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The isothermal-fluidic field of a secondary moderator jet in a ¼ scale CANDU-6 reactor model
Kim, Hyoung Tae,Rhee, Bo Wook,Im, Sunghyuk,Sung, Hyung Jin,Atkins, Michael D.,Rossouw, Dillon J.,Kim, Tongbeum North-Holland Pub. Co 2017 Nuclear engineering and design Vol.323 No.-
<P><B>Abstract</B></P> <P>The steady, isothermal-fluidic field of forced moderator streams in a ¼ scaled moderator circulation tank (MCT) of a CANDU-6 reactor is analysed. Particular focus is placed on characterizing a secondary jet formed by the collision of symmetric, counter flowing wall jets discharged upwards by nozzles installed at each side of the MCT’s horizontal axis. Two separate sets of experiments have been conducted employing water and air as the working fluids with different nozzle configurations (i.e., discrete dove-tail nozzles for water and two-dimensional slot jet nozzles for air). Then, cross validation of the fluidic data sets from these two different test facilities have been made where the fluidic similarity of the secondary jet generated by the inlet nozzles (particularly its rate of dissipation as it interacts with the calandria tubes (CTs)) has been established. Based on the established fluidic similarity, a series of numerical simulations have been performed according to the boundary conditions obtained extensively from the two-dimensional MCT experiments. Subsequently, the numerical results have been validated against the experimental data to assess the capability of a commercial code (ANSYS CFX V15.0) to resolve the moderator interaction with the CTs. It has been demonstrated that a monotonic decay of the secondary jet whose peak (having roughly 50% of the nozzle’s exit mean vertical velocity component) exists at the throat of the first row of the calandria tubes in the MCT takes place. After which, the momentum of the secondary jet is substantially reduced along its centreline. The rate of dissipation of the secondary jet is under-predicted by the default <I>k-ω</I> SST turbulence model, leading to a dramatic over-prediction of the penetration distance of the secondary jet into the core region. However, the accuracy of the numerical results can be substantially improved with turbulence model parameter tuning to achieve a closer fit with the reference experimental data.</P> <P><B>Highlights</B></P> <P> <UL> <LI> There exist secondary jet Reynolds number independence and fluidic similarity. </LI> <LI> Secondary jet peaks roughly at 50% of the nozzle’s exit means vertical velocity. </LI> <LI> The momentum of the secondary jet is substantially reduced along its centreline. </LI> <LI> The rate of dissipation of the secondary jet is under-predicted by the default <I>k-ω</I> SST turbulence model. </LI> <LI> The accuracy of the numerical results can be improved with turbulence model parameter tuning. </LI> </UL> </P>
한국형발사체 75톤 연소기 기술검증시제(TDM#1) 연소 시험 결과
소윤석(Younseok So),이광진(Kwangjin Lee),김성혁(Sunghyuk Kim),김승한(Seunghan Kim),김채형(Chaehyoung Kim),서대반(Daeban Seo),우성필(Seongphil Woo),임지혁(Jihyuk Im),전준수(Junsu Jeon),조남경(Namkyung Cho),황창환(Changhwan Hwang),한영민( 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.5
본 논문에서는 한국항공우주연구원에서 수행한 연소기 연소 시험 중 고주파 연소 불안정이 발생한 시험결과를 반영하여 보수된 TDM#1의 연소 시험 결과에 대해서 기술하고자 한다. 시험 결과, 시험설비에서 시험대상체로의 추진제 공급은 안정적으로 공급 가능하며, 저압 연소시험은 연소 불안정성을 확인하기에는 낮은 연소 압력임을 재확인 할 수 있었다. This paper is described for the test results of repaired combustion chamber TDM#1 after hot firing test which was occurred to the high frequency combustion instability. This test was performed in KARI"s Naro Space Center. The results are as follows. CCTF is possible for the stable supply with estimated propellant flow rates into combustion chamber. The low pressure hot firing test is improper to know the combustion instability of combustion chamber.