Open Access
Reliability and effective thermal conductivity of three metallic-ceramic composite insulating coatings on cooled hydrogen-oxygen rockets
TLDR
In this paper, the structural integrity and effective thermal conductivity of three metallic-ceramic composite coatings were investigated on the combustion side of water-cooled, 12.7-centimeter throat diameter, hydrogen-oxygen rocket thrust chambers operating at 2.07 to 4.14 meganewtons per square meter chamber pressure.Abstract:
An experimental investigation of the structural integrity and effective thermal conductivity of three metallic-ceramic composite coatings was conducted. These coatings were plasma sprayed onto the combustion side of water-cooled, 12.7-centimeter throat diameter, hydrogen-oxygen rocket thrust chambers operating at 2.07 to 4.14 meganewtons per square meter chamber pressure. The metallic-ceramic composites functioned for six to 17 cycles and for as long as 213 seconds of rocket operations and could have probably provided their insulating properties for many additional cycles. The effective thermal conductivity of all the coatings was in the range of 0.7472 to 4.483 w/(m)(K), which makes the coatings a very effective thermal barrier. Photomicrographic studies of cross-sectioned coolant tubes seem to indicate that the effective thermal conductivity of the coatings is controlled by contact resistance between the particles, as a result of the spraying process, and not the thermal conductivity of the bulk materials.read more
Citations
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Two-layer thermal barrier coating for turbine airfoils - furnace and burner rig test results
TL;DR: In this article, a two-layer plasma-sprayed thermal barrier coating system was developed which has the potential for protecting high temperature air-cooled gas turbine components, and the most promising system consisted of a Ni-16Cr-6Al-0.6Y (in wt%) thermal barrier covering the airfoil.
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Effects of yttrium, aluminum, and chromium concentrations in bond coatings on the performance of zirconia-yttria thermal barriers
TL;DR: A cyclic furnace study was conducted between 990 - 280 C and 1095- 280 C to evaluate the effects of yttrium, chromium, and aluminum concentrations in nickel base alloy bond coatings and also the effect of the bond coating thickness on the performance of ytria-stabilized zirconia thermal barrier coatings as discussed by the authors.
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Ceramic thermal-barrier coatings for cooled turbines
TL;DR: In this article, a plasma-sprayed layer of zirconia stabilized with either yttria, magnesia or calcia over a thin alloy bond coat has been developed, their potential analyzed and their durability and benefits evaluated in a turbojet engine.
Potential use of ceramic coating as a thermal insulation on cooled turbine hardware
C. H. Liebert,F. S. Stepka +1 more
TL;DR: In this article, an analysis was made to determine the potential benefits of using a ceramic thermal insulation coating of calcia-stabilized zirconia on cooled engine parts, applied to turbine vanes of a high temperature and high pressure core engine and a moderate temperature and low pressure research engine.
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The significance of thermal contact resistance in two-layer thermal-barrier-coated turbine vanes
TL;DR: In this paper, the importance of thermal contact resistance between layers in heat transfer through two layer, plasma sprayed, thermal barrier coatings applied to turbine vanes was investigated with a system of NiCrAlY bond and yttria stabilized zirconia ceramic.
References
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Journal ArticleDOI
Heat Transfer to Supercritical Water in Smooth-Bore Tubes
Experimental investigation of hot-gas side heat-transfer rates for a hydrogen-oxygen rocket
TL;DR: In this article, an experimental investigation was conducted at the Lewis Research center to determine the hot-gas side heat transfer rates in a rocket nozzle, and the experimental results showed that the side heat-transfer rates in the rocket nozzle can be improved.
Hydrogen plasma tests of some insulating coating systems for the nuclear rocket thrust chamber
TL;DR: In this article, several plasma-sprayed and slurry-coated insulating coating systems were evaluated for structural stability in a low-pressure hot hydrogen environment at a maximum heat flux of 19.6 million watts/sq meter.
Axial and circumferential variations of hot- gas-side heat-transfer rates in a hydrogen- oxygen rocket
R. J. Quentmeyer,R. L. Schacht +1 more
TL;DR: Axial and circumferential variations of hot gas side heat transfer coefficients in hydrogen oxygen engines for use in nozzle and injector design were proposed in this paper for hydrogen fuel cells.
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