Development of a Combustor Liner Composed of Ceramic Matrix Composite (CMC

Introduction In the process of developing more efficient industrial gas turbines and turbine engines for airplanes to travel at supersonic speeds, much effort has been directed at raising the combustor outlet (turbine inlet) temperature, as is shown in the chart of the increase in gas turbine inlet temperature in The Research Institute of AMG is conducting research and development to apply these composite materials as parts for gas generators that operate at ultra-high temperatures. The research period is nine years and one month, from March 1993 to March 2002, as shown in In the AMG program, we are engaged in the R&D of application technology and processing technology for CMC parts with the aim of applying CMC materials to gas generator static parts. In this paper, we describe the results of our evaluation of CMC's applicability as a combustor liner based on an analysis of thermal stress and evaluation of a CMC liner model, and a

In Situ SR-XPS Observation of Ni-Assisted Low-Temperature Formation of Epitaxial Graphene on 3C-SiC/Si

Low-temperature (~1073 K) formation of graphene was performed on Si substrates by using an ultrathin (2 nm) Ni layer deposited on a 3C-SiC thin film heteroepitaxially grown on a Si substrate. Angle-resolved, synchrotron-radiation X-ray photoemission spectroscopy (SR-XPS) results show that the stacking order is, from the surface to the bulk, Ni carbides(Ni(3)C/NiC(x))/graphene/Ni/Ni silicides (Ni(2)Si/NiSi)/3C-SiC/Si. In situ SR-XPS during the graphitization annealing clarified that graphene is formed during the cooling stage. We conclude that Ni silicide and Ni carbide formation play an essential role in the formation of graphene

Sample collection from asteroid (162173) Ryugu by Hayabusa2: Implications for surface evolution

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Collisional history of Ryugu's parent body from bright surface boulders

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