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  • 1
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    Long-Term Cyclic Oxidation Behavior of Uncoated and Coated Re-108 and In-939 at 980 and 870 C (2000)
    In:  Other Sources
    Details
    Publication Date: 2011-08-23
    Description: Very long-term cyclic oxidation behavior of Re108 and In939 with and without a protective coating was evaluated at 980 and 870 C, respectively. Re-108 and In-939 without a protective coating began to show a rapid weight loss at 3000 h due to scale spallation, indicating the need for an oxidation protective coating for longer than thousands of hours of oxidative life. NiAl-base coatings of a vapor phase aluminide (VPA), a pack aluminide (CODEP), and a slurry paint aluminide (SERMALOY J) were applied on Re-108 and In-939. The VPA and CODEP on Re-108 and all three coatings on In-939 showed excellent cyclic oxidation resistance out to 10,000 h. Coated alloys were annealed in an inert atmosphere to determine the loss of Al from the coating into the alloy substrate through diffusion. The Al loss from the coating through diffusion was twice as great as the Al loss through oxidation after 10,000 h of cyclic exposure. The oxidation life of VPA-coated Re-108 was estimated by calculating the amount of Al initially available for protective oxidation and the amount of Al lost through oxidation and diffusion.
    Keywords: Metals and Metallic Materials
    Type: Journal of Thermal Spray Technology; Volume 9; No. 1; 121-127
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    NiAl Coatings Investigated for Use in Reusable Launch Vehicles (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: As part of its major investment in the area of advanced space transportation, NASA is developing new technologies for use in the second- and third-generation designs of reusable launch vehicles. Among the prototype rocket engines being considered for these launch vehicles are those designed to use liquid hydrogen as the fuel and liquid oxygen as the oxidizer. Advanced copper alloys, such as copper-chromium-niobium (Cu-8(at.%)Cr- 4(at.%)Nb, also referred to as GRCop-84), which was invented at the NASA Glenn Research Center, are being considered for use as liner materials in the combustion chambers and nozzle ramps of these engines. However, previous experience has shown that, in rocket engines using liquid hydrogen and liquid oxygen, copper alloys are subject to a process called blanching, where the material undergoes environmental attack under the action of the combustion gases. In addition, the copper alloy liners undergo thermomechanical fatigue, which often results in an initially square cooling channel deforming into a dog-house shape. Clearly, there is an urgent need to develop new coatings to protect copper liners from environmental attack inside rocket chambers and to lower the temperature of the liners to reduce the probability of deformation and failure by thermomechanical fatigue.
    Keywords: Metals and Metallic Materials
    Type: Research and Technology 2002; NASA/TM-2003-211990
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Oxidation Behavior of Copper Alloy Candidates for Rocket Engine Applications (Technical Poster) (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A rocket engine's combustion chamber is lined with material that is highly conductive to heat in order to dissipate the huge thermal load (evident in a white-hot exhaust plume). Because of its thermal conductivity copper is the best choice of liner material. However, the mechanical properties of pure copper are inadequate to withstand the high stresses, hence, copper alloys are needed in this application. But copper and its alloys are prone to oxidation and related damage, especially "blanching" (an oxidation-reduction mode of degradation). The space shuttle main engine combustion chamber is lined with a Cu-Ag-Zr alloy, "NARloy-Z", which exhibits blanching. A superior liner is being sought for the next generation of RLVs (Reusable Launch Vehicles) It should have improved mechanical properties and higher resistance to oxidation and blanching, but without substantial penalty in thermal conductivity. GRCop84, a Cu-8Cr-4Nb alloy (Cr2Nb in Cu matrix), developed by NASA Glenn Research Center (GRC) and Case Western Reserve University, is a prime contender for RLV liner material. In this study, the oxidation resistance of GRCop-84 and other related/candidate copper alloys are investigated and compared
    Keywords: Metals and Metallic Materials
    Type: TMS IV Meeting; Oct 06, 2002 - Oct 10, 2002; Columbus, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Effect of Hydrogen Annealing on the Oxidation Resistance of Four EPM Single Crystal Superalloys (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Four single crystal EPM (enabling propulsion materials) developmental airfoil superalloys were hydrogen annealed at 1300 C for up to 100 hours to remove sulfur and improve oxidation resistance. Although the 1100 and 1150 C cyclic oxidation resistance was remarkably improved by annealing for 24 or 100 hours, the behavior was still considerably inferior to that of commercially available single crystal superalloys, especially those that are either Y-doped or hydrogen annealed. Excessive degradation in the developmental alloys appeared to be correlated with low Cr contents and, to a lesser extent, high Co and Re contents.
    Keywords: Metals and Metallic Materials
    Type: NASA/TM-2001-211064 , E-12883 , NAS 1.15:211064
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    High Conductivity Materials for High Heat Flux Applications in Space Propulsion Systems (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: GRCop-84 is a new copper base alloy with an excellent combination of strength and conductivity and has been developed to the point that it is a strong candidate for near term rocket engine applications. This work sought to establish the feasibility of new alloys with capabilities beyond GRCop-84. The use of coatings as environmental and thermal barriers adds further capability into the Copper base structure. Finally, Nickel-Aluminum based systems have also been explored.
    Keywords: Metals and Metallic Materials
    Type: E-14319 , JANNAF Meeting; Dec 04, 2003; Unknown
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Pt and Hf Additions to NiAl Bond Coats and Their Effect on the Lifetime of Thermal Barrier Coatings (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The lifetimes of thermal barrier coatings (TBC's) with various NiAlPt(HfZr) bond coats were determined by cyclic oxidation testing at 1163 C (2125 F). The bond coats were sprayed from powders by low pressure plasma spraying onto Rene N5 superalloy substrates. Yttria stabilized zirconia (8YSZ) top coats were applied by air plasma spraying. Surprisingly, there was not a strong correlation between TBC lifetime and Pt or Hf content although Zr additions decreased lifetimes. TBC failure morphologies and bond coat microstructures were examined and are discussed with respect to the bond coat compositions.
    Keywords: Metals and Metallic Materials
    Type: THERMEC 2003; Jul 07, 2003 - Jul 13, 2003; Madrid; Spain
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Cyclic Oxidation Testing and Modelling: A NASA Lewis Perspective (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Materials Division of the NASA Lewis Research Center has been heavily involved in the cyclic oxidation of high temperature materials for 30 years. Cyclic furnace and burner rig apparati have been developed, refined, and replicated to provide a large scale facility capable of evaluating many materials by a standard technique. Material behavior is characterized by weight change data obtained throughout the test, which has been modelled in a step-wise process of scale growth and spallation. This model and a coupled diffusion model have successfully described cyclic behavior for a number of systems and have provided insights regarding life prediction and variations in the spalling process. Performance ranking and mechanistic studies are discussed primarily for superalloys and coating alloys. Similar cyclic oxidation studies have been performed on steels, intermetallic compounds, thermal barrier coatings, ceramics, and ceramic composites. The most common oxidation test was performed in air at temperatures ranging from 800 deg. to 1600 C, for times up to 10000 h, and for cycle durations of 0.1 to 1000 h. Less controlled, but important, test parameters are the cooling temperature and humidity level. Heating and cooling rates are not likely to affect scale spallation. Broad experience has usually allowed for considerable focus and simplification of these test parameters, while still revealing the principal aspects of material behavior and performance. Extensive testing has been performed to statistically model the compositional effects of experimental alloys and to construct a comprehensive database of complex commercial alloys.
    Keywords: Metals and Metallic Materials
    Type: NASA/TM-2000-209769 , E-12048 , NAS 1.15:12048 , Cyclic Oxidation; Feb 25, 1999 - Feb 26, 1999; Frankfurt; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A High Temperature Cyclic Oxidation Data Base for Selected Materials Tested at NASA Glenn Research Center (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The cyclic oxidation test results for some 1000 high temperature commercial and experimental alloys have been collected in an EXCEL database. This database represents over thirty years of research at NASA Glenn Research Center in Cleveland, Ohio. The data is in the form of a series of runs of specific weight change versus time values for a set of samples tested at a given temperature, cycle time, and exposure time. Included on each run is a set of embedded plots of the critical data. The nature of the data is discussed along with analysis of the cyclic oxidation process. In addition examples are given as to how a set of results can be analyzed. The data is assembled on a read-only compact disk which is available on request from Materials Durability Branch, NASA Glenn Research Center, Cleveland, Ohio.
    Keywords: Metals and Metallic Materials
    Type: NASA/TM-2003-212546 , E-14112 , NAS 1.15:212546
    Format: application/pdf
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