• Nuclear Engineering and Technology
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• 제56권3호
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• pp.1002-1012
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• 2024

To remove insoluble fission products, which could possibly cause reactor instability and significantly reduce heat transfer efficiency from primary system of molten salt reactor, a helium bubbling method is employed into a passive molten salt fast reactor. In this regard, two-phase flow behavior of molten salt and helium bubbles was investigated experimentally because the helium bubbles highly affect the circulation performance of working fluid owing to an additional drag force. As the helium flow rate is controlled, the change of key thermal-hydraulic parameters was analyzed through a two-phase experiment. Simultaneously, to assess the applicability of numerical model for the analysis of two-phase flow behavior, the numerical calculation was performed using the OpenFOAM 9.0 code. The accuracy of the numerical analysis code was evaluated by comparing it with the experimental data. Generally, numerical results showed a good agreement with the experiment. However, at the high helium injection rates, the prediction capability for void fraction of helium bubbles was relatively low. This study suggests that the multiphaseEulerFoam solver in OpenFOAM code is effective for predicting the helium bubbling but there exists a room for further improvement by incorporating the appropriate drag flux model and the population balance equation.

• 오토저널
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• 제12권1호
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• pp.33-39
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• 1990

This study has been conducted by experiments for distribution of concentration of helium gas, which is jetted into stationary atmosphere at the normal temperature and pressure. It is able to obtain the data for concentration of helium and air mixtures by the use of hot wire probe which has fast response. At an up stream, the concentration gradient which is attained is steep. At a down stream, the mixing time of helium and air is gradually shortened with the lapse of time in front of a jet. The arrival frequency of a jet in an unsteady area is mostly constant from 0% to 100% up to 80mm, but the time which is reaching to 100% is gradually to lengthen as a descending downstream. After starting a jet and the point of 90%, the mixing time is especially to lengthen. This reason comes from the turbulent intensity which causes for mixing of helium and air. This time difference which causes according to lengthen a jet should be considered in the design of combustion chamber.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
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• pp.179-182
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• 2005

액체추진기관을 사용하는 발사체의 극저온 추진제 온도 conditioning 방안의 일환으로 헬륨분사에 의한 액체산소 과냉각 시험을 수행하였다. 동일한 질량의 액체산소에 대하여 서로 다른 유량의 헬륨을 분사하고 냉각 특성을 비교하였다. 시험조건 하에서 약 $5\sim6^{\circ}C$의 냉각 효과를 얻을 수 있었으며 외부 단열상태에서 특정 온도까지 냉각되는 시간은 헬륨 분사량에 반비례함을 알 수 있었다.

• 한국추진공학회지
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• 제11권2호
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• pp.9-17
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• 2007

기체공급계 추진제공급시스템의 재순환배관에 대하여 성능시험을 수행하였다. 극저온 추진제로 액체 산소를 사용하고 재순환촉진용 분사가스로는 헬륨을 사용하여 탱크 얼리지가 대기압 상태인 경우와 4 bars로 가압된 경우에 대하여 시험하였다. 자연재순환의 발생여부와 헬륨분사량에 따른 액체산소의 재순환량 변화 및 배관 내부 온도분포를 파악하였고, 주어진 규격의 배관시스템에 대한 적정 헬륨분사량과 터보펌프 전단의 추진제 온도상승 정도를 살펴보았다. 시험데이터를 이용하여 재순환배관의 성능계산을 위한 프로그램을 작성하고 시험과 계산결과를 비교하였다.

• 한국초전도ㆍ저온공학회논문지
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• 제9권3호
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• pp.72-82
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• 2007

This paper relates to reducing the temperature of a cryogenic liquid by contacting it with gas bubbles, which can be characterized by diffusion-driven evaporative cooling, The characteristic of diffusion-driven evaporative cooling is thoroughly examined by theoretical. analytical and experimental methods specifically for the case of helium injection into liquid oxygen. The results reveal that if the gaseous oxygen partial pressure in helium bubbles is lower than the liquid oxygen vapor pressure, cooling occurs autonomously due to diffusion mass transfer. The method of lowering the injected helium temperature turns out to be very effective for cooling purpose.

• 한국초전도ㆍ저온공학회논문지
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• 제14권1호
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• pp.38-43
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• 2012

In the extreme conditions of launch vehicle in a space, such as cryogenic temperature and low-gravity environment, the mass gauging of remaining propellants becomes a difficult problem. Pressure-volume-temperature (PVT) method is one of the attractive mass gauging methods under low-gravity due to its simplicity and reliability. PVT gauging experiment with various mass flow rates of helium injection is carried out with the experimental apparatus creating cryogenic homogeneous condition as the condition of low-gravity. Experimental results are analyzed by a novel PVT gauging analysis method which considers all instantaneous changes of pressure and temperature in the ullage volume with small time intervals. It is observed that the gauging error from the novel PVT gauging analysis is -0.11% with 2 slpm mass flow rate of helium injection.

• 한국초전도ㆍ저온공학회논문지
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• 제16권2호
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• pp.64-69
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• 2014

Measuring an exact amount of remaining cryogenic liquid propellant under microgravity condition is one of the important issues of rocket vehicle. A Pressure-Volume-Temperature (PVT) gauging method is attractive due to its minimal additional hardware and simple gauging process. In this paper, PVT gauging method using liquid nitrogen is investigated under microgravity condition with parabolic flight. A 9.2 litre metal cryogenic liquid storage tank containing approximately 30% of liquid nitrogen is pressurized by ambient temperature helium gas. During microgravity condition, the inside of the liquid tank becomes near-isothermal condition within 1 K difference indicated by 6 silicon diode sensors vertically distributed in the middle of the liquid tank. Helium injection with higher mass flow rate after 10 seconds of the waiting time results in successful measurements of helium partial pressure in the tank. Average liquid volume measurement error is within 11% of the whole liquid tank volume and standard deviation of errors is 11.9. As a result, the applicability of PVT gauging method to liquid propellant stored in space is proven with good measurement accuracy.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.241-244
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• 2006

The analysis of propellant feeding sub-system is performed using a commercial code SINDA/FLUINT, the comprehensive finite-difference, one-dimensional, lumped parameter tool. With the code, cryogenic helium supply system, liquid oxygen supply system, helium injection cooling system are evaluated. The code gave satisfactory estimation scheme for propulsion system characterized by cryogenic temperature and high pressure, two phase flow. This paper focuses on presenting calculation scheme of propulsion sub-system using one-dimensional code like SINDA/FLUINT.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.1080-1083
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• 2017

한국형발사체의 설계안에는 산화제 배관의 geysering 현상과 펌프 입구의 cavitation 현상을 방지하기 위하여 발사대기 중 산화제인 액체산소를 과냉각 하여 공급하는 시나리오가 포함되어 있다. 이 조건을 75톤급 엔진 개발 시험 단계에서 검증하기 위해 엔진 연소시험설비에는 액체산소를 과냉각 할 수 있는 시스템이 적용되었다. 여기에는 진공 이젝터를 이용한 방법과 탱크 내 헬륨 분사를 통한 방법이 적용되었으며, 성능 평가를 위해 각각에 대한 과냉각 시험이 수행되었다. 두 시험에서 모두 약 17분간 시험이 진행되었으며, 탱크 50%수위 지점 기준 이젝터를 이용한 시험에서는 약 3.3K, 헬륨 분사를 이용한 시 험에서는 약 2.2K 의 과냉각 결과를 나타내었다.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2019년도 춘계학술대회
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• pp.406-408
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• 2019

자동차에 사용되는 전동식 워터펌프에 적용되는 모터는 CANNED TYPE의 모터 구조이다. 모터의 구동 부품인 로터는 플라스틱 사출물의 격벽 구조 내에 위치하며, 부동액에 침수되어 있는 상태로 회전을 하게 된다. 플라스틱 사출물 격벽 구조 외부에 Stator가 위치되어 Rotor가 회전이 가능하도록 한다. Rotor의 구성은 Magnet와 Core, Shaft로 구성되며, Magnet와 Core의 경우 부품 특성상 수분 침투에 부식되는 재질이기 때문에 부품의 기밀 유지는 매우 중요하다. 차량에 장착된 상태에서는 120도의 환경조건에서 구동이 가능하여야 하며, 내부압력이 1 Bar 이상의 압력에도 누수가 없어야 한다. 본 논문에서는 이 조건을 만족하여 개발된 전동식 워터펌프의 불량을 검사하기 위하여 헬륨을 이용한 Leak 검사 자동화 시스템을 설계 및 구현하였다.