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Furudate, Michiko Ahn,Cho, Seungyon,Hagebaum-Reignier, Denis Elsevier 2018 Fusion engineering and design Vol.136 No.1
<P><B>Abstract</B></P> <P>Understanding the details of chemical kinetics related to the tritium recovery process is necessary to design highly efficient Tritium Extraction System (TES) in the fusion reactors. In the TES, tritium is expected to be released in the form of HTO from the breeder pebbles, and recovered in the form of HT in the helium purge gas containg small amount of hydrogen. The exchange reaction HTO + H<SUB>2</SUB> → H<SUB>2</SUB>O + HT is considered to be one of the important chemical reaction to obtain the tritium in the form of HT in the purge gas flow. In this study, the chemical kinetics of HTO + H<SUB>2</SUB> → H<SUB>2</SUB>O + HT is investigated based on quantum chemistry. Firstly, the potential energy surface will be explored to obtain information of reaction paths and its transition states by using a quantum chemistry calculation software. Then, the reaction rate constant of the exchange reaction is estimated from transition state theory.</P>
Computation of Hypersonic Flowfield over Reentry Capsule
Michiko Furudate,Reiji Takeuchi,Kanako Yasue,Keisuke Sawada 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A three-dimensional calculation of hypersonic flowfield over Apollo command module geometry is carried out, accounting for thermochemical nonequilibrium effects. From the calculated pressure distribution on the body surface, aerodynamic coefficients are deduced and compared with that of the AS-202 flight data. Reasonable agreement between the calculated results and the flight date for aerodynamic coefficients are obtained. Thermochemical nonequilibrium effects are shown to alter the aerodynamic coefficients considerably.
화성대기 돌입체 주위 열화학 비평형 유동장의 3차원계산
Michiko Ahn Furudate 한국기계기술학회 2015 한국기계기술학회지 Vol.17 No.2
A three-dimensional computational fluid dynamics code is developed for predicting nonequilibrium flowfields over Mars entry probes. The numerical scheme is based on the cell-vertex finite volume method for a prismatic unstructured mesh system. Internal energy excitations and chemical reactions with finite rates are considered by introducing the two-temperature model of Park. Eight chemical species, C, N, O, CO, N2, NO, O2, and CO2, and nine chemical reactions are considered in the calculations. The developed code is verified in terms of prediction of heat flux to the body surface near the stagnation point of a Mars entry probe flying with the velocity of 6 km/s. The calculated heat flux reasonably agree with the calculated result in the past studies.
CALCULATION OF SHOCK STAND-OFF DISTANCE FOR A SPHERE IN NONEQUILIBRIUM HYPERSONIC FLOW
M. Ahn Furudate 한국전산유체공학회 2012 한국전산유체공학회지 Vol.17 No.4
Hypersonic flowfields over a sphere is calculated by using a nonequilibrium flow solver. The flow solver features a two-temperature model and finite rate chemical reaction models to describe nonequilibrium thermochemical processes. For the purpose of validation, the calculated shock stand-off distance is compared with the experimental data which is measured in a ballistic range facility. The present nonequilibrium calculation well reproduced the experimental shock stand-off distance in the cases where the experimental flowfields are expected to be nearly equilibrium, as well as in the cases to be nonequilibrium flowfields in the velocity range 4000 to 5500 m/s.