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Статті в журналах з теми "Ceramic Fiber-Matrix Composites (CFMC)":
1
Ailey, K. S., K. L. More, and R. A. Lowden. "The Stability of BN Interfacial Coatings in CFCC Systems During Oxidation and Exposure to Moisture." Microscopy and Microanalysis 3, S2 (August 1997): 729–30. http://dx.doi.org/10.1017/s1431927600010539.
The mechanical reliability of ceramic matrix composites (CMCs) at elevated temperatures in oxidative environments is primarily dependent upon the chemical and structural stability of the fiber/matrix interface. Graphitic carbon coatings have traditionally been used to control the interfacial properties in CMCs, however, their use is limited in high temperature oxidative environments due to the loss of carbon and subsequent oxidation of the fiber and matrix. Thus, BN is being investigated as an alternative interfacial coating since it has comparable room temperature properties to carbon with improved oxidation resistance. The stability of BN interfaces in SiC/SiC composites is being investigated at elevated temperatures in either flowing oxygen or environments containing water vapor. The effect of several factors on BN stability, including crystallographic structure, extent of BN crystallization, and impurity content, are being evaluated.Nicalon™ fiber preforms were coated with ≈ 0.4 μm of BN by CVD using BCl3, NH3, and H2 at 1373 K. The coated preforms were densified using a forced-flow chemical vapor infiltration (FCVI) technique developed at ORNL.
2
Mingazzini, Claudio, Matteo Scafè, Daniele Caretti, Daniele Nanni, Emiliano Burresi, and Alida Brentari. "Poly-Siloxane Impregnation and Pyrolysis of Basalt Fibers for the Cost-Effective Production of CFCCs." Advances in Science and Technology 89 (October 2014): 139–44. http://dx.doi.org/10.4028/www.scientific.net/ast.89.139.
In this work, the optimisation of basalt fiber CFCCs (Continuous Fiber Ceramic Composites) production is presented, focusing on the development of a silicon-oxycarbide matrix by PIP (Polymer Impregnation Pyrolysis). The use of low cost poly-siloxanes and basalt fibers is particularly promising for transports and constructions, where thermostructural CFCCs would be interesting for vehicle weight reduction and fire-resistant panels, but only on the condition that production costs are kept really low. The basalt/SiCO composites are suitable for mechanical applications up to 600°C and stand up temperatures up to 1200°C, also in oxidative environments. The key parameters to keep the production costs low are the furnace and moulds type, being steel probably the best material for both, since it withstands the pyrolysis temperature and can be easily cleaned, by oxidation, from any residue. Regarding the pyrolysis environment, two conditions were compared, nitrogen flow and vacuum, being perhaps the vacuum procedure less expensive and so potentially more appealing for a large scale production. The microstructure and the thermomechanical characteristics of the obtained composites were compared, Another key parameter in determining the production costs is the number of PIP steps, which has to be minimised. The present results support the conclusion that one PIP step in nitrogen or two PIP steps in vacuum can provide CFCC with satisfactory mechanical characteristics for thermomechanical applications in oxidative environments.
3
MARSHALL, D. B., and A. G. EVANS. "Failure Mechanisms in Ceramic-Fiber/Ceramic-Matrix Composites." Journal of the American Ceramic Society 68, no. 5 (May 1985): 225–31. http://dx.doi.org/10.1111/j.1151-2916.1985.tb15313.x.
Mullite fiber reinforced alumina ceramic matrix composites (MFACC) were prepared using CaO-MgO-SiO2 (CMS) and TiO2 as sintering aids. The effects of the contents of sintering aids and mullite fiber on the density and sintering temperature of MFACC are studied. The results showed that when the CMS content is 8.0% and the TiO2 content is 1.0%, the density of the as-sintered MFACC is 98.9%. When the mullite fiber content is 15.0% and the sintering temperature is 1450 °C, the flexural strength of the resultant composite increases to 504.5MPa, 70.7% higher than the original matrix, and the relative density of the composites reaches 98.4%. The reinforcement mechanisms are fibers pull-out and sticky point.
5
Shin, Dong-Woo, Keun Ho Auh, and Hidehiko Tanaka. "Tensile Properties of Ceramic Matrix Fiber Composites." Journal of the American Ceramic Society 78, no. 11 (November 1995): 3137–41. http://dx.doi.org/10.1111/j.1151-2916.1995.tb09098.x.
Goushegir, S. M., P. O. Guglielmi, Antonio Pedro Novaes de Oliveira, Dachamir Hotza, and Rolf Janssen. "Fiber-Matrix Compatibility in LZSA Glass-Ceramic Matrix Composites." Materials Science Forum 727-728 (August 2012): 562–67. http://dx.doi.org/10.4028/www.scientific.net/msf.727-728.562.
Continuous fiber reinforced glass-ceramic (GC) matrix composites are potential candidates for thermomechanical applications at moderate temperatures (up to 1000°C) due to the combination of interesting properties such as high specific strength and toughness. Crack deflection into fiber-matrix interface, as well as subsequent fiber pullout and bridging are the respective toughening mechanisms. In this paper, the compatibility between LZSA glass-ceramic matrix and commercially available oxide alumina fibers (NextelTM610) is qualitatively examined. Toughening mechanisms such as crack deflection and fiber pullout are investigated by analyzing the path of Vickers-induced matrix cracks formed in the vicinity of the fibers and by investigating the crack surface of bending samples, respectively. GC matrix samples sintered and crystallized at different heat-treatment conditions have shown strong interfacial bonds between matrix and fibers, which leads to a brittle fracture without significant fiber pullout in all cases. This behavior indicates the requirement of using fiber coatings in this CMC system, to produce weak interfaces that enable toughening mechanisms to take place.
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Delale, F. "Critical fiber size for microcrack suppression in ceramic-fiber/ceramic-matrix composites." Engineering Fracture Mechanics 31, no. 1 (January 1988): 145–55. http://dx.doi.org/10.1016/0013-7944(88)90128-2.
PurposeThis paper aims to predict fatigue life and fatigue limit of fiber-reinforced ceramic-matrix composites (CMCs) with different fiber preforms, i.e. unidirectional, cross-ply, 2D-, 2.5D- and 3D-woven, at room and elevated temperatures.Design/methodology/approachUnder cyclic loading, matrix multicracking and interface debonding occur upon first loading to fatigue peak stress, and the interface wear appears with increasing cycle number, leading to degradation of the interface shear stress and fibers strength. The relationships between fibers fracture, cycle number, fatigue peak stress and interface wear damage mechanism have been established based on the global load sharing (GLS) criterion. The evolution of fibers broken fraction versus cycle number curves of fiber-reinforced CMCs at room and elevated temperatures have been obtained.FindingsThe predicted fatigue life S–N curve can be divided into two regions, i.e. the Region I controlled by the degradation of interface shear stress and fibers strength and the Region II controlled by the degradation of fibers strength.Practical/implicationsThe proposed approach can be used to predict the fatigue life and fatigue limit of unidirectional, cross-ply, 2D-, 2.5D- and 3D-woven CMCs under cyclic loading.Originality/valueThe fatigue damage mechanisms and fibers failure model were combined together to predict the fatigue life and fatigue limit of fiber-reinforced CMCs with different fiber preforms.
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Budiansky, B., A. G. Evans, and J. W. Hutchinson. "Fiber-matrix debonding effects oncracking in aligned fiber ceramic composites." International Journal of Solids and Structures 32, no. 3-4 (February 1995): 315–28. http://dx.doi.org/10.1016/0020-7683(94)00154-o.
Lamouroux, F., S. Bertrand, R. Pailler, R. Naslain, and M. Cataldi. "Oxidation-resistant carbon-fiber-reinforced ceramic-matrix composites." Composites Science and Technology 59, no. 7 (May 1999): 1073–85. http://dx.doi.org/10.1016/s0266-3538(98)00146-8.
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.
2
Dannemann, Kathryn Ann. "Damage development and failure of fiber-reinforced ceramic matrix composites." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/14197.
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Materials Science and Engineering, 1989. Vita. Includes bibliographical references (leaves 111-120). by Kathryn Ann Dannemann. Ph.D.
3
Bricker, Stephen. "Anomaly Detection and Microstructure Characterization in Fiber Reinforced Ceramic Matrix Composites." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1448880983.
Hu, Yile, and Yile Hu. "Peridynamic Modeling of Fiber-Reinforced Composites with Polymer and Ceramic Matrix." Diss., The University of Arizona, 2017. http://hdl.handle.net/10150/625367.
This study focuses on developing novel modeling techniques for fiber-reinforced composites with polymer and ceramic matrix based on Peridynamic approach. To capture the anisotropic material behaviors of composites under quasi-static and dynamic loading conditions, a new peridynamic model for composite laminate and a modified peridynamic approach for non-uniform discretization are proposed in this study. In order to achieve the numerical implementation of the proposed model and approach, a mixed implicit-explicit solver based on GPU parallel computing is developed as well.
The new peridynamic model for composite laminates does not have any limitation in fiber orientation, material properties and stacking sequence. It can capture the expected orthotropic material properties and coupling behaviors in laminates with symmetric and asymmetric layups. Unlike the previous models, the new model enables the evaluation of stress and strain fields in each ply of the laminate. Therefore, it permits the use of existing stress- or strain-based failure criteria for damage prediction. The computation of strain energy stored at material points allows the energy-based failure criteria required for delamination propagation and fatigue crack growth. The capability of this approach is verified against benchmark solutions, and validated by comparison with the available experimental results for three laminate layups with an open hole under tension and compression.
The modified peridynamic approach for non-uniform discretization enables computational efficiency and removes the effect of geometric truncations in the simulation. This approach is a modification to the original peridynamic theory by splitting the strain energy associated with an interaction between two material points according to the volumetric ratio arising from the presence of non-uniform discretization and variable horizon. It also removes the requirement for correction of peridynamic material parameters due to surface effects. The accuracy of this approach is verified against the benchmark solutions, and demonstrated by considering cracking in nuclear fuel pellet subjected to a thermal load with non-uniform discretizations.
Unlike the previous peridynamic simulations which primarily employs explicit algorithm, this study introduces implicit algorithm to achieve peridynamic simulation under quasi-static loading condition. The Preconditioned Conjugate Gradient (PCG) and Generalized Minimal Residual (GMRES) algorithms are implemented with GPU parallel computing technology. Circulant preconditioner provides significant acceleration in the convergence of peridynamic analyses. To predict damage evolution, the simulation is continued with standard explicit algorithms. The validity and performance of this mixed implicit-explicit solver is established and demonstrated with benchmark tests.
5
Huang, Xinyu. "Mechanics and Durability of Fiber Reinforced Porous Ceramic Composites." Diss., Virginia Tech, 2001. http://hdl.handle.net/10919/26063.
Porous ceramics and porous ceramic composites are emerging functional materials
that have found numerous industrial applications, especially in energy conversion
processes. They are characterized by random microstructure and high porosity.
Examples are ceramic candle filters used in coal-fired power plants, gas-fired
infrared burners, anode and cathode materials of solid oxide fuel cells, etc.
In this research, both experimental and theoretical work have been conducted to
characterize and to model the mechanical behavior and durability of this novel
class of functional material. Extensive experiments were performed on a hot gas
candle filter material provided by the McDermott Technologies Inc (MTI). Models at
micro-/meso-/macro- geometric scales were established to model the porous ceramic
material and fiber reinforced porous ceramic material. The effective mechanical
properties are of great technical interest in many applications. Based on the
average field formalism, a computational micromechanics approach was developed to estimate
the effective elastic properties of a highly porous material with random microstructure.
A meso-level analytical model based on the energy principles was developed to estimate
the global elastic properties of the MTI filament-wound ceramic composite tube.
To deal with complex geometry, a finite element scheme was developed for
porous material with strong fiber reinforcements. Some of the model-predicted elastic
properties were compared with experimental values. The long-term performance of ceramic
composite hot gas candle filter materials was discussed. Built upon the stress analysis
models, a coupled damage mechanics and finite element approach was presented to assess
the durability and to predict the service life of the porous ceramic composite
candle filter material. Ph. D.
6
Butts, Mark D. "Nondestructive examination of nicalon fiber composite preforms using x-ray tomographic microscopy." Thesis, Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/19959.
Bulsara, Vatsal N. "Effects of fiber spatial distribution and interphase on transverse damage in fiber-reinforced ceramic matrix composites." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/21429.
Bhatt, Hemanshu D. "Effect of interfacial thermal conductance and fiber orientation on the thermal diffusivity/conductivity of unidirectional fiber-reinforced ceramic matrix composites." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-07282008-135034/.
Shin, Hyunho. "Interface reactions and their influence on properties of SiC fiber-reinforced ceramic matrix composites." Diss., Georgia Institute of Technology, 1994. http://hdl.handle.net/1853/19122.
Maldia, Leopoldo C. "Sodium sulfate corrosion of silicon carbide fiber-reinforced lithium aluminosilicate glass-ceramic matrix composites." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA277224.
Tredway, W. K. Carbon fiber reinforced glass matrix composites for satellite applications. East Hartford, Ct: United Technologies Research Center, 1992.
Halbig, Michael C. Degradation of continuous fiber ceramic matrix composites under constant-load conditions. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2000.
International Conference on High-Temperature Ceramic-Matrix Composites (5th 2004 Seattle, Wash.). High temperature ceramic matrix composites 5: Proceedings of the 5th International Conference on High Temperature Ceramic Matrix Composites (HTCMC 5). Westerville, Ohio: American Ceramic Society, 2005.
Murthy, Pappu L. N. Probabilistic micromechanics and macromechanics for ceramic matrix composites. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.
Halbig, Michael C. Oxygen diffusion and reaction kinetics in continuous fiber ceramic matrix composites. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1999.
Campbell, Christian X. Databook on mechanical and thermophysical properties of fiber-reinforced ceramic matrix composites. West Lafayette, IN: Ceramic Information Analysis Center, Center for Information and Numerical Data Analysis and Synthesis, Purdue University, 1997.
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.
Gottlieb, Rebecca, Shannon Poges, Chris Monteleone, Steven L. Suib, and Steven L. Suib. "Continuous Fiber-reinforced Ceramic Matrix Composites." In Advanced Ceramic Materials, 146–99. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119242598.ch4.
Lamon, Jacques. "Influence of Interfaces and Interphases on the Mechanical Behavior of Fiber-Reinforced Ceramic Matrix Composites." In Ceramic Matrix Composites, 40–64. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2014. http://dx.doi.org/10.1002/9781118832998.ch3.
Cinibulk, M. K., R. S. Hay, and R. E. Dutton. "Textured Calcium Hexaluminate Fiber-Matrix Interphase for Ceramic-Matrix Composites." In Ceramic Microstructures, 731–39. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4615-5393-9_75.
Park, M. J., H. J. Song, B. S. Lee, J. S. Jang, M. S. Hong, and J. C. Lee. "Properties of Porous Si/SiC Fiber Composites Prepared by Infiltrating Carbon Fiber Composites with Liquid Silicon." In High Temperature Ceramic Matrix Composites, 341–46. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch54.
Müller, B. R., D. Ekenhorst, K. W. Brzezinka, and M. P. Hentschel. "Fiber Induced Failure of Carbon/Carbon Composites." In High Temperature Ceramic Matrix Composites, 175–80. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch28.
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.
Kerans, Ronald J., Randall S. Hay, Emmanuel E. Boakye, Kristen A. Keller, Tai-il Mah, Triplicane A. Parthasarathy, and Michael K. Cinibulk. "Oxide Fiber-Coatings for Interface Control in Ceramic Composites." In High Temperature Ceramic Matrix Composites, 127–35. Weinheim, FRG: Wiley-VCH Verlag GmbH & Co. KGaA, 2006. http://dx.doi.org/10.1002/3527605622.ch22.
Тези доповідей конференцій з теми "Ceramic Fiber-Matrix Composites (CFMC)":
1
More, Karren L., Peter L. Tortorelli, Larry R. Walker, Josh B. Kimmel, Narendernath Miriyala, Jeffrey R. Price, Harry E. Eaton, Ellen Y. Sun, and Gary D. Linsey. "Evaluating Environmental Barrier Coatings on Ceramic Matrix Composites After Engine and Laboratory Exposures." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30630.
SiC/SiC continuous fiber-reinforced ceramic matrix composite (CFCC) combustor liners having protective environmental barrier coatings (EBCs) applied to the liner working surfaces have been field-tested in a Solar Turbines’ Centaur 50S SoLoNOx engine at the Chevron, Bakersfield, CA engine test site. This latest engine test ran for a total of 13,937h. The EBCs significantly increased the lifetime of the in-service liners compared with uncoated CFCC liners used in previous field-tests. The engine test was concluded when a routine borescope inspection revealed the formation of a small hole in the inner liner. Extensive microstructural evaluation of both the inner and outer liners was conducted after removal from the engine. Post-test analysis indicated that numerous degradation mechanisms contributed to the EBC and CFCC damage observed on the liners, including EBC volatilization, sub-surface CFCC oxidation and recession, and processing defects which resulted in localized EBC spallation and accelerated CFCC oxidation. The characterization results obtained from these field-tested liners have been compared with the analyses of similarly-processed CFCC/EBCs that were laboratory-tested in a high-pressure, high temperature exposure facility (the ORNL “Keiser Rig”) for >6000h.
2
van Roode, Mark, William D. Brentnall, Kenneth O. Smith, Bryan D. Edwards, Leslie J. Faulder, and Paul F. Norton. "Ceramic Stationary Gas Turbine Development Program: Third Annual Summary." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-460.
The goal of the Ceramic Stationary Gas Turbine (CSGT) Development Program, under the sponsorship of the United States Department of Energy (DOE), Office of Industrial Technologies (OIT), is to improve the performance (fuel efficiency, output power, exhaust emissions) of stationary gas turbines in cogeneration through the selective replacement of hot section components with ceramic parts. The program, currently in Phase II focuses on detailed engine and component design, ceramic component fabrication and testing, establishment of a long term materials property data base, the development of supporting nondestructive evaluation (NDE) technologies, and the application of ceramic component life prediction. A 4000 hr engine field test is planned for Phase III of the program. This paper summarizes progress from January 1995 through January 1996. First generation designs of the primary ceramic components (first stage blades and nozzles, combustor liners) for the program engine, the Solar Centaur 50S, and of the secondary metallic components interfacing with the ceramic parts were completed. The fabrication of several components has been completed as well. These components were evaluated in rigs and the Centaur 50S test engine. NTI64 (Norton Advanced Ceramics) and GN-10 (AlliedSignal Ceramic Components) silicon nitride dovetail blades were cold and hot spin tested and engine tested at the baseline nominal turbine rotor inlet temperature (TRIT) of 1010°C. Full scale SiC/SiC continuous fiber-reinforced ceramic matrix composite (CFCC) liners (B.F. Goodrich Aerospace) were also rig tested and engine tested at the nominal baseline TRIT of 1010°C. One of the engine tests, incorporating both the GN-10 blades and the full scale SiC/SiC CFCC liners, was performed for 21.5 hrs (16 hrs at 100% load) with six start/stop cycles. A cumulative 24.5 hrs of engine testing was performed at the end of January, 1996. The ceramic components were in good condition following completion of the testing. Subscale Hexoloy® SA silicon carbide (Carborundum) and enhanced SiC/SiC CFCC (DuPont Lanxide Composites) and Al2O3/Al2O3 CFCC (Babcock & Wilcox) combustor liners were tested to evaluate mechanical attachment, durability and/or emissions reduction potential. The enhanced SiC/SiC CFCC of DuPont Lanxide Composites demonstrated superior durability in subscale combustor testing and this material was subsequently selected for the fabrication of full scale combustor liners for final engine rig testing in Phase II and field testing in Phase III of the program. Enhanced SiC/SiC CFCC liners also showed significantly reduced emissions of NOx and CO when compared with conventionally cooled subscale metallic liners. This observation is believed to apply generally to “hot wall” combustor substrates. The emissions results for the enhanced SiC/SiC CFCC liners were paralleled by similar emissions levels of NOx and CO monitored during engine testing with B.F. Goodrich Aerospace SiC/SiC CFCC combustor liners. NOx levels below 25 ppmv and CO levels below 10 ppmv were measured during the engine testing. Short term (1,000 hrs) creep testing of candidate ceramic materials under approximate nozzle “hot spot” conditions was completed and long term (5000–10,000 hrs) creep testing is in progress. The selected nozzle material, SN-88 silicon nitride, has survived over 5,500 hrs at 1288°C and 186 MPa stress at the end of January, 1996.
3
Price, Jeffrey, Josh Kimmel, Xiaoqun Chen, Arun Bhattacharya, Anthony Fahme, and Joel Otsuka. "Advanced Materials for Mercury™ 50 Gas Turbine Combustion System." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90568.
Solar Turbines Incorporated (Solar), under cooperative agreement number DE-FC26-00CH 11049, is improving the durability of gas turbine combustion systems while reducing life cycle costs. This project is part of the Advanced Materials in Advanced Industrial Gas Turbines program in DOE’s Office of Distributed Energy. The targeted engine is the Mercury™ 50 gas turbine, which was developed by Solar under the DOE Advanced Turbine Systems (ATS) program (DOE contract number DE-FC21-95MC31173). The ultimate goal of the program is to demonstrate a fully integrated Mercury 50 combustion system, modified with advanced materials technologies, at a host site for 4,000 hours. The program has focused on a dual path development route to define an optimum mix of technologies for the Mercury 50 turbine and future Solar products. For liner and injector development, multiple concepts including high thermal resistance thermal barrier coatings (TBC), oxide dispersion strengthened (ODS) alloys, continuous fiber ceramic composites (CFCC), and monolithic ceramics were evaluated. An advanced TBC system for the combustor was down-selected for field evaluation. ODS alloys were down-selected for the fuel injector tip application. Preliminary component and sub-scale testing was conducted to determine material properties and demonstrate proof-of-concept. Full-scale rig and engine testing were used to validate engine performance prior to field evaluation. Field evaluation of ceramic matrix composite liners in the Centaur® 50 gas turbine engine [1–3] which was previously conducted under the DOE sponsored Ceramic Stationary Gas Turbine program (DE-AC02-92CE40960), is continuing under this program. This paper is a status review of the program, detailing the current progress of the development and field evaluations.
4
van Roode, Mark, William D. Brentnall, Paul F. Norton, and Bryan D. Edwards. "Ceramic Stationary Gas Turbine Development Program: Second Annual Summary." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-459.
A program is being performed under the sponsorship of the United States Department of Energy, Office of Industrial Technologies, to improve the performance of stationary gas turbines in cogeneration through the selective replacement of hot section components with ceramic parts. Solar Turbines Incorporated leads a team that includes major U.S. and offshore suppliers of ceramic components, recognized test laboratories and a cogeneration enduser to develop and demonstrate ceramic insertion in a stationary gas turbine with the objectives of more efficient engine operation, resulting in significant fuel savings, increased output power, and reduced emissions. The engine selected for the program, the Centaur 50 is being retrofitted with first stage ceramic blades, first stage ceramic nozzles, and a ceramic combustor liner. The engine hot section is being redesigned to accommodate the ceramic parts to the existing metallic support structure. Detailed design of the ceramic components and of the interfacing metallic support structure has been completed. Two blade designs with different attachments and a nozzle design with a modified airfoil geometry have been developed. Three combustor liner designs are being evaluated based on monolithic tiles or rings, or integral cylinders of continuous fiber-reinforced ceramic matrix composites (CFCC). Fabrication of first generation prototype blades and nozzles is in progress. Fabrication of subscale combustor hardware has been completed. Materials property data are being gathered in support of the ceramic component design and life prediction. Fast fracture and dynamic fatigue testing were performed for the candidate blade and nozzle materials. Creep and oxidation testing is in progress. Nondestructive methodologies are being applied to test specimens, simulated components, subscale hardware and prototype components. A Centaur 50 engine was procured and has been modified for ceramic component testing in a full-size engine configuration.
5
Corman, Gregory S., Jeffrey T. Heinen, and Raymond H. Goetze. "Ceramic Composites for Industrial Gas Turbine Engine Applications: DOE CFCC Phase 1 Evaluations." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-387.
Conceptual design evaluations of the use of continuous fiber ceramic composite (CFCC) turbine shrouds and combustor liners in an industrial gas turbine engine were performed under Phase 1 of the DOE CFCC program. Significant engine performance improvements were predicted with the use of CFCC components. Five composite systems were evaluated for use as shrouds and combustor liners, the results of which are discussed with particular reference to Toughened Silcomp. Several current CFCC materials were judged to be relatively close to meeting the short term performance requirements of such a system. However, additional CFCC property data are required for significant component design optimization and life prediction, two key design steps that must be completed before ceramic composites can be utilized in large gas turbines.
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Snead, Lance L., Yutai Katoh, William E. Windes, Robert J. Shinavski, and Timothy D. Burchell. "Ceramic Composites for Near Term Reactor Application." In Fourth International Topical Meeting on High Temperature Reactor Technology. ASMEDC, 2008. http://dx.doi.org/10.1115/htr2008-58050.
Currently, two composites types are being developed for incore application: carbon fiber carbon composite (CFC), and silicon carbide fiber composite (SiC/SiC.) Irradiation effects studies have been carried out over the past few decades yielding radiation-tolerant CFC’s and a composite of SiC/SiC with no apparent degradation in mechanical properties to very high neutron exposure. While CFC’s can be engineered with significantly higher thermal conductivity, and a slight advantage in manufacturability than SiC/SiC, they do have a neutron irradiation-limited lifetime. The SiC composite, while possessing lower thermal conductivity (especially following irradiation), appears to have mechanical properties insensitive to irradiation. Both materials are currently being produced to sizes much larger than that considered for nuclear application. In addition to materials aspects, results of programs focusing on practical aspects of deploying composites for near-term reactors will be discussed. In particular, significant progress has been made in the fabrication, testing, and qualification of composite gas-cooled reactor control rod sheaths and the ASTM standardization required for eventual qualification.
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Dharani, L., and S. Haug. "Fiber/matrix interface properties of hybrid ceramic matrix composites." In 40th Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1334.
PATEL, DIPEN, TRIPLICANE PARTHASARATHY, DANIEL RAPKING, MICHAEL BRAGINSKY, and CRAIG PRZYBYLA. "Quantification and Classification of Continuous Ceramic Fiber Reinforced Ceramic Matrix Composites Microstructures." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15306.
Miriyala, Narendernath, Jane F. Simpson, Vijay M. Parthasarathy, and William D. Brentnall. "The Evaluation of CFCC Liners After Field-Engine Testing in a Gas Turbine." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-395.
In a program sponsored by the U.S. Department of Energy (DOE), Solar Turbines Incorporated is currently investigating the use of ceramics in industrial gas turbines by selectively replacing cooled metallic components with uncooled ceramic parts. As part of this program, Solar has developed CFCC (SiC/SiC) combustor liners and demonstrated their potential for low emissions in three field-engine tests for a total duration of over 3000 hours. The durability of the SiC/SiC liners appears to be primarily limited by surface recession, composite embrittlement and fiber degradation (particularly for CG-Nicalon). The microstructural, mechanical properties, and nondestructive evaluation of the CFCC liners after the three field tests are discussed in this paper.
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Szweda, A., T. E. Easler, D. R. Petrak, and V. A. Black. "Continuous Fiber Ceramic Matrix Composites for Gas Turbine Applications." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-189.
Continuous fiber ceramic composites (CFCCs) are being considered as high temperature structural materials for gas turbine applications due to their high temperature capability, toughness, and durability. Polymer impregnation and pyrolysis (PIP) derived CFCCs are one class of these materials that can be fabricated using widely available polymer composite processing methods. This paper will discuss the general PIP fabrication process and thermo-mechanical properties of these materials, and show examples of complex prototype gas turbine components that have been fabricated and evaluated.
Звіти організацій з теми "Ceramic Fiber-Matrix Composites (CFMC)":
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R. A. Wagner. Continuous Fiber Ceramic Composites (CFCC). Office of Scientific and Technical Information (OSTI), December 2002. http://dx.doi.org/10.2172/806820.
Besmann, T. M., D. P. Stinton, E. R. Kupp, S. Shanmugham, and P. K. Liaw. Fiber-matrix interfaces in ceramic composites. Office of Scientific and Technical Information (OSTI), December 1996. http://dx.doi.org/10.2172/425298.
Hurley, JP. Support Services for Ceramic Fiber-Ceramic Matrix Composites. Office of Scientific and Technical Information (OSTI), August 2001. http://dx.doi.org/10.2172/788362.
Hurley, J. P., and J. W. Nowok. Support Services for Ceramic Fiber-Ceramic Matrix Composites. Office of Scientific and Technical Information (OSTI), June 1999. http://dx.doi.org/10.2172/8836.
Hurley, J. P., and C. R. Crocker. Support Services for Ceramic Fiber-Ceramic Matrix Composites. Office of Scientific and Technical Information (OSTI), June 2000. http://dx.doi.org/10.2172/768818.
Hurley, J. P. Support Services for Ceramic Fiber-Ceramic Matrix Composites. Office of Scientific and Technical Information (OSTI), June 2000. http://dx.doi.org/10.2172/814089.
R. Suplinskas G. DiBona and W. Grant. Continuous Fiber Ceramic Composite (CFCC) Program: Gaseous Nitridation. Office of Scientific and Technical Information (OSTI), October 2001. http://dx.doi.org/10.2172/791414.
Lowden, R. A. Characterization and control of the fiber-matrix interface in ceramic matrix composites. Office of Scientific and Technical Information (OSTI), March 1989. http://dx.doi.org/10.2172/6855809.
Hurley, J. P. Support services for Ceramic Fiber-Ceramic Matrix Composites. Annual technical progress report. Office of Scientific and Technical Information (OSTI), September 1995. http://dx.doi.org/10.2172/101035.
Hurley, J. P., and J. W. Nowok. Support services for ceramic fiber-ceramic matrix composites. Annual technical progress report. Office of Scientific and Technical Information (OSTI), December 1996. http://dx.doi.org/10.2172/458591.
