward various production routes, especially for semi-finished products and components, and the associated findings. These general material concepts are applied to own current research projects pertaining to metal-matrix and polymer-matrix composites and hybrid material compounds. Research fields for future projects are extrapolated. Particular attention is paid to hybrid material compounds as the mainstay of future developments in lightweight construction. In-line and in-situ processes play a key role for large-scale, cost- and resource-efficient production
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Books on the topic "Ceramic Matrix Composite (CMC)"

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United States. National Aeronautics and Space Administration., ed. Approaches to polymer-derived CMC matrices. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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United States. National Aeronautics and Space Administration., ed. Approaches to polymer-derived CMC matrices. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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1955-, Duffy S. F., Gyekenyesi John P, and United States. National Aeronautics and Space Administration., eds. Reliability analysis of laminated CMC components through shell subelement techniques. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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International Conference on High Temperature Ceramic Matrix Composites (3rd 1998 Osaka, Japan). High temperature ceramic matrix composites III: Proceedings of the 3rd International Conference on High Temperature Ceramic Matrix Composites (HT-CMC 3), September 6-9, 1998, Osaka, Japan. Edited by Niihara Koichi, Nihon Seramikkusu Kyōkai, and International Symposium on the Science of Engineering Ceramics (2nd : 1998 : Osaka, Japan). Uetikon-Zuerich, Switzerland: Trans Tech Publications, 1999.

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A, DiCarlo James, and NASA Glenn Research Center, eds. Thermomechanical characterization of SiC fiber tows and implications for CMC. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

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P, Gyekenyesi John, and United States. National Aeronautics and Space Administration., eds. CCARES, a computer algorithm for the reliability analysis of laminated CMC components. [Washington, DC: National Aeronautics and Space Administration, 1993.

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R, Naslain, Lamon J, Doumeingts D, European Association for Composite Materials., American Ceramic Society, Ceramic Society of Japan, International Conference on High Temperature Ceramic Matrix Composites (1993 : Bordeaux), and European Conference on Composite Materials, (6th : 1993 : Bordeaux), eds. High temperature ceramic matrix composites: HT-CMC1. Cambridge: Woodhead Publishing, 1993.

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

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

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

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Book chapters on the topic "Ceramic Matrix Composite (CMC)"

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Spriet, Patrick. "CMC Applications to Gas Turbines." In Ceramic Matrix Composites, 591–608. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2014. http://dx.doi.org/10.1002/9781118832998.ch21.

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Schmidt, J., M. Scheiffele, and W. Krenkel. "Engineering of CMC Tubular Components." In High Temperature Ceramic Matrix Composites, 826–31. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch126.

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Boitier, G., J. L. Chermant, H. Cubero, S. Darzens, G. Farizy, J. Vicens, and J. C. Sangleboeuf. "CMC Creep Mechanism under Argon." In High Temperature Ceramic Matrix Composites, 492–97. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch76.

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Ortelt, M., F. Ruehle, H. Hald, and H. Weihs. "Dynamic Qualification of a New CMC Fastener." In High Temperature Ceramic Matrix Composites, 760–66. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch115.

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Khaliq, Jibran. "Ceramic Matrix Composites (CMCs)." In Advances in Machining of Composite Materials, 285–309. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-71438-3_11.

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Igashira, Kenichiroh, Yoshihiro Matsuda, Go Matsubara, and Akira Imamura. "Development of the Advanced Combustor Liner Composed of CMC/GMC Hybrid Composite Material." In High Temperature Ceramic Matrix Composites, 789–96. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch120.

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Demmel, J., H. Lallinger, and G. Kopp. "Applications of CMC-Racks for High Temperature Processes." In High Temperature Ceramic Matrix Composites, 832–38. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch127.

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Renz, R., B. Heidenreich, W. Krenkel, A. Schöppach, and F. Richter. "CMC Materials for Lightweight and Low CTE Applications." In High Temperature Ceramic Matrix Composites, 839–45. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch128.

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Heidenreich, B., R. Renz, and W. Krenkel. "Short Fibre Reinforced CMC Materials for High Performance Brakes." In High Temperature Ceramic Matrix Composites, 809–15. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch123.

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Withers, J. C., B. Safadi, W. Kowbel, and R. O. Loutfy. "A Low-Cost and Unique Carbon Fiber for CMC." In High Temperature Ceramic Matrix Composites, 13–16. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch2.

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Conference papers on the topic "Ceramic Matrix Composite (CMC)"

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Ghoshal, Anindya, Clara Mock, Muthuvel Murugan, Andy Nieto, Michael Walock, Luis Bravo, Marc Pepi, Jeffrey Swab, Samuel Hirsch, and Robert Dowding. "High Temperature Ceramic Matrix Composite Materials Research for Next Generation Army Propulsion System." In Vertical Flight Society 74th Annual Forum & Technology Display, 1–16. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12871.

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Aviation propulsion system structures are subjected to challenging conditions such as extremely high velocities, ultra-high/low temperatures, and excessive dust/sand/smoke/volcanic ash conditions during military operations. Therefore, the research and development of high-performance engine materials with superior characteristics such as great mechanical strength, high fatigue resistance and creep resistance, good tolerance to wide temperature variations, and excellent resistance to corrosion and oxidation is essential to the evolution of highly robust and efficient propulsion systems without a compromise on capabilities, even in hostile environments. The goal of this collaborative program within United States Army Research Laboratory (ARL) is to establish a generalized fundamental physics-based approach and probabilistic-based lifing method to extrapolate thermal loading performance and material characterization results from high performance high temperature ceramic materials such as ceramic matrix composites (CMC) based flat specimens and engine component representative specimens. High temperature structural integrity and durability and probabilistic-based lifing assessment will be evaluated both analytically and experimentally under thermal shock, thermal cycling, and combined thermo-mechanical loadings. This paper presents the ARL CMC propulsion materials strategy in each of the identified thrust areas and present some results from some of the ongoing research at ARL and its research partners.
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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." 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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Presby, M. J., C. Gong, S. Kane, N. Kedir, A. Stanley, D. C. Faucett, and S. R. Choi. "Erosion in an MI SiC/SiC Ceramic Matrix Composite (CMC)." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90837.

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Abstract Erosion phenomenon of ceramic matrix composites (CMCs), attributed to their unique architectural configurations, is markedly different from conventional monolithic ceramic counterparts. Prior to further integration of CMCs into hot-section components of aeroengines subject to erosive environments, their erosion behavior needs to be characterized, analyzed, and formulated. The erosion behavior of a 2-D woven melt-infiltrated (MI) SiC/SiC CMC was assessed in this work as a function of variables such as particle velocity and size. The erosion damage was characterized using appropriate analytical tools such as optical and scanning electron microscopy (SEM). A phenomenological erosion model was developed for SiC/SiC CMC material systems with respect to kinetic energy of impacting particles in conjunction with nominal density, matrix hardness and elastic modulus of the SiC/SiC CMCs. The model was in reasonable agreement with the experimental data.
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Xue, Yibin, Frank Abdi, Gregory N. Morscher, and Sung Choi. "Non-Destructive Ceramic Matrix Composite Impact Modeling Validation." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94728.

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Ceramic matrix composite (CMC) materials technology is of fundamental importance to gas turbine engine application. FOD (foreign Object Damage) in CMC components can result in component localized damage and a loss of post-impact performance. CMC impact generates a varying degree of damage from localized surface damage to complete penetration depending on the severity of impact events. Ceramic Composite equivalent electrical properties are computed based on simplified Multi-scale micromechanics equations. Electrical resistance and/or conductivity are computed utilizing the constituent material properties, effective medium, and percolation theories. Ceramic composite electrical properties simulation requires the algorithm development that combines the effective medium and percolation theories. A physically based percolation model is implemented to characterize the effective electrical conductivity of heterogeneous composites by means of the combination of effective medium (EM) and percolation equations with universal exponents. It is shown that the present model correlates well with the experimental electrical resistivity and acoustic emission data. The change in electrical resistivity after impact is compared with test data of a SA-SiC fiber reinforced SiC matrix composite. The predicted damage after impact and the trend of damage volume correlated well with experimental observations of damage shape and reduction in electrical resistance. Thus, an empirical relationship between damage volume and mechanisms and electrical resistance are developed and presented.
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Brewer, David, Greg Ojard, and Martin Gibler. "Ceramic Matrix Composite Combustor Liner Rig Test." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0670.

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The NASA High Speed Research (HSR)/Enabling Propulsion Materials (EPM) program was charged with the responsibility for developing the materials and technologies necessary to meet the High Speed Civil Transport (HSCT) engine requirements. The combustor liner was identified as a critical component for meeting the efficiency and environmental acceptability goals of the HSCT engine. The EPM Ceramic Matrix Composite (CMC) Combustor liner program was tasked with developing and demonstrating a material system and design concept that meets the HSCT environmental, thermal, structural, economic, and durability requirements. Melt Infiltration (MI) SiC/SiC composites were ultimately selected for the combustor liner application. The culmination of this development effort was the delivery and testing of a CMC combustor liner. Testing was performed at NASA Glenn Research Center in the Sector Rig under HSCT operating conditions. The initial results of the rig testing are presented.
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Edelson, Ryan D., and Karen A. Thole. "Impact of Ceramic Matrix Composite Topology on Overall Effectiveness." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82326.

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Abstract Ceramic matrix composites (CMCs) are a material of interest for components in the hot section of gas turbine engines due to their high strength-to-weight ratio and high temperature capabilities. CMCs are a class of material made of macro scale woven ceramic fibers infiltrated with a ceramic matrix making them significantly different than their nickel superalloy counterparts. As CMCs are implemented into gas turbine engines, the effects of the inherent topology of the CMC weave on convective heat transfer must be understood. In this study, film cooling holes were integrated into a representative CMC weave for three test coupons that were printed using additive manufacturing. The three coupons included: one having a weave topology along the surface of the internal channel supplying coolant to the film cooling holes; one having a weave topology along the external film cooled surface; and one having a weave topology on both the coolant supply channel as well as the external film cooled surface. Overall effectiveness levels for the two cases with a weave surface on the external film cooled wall were measured to be lower than levels for the case with the smooth external surface. The external weave significantly increased the mixing of the coolant jet with the hot mainstream resulting in poor cooling.
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Watanabe, Fumiaki, Takeshi Nakamura, and Yousuke Mizokami. "Design and Testing for Ceramic Matrix Composite Turbine Vane." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63264.

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Ceramic matrix composite (CMC) have higher temperature capability and lower density than nickel based alloys which have been used for hot section components of gas turbine engines. These properties are expected to bring many benefits, such as higher turbine inlet temperature (TIT), reduction of cooling air, and reduction of weight, when it is used as the material for hot section components of gas turbine engine. The authors have been developing CMC turbine vane for aircraft engines. In this paper, the authors present the summary of design, manufacturing, and testing, which were conducted from 2010 to 2012. The purpose of this work was to verify that the SiC-SiC CMC which IHI has developed has the applicability to aircraft turbine vanes. The concept was planned for CMC hollow turbine vanes, in which the airfoil and the platform are fabricated in CVI process. As the demonstration of this concept, the first stage turbine vane was designed with CMC for IHI IM270 that is the 2MW-class small industrial gas turbine engine. Bending rig test was conducted at room temperature in order to check the structural feasibility of the airfoil-platform joint. The outer platform of vane was fixed in the same way with the engine parts, and the load simulating the aerodynamic force was applied at the airfoil portion. The fracture load was higher than the load which the vanes receive in the actual engine. Burner rig test was conducted in order to check the durability against thermal cycle. A CMC vane was set between dummy metal vanes, and cyclically heated by gas burner. The maximum airfoil surface temperature was set to 1200 degree C, and the maximum temperature difference between airfoil and platform was about 700 degree C. The minimum airfoil temperature at the interval of heating was about 300 degree C. The time of one thermal cycle was 6 minutes that consisted of 3 minute heating and 3 minute natural cooling. The test was conducted for 1,000 cycles. In post-test inspection there was no defect like a crack. Engine test for CMC vanes was conducted using IHI IM270. The four CMC vanes were mounted into the first stage turbine nozzle assembly in place of the normal metal vanes. The test was conducted for 400 hours. The inlet temperature of CMC vanes were measured by thermocouples installed at the leading edge, and the measured temperature was about 1050 degree C at the steady state. From this work, the applicability of the design concept for the CMC vane to actual engine was verified in which airfoil-platform are fabricated in CVI process.
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Boyle, Robert J., Ankur H. Parikh, and Vinod K. Nagpal. "Design Considerations for Ceramic Matrix Composite High Pressure Turbine Blades." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91787.

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Abstract Issues associated with using SiC/SiC Ceramic Matrix Composite (CMC) materials for High Pressure Turbine (HPT) rotor blades are explored. SiC/SiC materials have higher temperature capability than current HPT superalloys. The strength versus temperature characteristics of SiC/SiC CMCs differs from that of superalloys. Stress analyses were done for a NASA specified notional single aisle aircraft engine blade to be available in the N+3 time frame, (beyond 2030). Stacking, the relative position of hub and tip sections, depends on both pressure and centrifugal forces, and material density. The effect of blade stacking on blade stresses is examined. The change in stresses as the rotation rate varies is examined. The change in engine weight, and thus fuel consumption, due to changes in engine size as the rpm changes is discussed. SiC/SiC CMC materials are generally not isotropic. The effect on stresses and strains of a directional variation in Young’s modulus is examined. Shrouding metallic HPT rotor blades is not common. Shrouding SiC/SiC CMC rotor blades may be feasible due to the lower density, and thus lower centrifugal loads, of SiC/SiC blades. The increase in stresses due to shrouding a SiC/SiC blade is discussed.
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Wilkins, Peter H., Stephen P. Lynch, Karen A. Thole, San Quach, and Tyler Vincent. "Experimental Heat Transfer and Boundary Layer Measurements on a Ceramic Matrix Composite Surface." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15053.

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Abstract Ceramic matrix composites (CMCs) are quickly becoming more prevalent in the design of gas turbines due to their advantageous weight and thermal properties. While there are many advantages, the CMC surface morphology differs from that of conventional cast airfoil components. Despite a great deal of research focused on the material properties of CMCs, little public work has been done to investigate the impact that the CMC surface morphology has on the boundary layer development and resulting heat transfer. In this study, a scaled-up CMC weave pattern was developed and tested in a low speed wind tunnel to evaluate both heat transfer and boundary layer characteristics. Results from these experiments indicate that the CMC weave pattern results in augmented heat transfer and flow field properties that significantly vary locally when compared to a smooth surface.
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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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Reports on the topic "Ceramic Matrix Composite (CMC)"

1

Mosher, Daniel, Justin Alms, and John Holowczak. Low Cost Glass-Ceramic Matrix Composite Heat Exchanger. Office of Scientific and Technical Information (OSTI), February 2023. http://dx.doi.org/10.2172/2282105.

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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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Lynch, Stephen. Development of Additive Manufacturing for Ceramic Matrix Composite Vanes. Office of Scientific and Technical Information (OSTI), July 2024. http://dx.doi.org/10.2172/2404290.

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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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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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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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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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