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  • 1
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    Hypervelocity Impact (HVI) (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target RCC16R was to study hypervelocity impacts through the reinforced carbon-carbon (RCC) panels of the Wing Leading Edge. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight.
    Keywords: Composite Materials
    Type: NASA/CR-2007-214885/VOL7
    Format: application/pdf
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  • 2
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    Hypervelocity Impact (HVI) (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target Fg(RCC)-2 was to study hypervelocity impacts through the reinforced carbon-carbon (RCC) panels of the Wing Leading Edge. Fiberglass was used in place of RCC in the initial tests. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight.
    Keywords: Composite Materials
    Type: NASA/CR-2007-214885/VOL6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Hypervelocity Impact (HVI) (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target C-1 was to study hypervelocity impacts on the reinforced carbon-carbon (RCC) panels of the Wing Leading Edge. Fiberglass was used in place of RCC in the initial tests. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight.
    Keywords: Composite Materials
    Type: NASA/CR-2007-214885/VOL3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Ceramic fiber insulation impregnated with an infra-red retardant coating and method for production thereof (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The invented insulation is a ceramic fiber insulation wherein the ceramic fibers are treated with a coating which contains transition metal oxides. The invented process for coating the insulation is a process of applying the transition metal oxide coating to the fibers of the insulation after the fibers have been formed into a tile or other porous body. The coating of transition metal oxide lowers the transmittance of radiation through the insulation thereby lowering the temperature of the backface of the insulation and better protecting the structure that underlies the insulation.
    Keywords: Composite Materials
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  • 5
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    Damage Accumulation and Failure of Plasma-Sprayed Thermal Barrier Coatings under Thermal Gradient Cyclic Conditions (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Thermal barrier coatings will be more aggressively designed to protect gas turbine engine hot-section components in order to meet future engine higher fuel efficiency and lower emission goals. A fundamental understanding of the sintering and thermal cycling induced delamination of thermal barrier coating systems under engine-like heat flux conditions will potentially help to improve the coating temperature capability. In this study, a test approach is established to emphasize the real-time monitoring and assessment of the coating thermal conductivity, which can initially increase under the steady-state high temperature thermal gradient test due to coating sintering, and later decrease under the thermal gradient cyclic test due to coating cracking and delamination. Thermal conductivity prediction models have been established for a ZrO2-(7- 8wt%)Y2O3 model coating system in terms of heat flux, time, and testing temperatures. The coating delamination accumulation is then assessed based on the observed thermal conductivity response under the combined steady-state and cyclic thermal gradient tests. The coating thermal gradient cycling associated delaminations and failure mechanisms under simulated engine heat-flux conditions will be discussed in conjunction with the coating sintering and fracture testing results.
    Keywords: Composite Materials
    Type: 29th Annual International Conference on Advanced Ceramics and Composites; Jan 23, 2005 - Jan 28, 2005; Cocoa Beach, FL; United States|Symposium on Advanced Ceramic Coatings for Structural, Environmental and Functional Applications; Jan 23, 2005 - Jan 28, 2005; Cocoa Beach, FL; United States
    Format: text
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  • 6
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    Environmental Barrier Coatings for Turbine Engines: A Design and Performance Perspective (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ceramic thermal and environmental barrier coatings (TEBC) for SiC-based ceramics will play an increasingly important role in future gas turbine engines because of their ability to effectively protect the engine components and further raise engine temperatures. However, the coating long-term durability remains a major concern with the ever-increasing temperature, strength and stability requirements in engine high heat-flux combustion environments, especially for highly-loaded rotating turbine components. Advanced TEBC systems, including nano-composite based HfO2-aluminosilicate and rare earth silicate coatings are being developed and tested for higher temperature capable SiC/SiC ceramic matrix composite (CMC) turbine blade applications. This paper will emphasize coating composite and multilayer design approach and the resulting performance and durability in simulated engine high heat-flux, high stress and high pressure combustion environments. The advances in the environmental barrier coating development showed promise for future rotating CMC blade applications.
    Keywords: Composite Materials
    Type: E-17380 , 33rd International Conference on Advanced Ceramics and Composites; Jan 18, 2009 - Jan 23, 2009; Daytona Beach, Fl; United States
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  • 7
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    Low Conductivity Thermal Barrier Coatings (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Thermal barrier coatings will be more aggressively designed to protect gas turbine engine hot-section components in order to meet future engine higher fuel efficiency and lower emission goals. In this presentation, thermal barrier coating development considerations and requirements will be discussed. An experimental approach is established to monitor in real time the thermal conductivity of the coating systems subjected to high-heat-flux, steady-state and cyclic temperature gradients. Advanced low conductivity thermal barrier coatings have also been developed using a multi-component defect clustering approach, and shown to have improved thermal stability. The durability and erosion resistance of low conductivity thermal barrier coatings have been improved utilizing advanced coating architecture design, composition optimization, in conjunction with more sophisticated modeling and design tools.
    Keywords: Composite Materials
    Type: NASA/TM-2005-213857 , E-15227 , School of Materials Engineering Seminar; Feb 28, 2005; West Lafayette, IN; United States
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  • 8
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    Method of synthesizing small-diameter carbon nanotubes with electron field emission properties (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Carbon nanotube material having an outer diameter less than 10 nm and a number of walls less than ten are disclosed. Also disclosed are an electron field emission device including a substrate, an optionally layer of adhesion-promoting layer, and a layer of electron field emission material. The electron field emission material includes a carbon nanotube having a number of concentric graphene shells per tube of from two to ten, an outer diameter from 2 to 8 nm, and a nanotube length greater than 0.1 microns. One method to fabricate carbon nanotubes includes the steps of (a) producing a catalyst containing Fe and Mo supported on MgO powder, (b) using a mixture of hydrogen and carbon containing gas as precursors, and (c) heating the catalyst to a temperature above 950.degree. C. to produce a carbon nanotube. Another method of fabricating an electron field emission cathode includes the steps of (a) synthesizing electron field emission materials containing carbon nanotubes with a number of concentric graphene shells per tube from two to ten, an outer diameter of from 2 to 8 nm, and a length greater than 0.1 microns, (b) dispersing the electron field emission material in a suitable solvent, (c) depositing the electron field emission materials onto a substrate, and (d) annealing the substrate.
    Keywords: Composite Materials
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  • 9
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    Formation and Growth of Micro and Macro Bubbles on Copper-Graphite Composite Surfaces (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Micro scale boiling behavior in the vicinity of graphite micro-fiber tips on the coppergraphite composite boiling surfaces is investigated. It is discovered that a large number of micro bubbles are formed first at the micro scratches and cavities on the copper matrix in pool boiling. In virtue of the non-wetting property of graphite, once the growing micro bubbles touch the graphite tips, the micro bubbles are sucked by the tips and merged into larger micro bubbles sitting on the tips. The micro bubbles grow rapidly and coalesce to form macro bubbles, each of which sitting on several tips. The growth processes of the micro and macro bubbles are analyzed and formulated followed by an analysis of bubble departure on the composite surfaces. Based on these analyses, the enhancement mechanism of the pool boiling heat transfer on the composite surfaces is clearly revealed. Experimental results of pool boiling heat transfer both for water and Freon-113 on the composite surfaces convincingly demonstrate the enhancement effects of the unique structure of Cu-Gr composite surfaces on boiling heat transfer.
    Keywords: Composite Materials
    Type: 45th AIAA Aerospace Science Meeting and Exhibit; Jan 08, 2007 - Jan 12, 2007; Reno, NV; United States
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  • 10
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    Processing and Structural Advantages of the Sylramic-iBN SiC Fiber for SiC/SiC Components (2008)
    In:  Other Sources
    Details
    Publication Date: 2019-07-19
    Description: The successful high-temperature application of complex-shaped SiC/SiC components will depend on achieving as high a fraction of the as-produced fiber strength as possible during component fabrication and service. Key issues center on a variety of component architecture, processing, and service-related factors that can reduce fiber strength, such as fiber-fiber abrasion during architecture shaping, surface chemical attack during interphase deposition and service, and intrinsic flaw growth during high-temperature matrix formation and composite creep. The objective of this paper is to show that the NASA-developed Sylramic-iBN SiC fiber minimizes many of these issues for state-of-the-art melt-infiltrated (MI) SiC/BN/SiC composites. To accomplish this, data from various mechanical tests are presented that compare how different high performance SiC fiber types retain strength during formation of complex architectures, during processing of BN interphases and MI matrices, and during simulated composite service at high temperatures.
    Keywords: Composite Materials
    Type: 27th Annual International Conference on Advanced Ceramics and Composites; Jan 21, 2002 - Jan 26, 2002; Cocoa Beach, FL; United States
    Format: text
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