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  • 1
    Electronic Resource
    Electronic Resource
    Effect of Environment on the Stress-Rupture Behavior of a Carbon-Fiber-Reinforced Silicon Carbide Ceramic Matrix Composite (2004)
    Westerville, Ohio : American Ceramics Society
    Journal of the American Ceramic Society 87 (2004), S. 0 
    Details
    ISSN: 1551-2916
    Source: Blackwell Publishing Journal Backfiles 1879-2005
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Notes: Stress-rupture tests were conducted in air, under vacuum, and in steam-containing environments to identify the failure modes and degradation mechanisms of a carbon-fiber-reinforced silicon carbide (C/SiC) composite at two temperatures, 600° and 1200°C. Stress-rupture lives in air and steam-containing environments (50–80% steam with argon) are similar for a stress of 69 MPa at 1200°C. Lives of specimens tested in a 20% steam/argon environment were about twice as long. For tests conducted at 600°C, composite life in 20% steam/argon was 30 times longer than life in air. Thermogravimetric analysis of the carbon fibers was conducted under conditions similar to the stress-rupture tests. The oxidation rate of the fibers in the various environments correlated with the composite stress-rupture lives. Examination of the failed specimens indicated that oxidation of the carbon fibers was the primary damage mode for specimens tested in air and steam environments at both temperatures.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1111/j.1551-2916.2004.01536.x
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Effect of Environment on the Stress-Rupture Behavior of a Carbon-Fiber-Reinforced Silicon Carbide Ceramic Matrix Composite (2004)
    Wiley
    Details
    Publication Date: 2004-08-01
    Print ISSN: 0002-7820
    Electronic ISSN: 1551-2916
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Wiley on behalf of American Ceramic Society.
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    PAPER CURRENT
  • 3
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    Effect of Environment on the Stress- Rupture Behavior of a C/SiC Composite Studied (2002)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Advanced reusable launch vehicles will likely incorporate fiber-reinforced ceramic matrix composites (CMC's) in critical propulsion and airframe components. The use of CMC's is highly desirable to save weight, improve reuse capability, and increase performance. One of the candidate CMC materials is carbon-fiber-reinforced silicon carbide (C/SiC). In potential propulsion applications, such as turbopump rotors and nozzle exit ramps, C/SiC components will be subjected to a service cycle that includes mechanical loading under complex, high-pressure environments containing hydrogen, oxygen, and steam. Degradation of both the C fibers and the SiC matrix are possible in these environments. The objective of this effort was to evaluate the mechanical behavior of C/SiC in various environments relevant to reusable launch vehicle applications. Stress-rupture testing was conducted at the NASA Glenn Research Center on C/SiC specimens in air and steam-containing environments. Also, the oxidation kinetics of the carbon fibers that reinforce the composite were monitored by thermogravimetric analysis in the same environments and temperatures used for the stress-rupture tests of the C/SiC composite specimens. The stress-rupture lives obtained for C/SiC tested in air and in steam/argon mixtures are shown in the following bar chart. As is typical for most materials, lives obtained at the lower temperature (600 C) are longer than for the higher temperature (1200 C). The effect of environment was most pronounced at the lower temperature, where the average test duration in steam at 600 C was at least 30 times longer than the lives obtained in air. The 1200 C data revealed little difference between the lives of specimens tested in air and steam at atmospheric pressure.
    Keywords: Nonmetallic Materials
    Type: Research and Technology 2001; NASA/TM-2002-211333
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    SiC/SiC Ceramic Matrix Composites Developed for High-Temperature Space Transportation Applications (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Researchers at the NASA Glenn Research Center have been developing durable, high-temperature ceramic matrix composites (CMCs) with silicon carbide (SiC) matrices and SiC or carbon fibers for use in advanced reusable launch vehicle propulsion and airframe applications in the Next Generation Launch Technology (NGLT) Program. These CMCs weigh less and are more durable than competing metallic alloys, and they are tougher than silicon-based monolithic ceramics. Because of their high specific strength and durability at high temperatures, CMCs such as C/SiC (carbon- fiber-reinforced silicon carbide) and SiC/SiC (silicon-carbide-fiber-reinforced silicon carbide) may increase vehicle performance and safety significantly and reduce the cost of transporting payloads to orbit.
    Keywords: Composite Materials
    Type: Research and Technology 2004; NASA/TM-2005-213419
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Development of Ceramic Matrix Composite Turbine Blisks for Rocket Engines (2000)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Ceramic matrix composite (CMC) integrally bladed turbine disks (blisks) are being considered for use in various advanced propulsion systems for space vehicles. The successful development of this technology can significantly impact National Aeronautics and Space Administration (NASA) space transportation missions, by enabling new efficient systems that can operate at higher temperatures, while reducing costs. Composite blisks comprised of carbon (C) fibers and a silicon carbide (SiC) ceramic matrix were designed, fabricated, characterized, and tested by a multidisciplinary team involving materials, design, structural analysis, turbomachinery, and nondestructive evaluation representatives from government, academia, and industry during a 4.5 year effort led by the NASA Marshall Space Flight Center (MSFC). The testing of several of these blisks, which were developed in the Simplex Turbopump CMC Blisk ]Program for use in rocket engine turbopumps, was recently completed. CMC blisks offer potential advantages in rocket engine turbopumps including increased safety resulting from increased operating temperature margins and greater pump reliability, and decreased costs resulting from improved turbopump performance. The progress that was achieved in that development effort is reviewed, and some of the technology that could be applied to other advanced space transportation propulsion systems is discussed.
    Keywords: Composite Materials
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Fabrication and Testing of Ceramic Matrix Composite Propulsion Components (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A viewgraph presentation outlines NASA's goals for the Second and Third Generation Reusable Launch Vehicles, placing emphasis on improving safety and decreasing the cost of transporting payloads to orbit. The use of ceramic matrix composite (CMC) technology is discussed. The development of CMC components, such as the Simplex CMC Blisk, cooled CMC nozzle ramps, cooled CMC thrust chambers, and CMC gas generators, are described, including challenges, test results, and likely future developments.
    Keywords: Spacecraft Propulsion and Power
    Type: Aerospace Materials, Processes and Environmental Technology; Jun 26, 2000 - Jun 29, 2000; Bellevue, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Importance of Measuring SiC Fiber Diameter Prior to Conducting Fiber Stress Rupture / Creep Tests? (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A very significant amount of SiC fiber creep / stress rupture data has been generated and reported in the past by various researchers. Due to the difficulty of measuring fiber diameter and the amount of time required to make accurate measurements, researchers have quite often used an accepted average diameter value (which is fiber type-dependent) when determining the load that will be applied to a fiber to generate a specific stress during testing. Of course, this approach has less of an effect on data scatter when the individual fibers in a tow have very similar diameters (minimal fiber-to-fiber variation in diameter). NASA GRC has begun using a laser fiber diameter measurement system, and we are considering eventually characterizing each SiC fiber prior to testing in creep/stressed oxidation. The laser system will be described in this presentation, as well as examples of fiber diameter data obtained in the past at AFRL. We are currently discussing the merits of using an average diameter in testing/data analysis vs. using a measured or "known" diameter. Information about our current intermediate temperature SiC fiber stress rupture testing will also be provided.
    Keywords: Composite Materials
    Type: GRC-E-DAA-TN51791 , Annual Conference on Composites, Materials, and Structures; Jan 22, 2018 - Jan 25, 2018; Cocoa Beach, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Characterization of C/SiC Ceramic Matrix Composites (CMCs) with Novel Interface Fiber Coatings (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ceramic Matrix Composites (CMCs) are attractive candidate aerospace materials due to their high specific strength, low density and high temperature capabilities. The National Aeronautics and Space Administration (NASA) is pursuing the use of CMC components in advanced Reusable Launch Vehicle (RLV) propulsion applications. Carbon fiber-reinforced silicon carbide (C/SiC) is the primary material of interest for a variety of RLV propulsion applications. These composites consist of high-strength carbon fibers and a high modulus, oxidation resistant matrix. For RLV propulsion applications, environmental durability will be critical. Two types of carbon fibers were processed with both standard (pyrolytic carbon) and novel (multilayer and pseudoporous) types of interface coatings as part of a study investigating various combinations of constituents. The benefit of protecting the composites with a surface sealant was also investigated. The strengths, durability in oxidizing environments, and microstructures of these developmental composite materials are presented. The novel interface coatings and the surface sealant show promise for protecting the carbon fibers from the oxidizing environment.
    Keywords: Nonmetallic Materials
    Type: National Space and Missile Materials Symposium (NSMMS); Jun 24, 2002 - Jun 28, 2002; Colorado Springs, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Oxide_Oxide Ceramic Matrix Composite (CMC) Exhaust Mixer Development in the NASA Environmentally Responsible Aviation (ERA) Project (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: LibertyWorks, a subsidiary of Rolls-Royce Corporation, first studied CMC (ceramic matrix composite) exhaust mixers for potential weight benefits in 2008. Oxide CMC potentially offered weight reduction, higher temperature capability, and the ability to fabricate complex-shapes for increased mixing and noise suppression. In 2010, NASA was pursuing the reduction of NOx emissions, fuel burn, and noise from turbine engines in Phase I of the Environmentally Responsible Aviation (ERA) Project (within the Integrated Systems Research Program). ERA subtasks, including those focused on CMC components, were being formulated with the goal of maturing technology from Proof of Concept Validation (Technology Readiness Level 3 (TRL 3)) to System/Subsystem or Prototype Demonstration in a Relevant Environment (TRL 6). LibertyWorks, a subsidiary of Rolls-Royce Corporation, first studied CMC (ceramic matrix composite) exhaust mixers for potential weight benefits in 2008. Oxide CMC potentially offered weight reduction, higher temperature capability, and the ability to fabricate complex-shapes for increased mixing and noise suppression. In 2010, NASA was pursuing the reduction of NOx emissions, fuel burn, and noise from turbine engines in Phase I of the Environmentally Responsible Aviation (ERA) Project (within the Integrated Systems Research Program). ERA subtasks, including those focused on CMC components, were being formulated with the goal of maturing technology from Proof of Concept Validation (Technology Readiness Level 3 (TRL 3)) to System/Subsystem or Prototype Demonstration in a Relevant Environment (TRL 6). Oxide CMC component at both room and elevated temperatures. A TRL5 (Component Validation in a Relevant Environment) was attained and the CMC mixer was cleared for ground testing on a Rolls-Royce AE3007 engine for performance evaluation to achieve TRL 6.
    Keywords: Mechanical Engineering; Aircraft Propulsion and Power
    Type: GT2015-43593 , GRC-E-DAA-TN18450 , ASME Turbo Expo 2015: Ceramics GT2015; Jun 15, 2015 - Jun 19, 2015; Montreal; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Diffusion Bonding of Silicon Carbide for MEMS-LDI Applications (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A robust joining approach is critically needed for a Micro-Electro-Mechanical Systems-Lean Direct Injector (MEMS-LDI) application which requires leak free joints with high temperature mechanical capability. Diffusion bonding is well suited for the MEMS-LDI application. Diffusion bonds were fabricated using titanium interlayers between silicon carbide substrates during hot pressing. The interlayers consisted of either alloyed titanium foil or physically vapor deposited (PVD) titanium coatings. Microscopy shows that well adhered, crack free diffusion bonds are formed under optimal conditions. Under less than optimal conditions, microcracks are present in the bond layer due to the formation of intermetallic phases. Electron microprobe analysis was used to identify the reaction formed phases in the diffusion bond. Various compatibility issues among the phases in the interlayer and substrate are discussed. Also, the effects of temperature, pressure, time, silicon carbide substrate type, and type of titanium interlayer and thickness on the microstructure and composition of joints are discussed.
    Keywords: Metals and Metallic Materials
    Type: 31st. International Conference and Exposition on Advanced Ceramics and Composites; Jan 21, 2007 - Jan 26, 2007; Daytona Beach, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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