• Proceedings of the Korean Nuclear Society Conference
• /
• 1996.05b
• /
• pp.160-165
• /
• 1996

중수로형 원전에서 일차측 냉각수를 순환시키는 주연수송펌프가 정상운전중 갑자기 정지하는 사고를 강제순환 상실사고라 한다. 강제순환 상실사고는 주열수송계통을 과도압력상태로 만들며, 일반적으로 펌프에 공급되는 IV등급전원 상실사고와 기계적 손상에 의한 주열수송펌프 고착사고로 분류할 수 있다. 본 논문에서는 강제순환 상실사고에 대하여 중수로계통설계의 열수력 해석코드인 SOPHT를 이용하여 주열수송계통의 과도압력상태를 해석하였다. 카나다 원자력 규제위원회(AECB)의 과압 방지조건인 R-77 요구조건에 적절한 유효트립변수를 결정하기 위한 해석이 수행되었으며, 증기발생기 오염상태와 액체방출밸브 작동여부가 고도압력상태에 미치는 영향을 고찰하여 보수적 조건을 제시하였다. 또한 위와같이 결정된 보수적 조건을 근거로 ASME 코드에 명시된 과압 한계치에 대한 만족여부와 과도압력상태에 따른 주열수송계통의 열수력학적 거동을 고찰하여 보았다. 해석결과, 강제순환상실사고시 주열수송계통은 R-77 요구조건에 적합한 원자로트립변수에 따라 안정화되었으며, 계통의 최대압력은 ASME 코드가 규정한 한계치내에 있음을 알 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.4
• /
• pp.84-90
• /
• 2004

A performance evaluation is made in terms of thrust, impulse bit. and specific impulses for a set of mono-propellant hydrazine thrusters producing 0.95 lbf of nominal thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test configuration and procedures. a typical data obtained from steady-state firing mode is given directly showing the variational behavior of propellant supply pressure, mass flow rate, vacuum condition, and thrust. The performance features are successfully compared to the reference criteria of 1-lbf standard mono-propellant rocket engine. Additionally. a statistical inter-thruster treatment is concisely depicted for the justification of selected thrusters as a grouped member of flight model for spacecraft propulsion system.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.6
• /
• pp.48-55
• /
• 2008

We have simulated the performance of a simple engine model with a gas turbine engine simulation program based on CFD. 2-dimensional Navier-Stokes code for the viscous flow was applied to simulate a compressor and a turbine, and the chemical equilibrium code with the lumped method was applied to simulate the combustor. Unsteady-flow phenomenon between rotor and stator of the compressor and the turbine was analyzed by steady mixing-plane method. In this way, the influence of the turbine blade pitch on the engine was investigated. It was shown that the compressor is operated at more higher pressure conditions as narrower the pitch distance of the turbine.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.5
• /
• pp.79-87
• /
• 2002

Acoustic responses to pressure oscillations in axisymmetric combustion chamber are numerically investigated to examine the qualitative trend of acoustic instability in liquid rocket engine. Chamber operating condition and excitation frequency of oscillating pressure are selected as exciting parameters of acoustic instability. Artificial perturbation is simulated by total-pressure oscillation with sine wave at chamber inlet. Many approximations and simplifications are introduced without losing the essence of acoustic pressure response. First, steady-state solution for each operating condition is obtained and next, transient analysis is conducted. Depending on operating condition and excitation frequency, the distinct response characteristics are brought. Weak-strength flames and high-frequency excitation tend to cause sensitive acoustic pressure response leading to unstable pressure field. These results are analyzed based on the correlation with acoustic pressure responses from the previous works adopting laminar flamelet model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• v.y2005m4
• /
• pp.194-197
• /
• 2005

Pulse-mode performance evaluation is made for a set of monopropellant hydrazine thrusters producing $0.95 lb_{f}$ of nominal steady-state thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test matrix, a typical data obtained from pulse-mode firing is given directly showing the variational behavior of propellant supply pressure, vacuum condition, and thrust, in addition to the thermal response of the thruster. The performance features are successfully compared to the reference criteria of 1-lbf standard monopropellant rocket engine.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.16 no.9
• /
• pp.5763-5768
• /
• 2015

A relief valve is a mechanical element to keep safety by controlling high pressure. Usually, the high pressure is relieved by using the spring force and letting the fluid to flow from another way out of system. When its normal pressure is reached, the relief valve can return to initial state. The relief valve should be designed for smooth operation and should satisfy the structural safety requirement under operating condition. The commercial software ANSYS/WORKBENCH is utilized for flow and structural analysis. Very high pressure may cause structural problem due to severe stress. The study suggests the design satisfying the structural design requirement

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.433-436
• /
• 2005

The combustion behavior of initiators and can-type ignitor, acting on vacuum pressure, was invested. It was found that if the ignited propellants of a can-type igniter were exposed at certain level of low pressure, it would be burnt improperly or even be extinguished. When we design the can-type igniters for some rocket motor, it is most important that the pressure built-up by the gases which were already burnt inside of the igniter case keep as high as possible. For this purpose, it is recommended that the ignitor case have some strength to produce as much gases as possible before breaking out and the free volume be kept as small as possible.

• Nuclear Engineering and Technology
• /
• v.26 no.2
• /
• pp.161-167
• /
• 1994

This paper presents a concept of a pressure tube-type water-cooled reactor without the emergency core cooling system. It adopts an innovative fuel channel design using metallic fuel matrix to improve heat transfer from fuel to moderator at loss of coolant cooling. The heat produced in the fuel is cooled by the coolant system during normal operation, but by the passive moderator system at loss of coolant cooling including the loss-of-coolant accident(LOCA). Simple analysis shows that the fuel channel temperature can be maintained within the permissible range for both normal operation and a complete LOCA.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.2 no.2
• /
• pp.234-241
• /
• 1999

본 논문에서는 얇은 직사각형 단면 형상을 가지는 세 가지 서로 다른 유동로 안에서 움직이는 공기버블의 변형 거동에 대한 실험을 수행하였다. 압력 차이로 유체는 유동되며, 유동장을 따라서 변형하는 버블의 정상상태 모양을 관찰하였다. 벽면효과를 알아보기 위해 세 종류의 얇은 사각단면을 사용하였으며, 두 가지 종류의 작동 유체, 버블의 초기 크기, 작동 유체의 유량 등을 변화시켰을 때 이에 대한 공기 버블의 변형을 체계적으로 관찰하고 이들의 관계를 고찰하였다. 실험데이타를 정량화하여 캐필러리 수에 대한 버블의 무차원 속도비와의 관계를 상세하게 고찰하였다. 글리세린의 경우는 항상 버블 선단부의 곡률이 후단의 곡률보다 더 작게 나타났으며 실리콘 오일의 경우와 반대 경향이 관찰되었다. 두 경우 모두 캐필러리 수에 대한 속도비와 세장비 값은 1 보다 큰 값을 가졌다. 실리콘 오일의 경우는 주어진 Ca 수에 대하여 속도비가 글리세린의 경우보다 더 크게 나왔으며 버블 크기에 따른 속도비 분산도가 더 조밀하게 나타났다. 사각 단면 폭이 감소할수록 벽면 효과는 증대되었으며 같은 폭에 대해서는 버블 변형이 축소관의 경우가 가장 크게 나타났다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.399-404
• /
• 2010

Test results including the variation of propellant-inlet pressure, pulsed thrust, and environment vacuum with the accompanying thermal responses are presented for the pulse-mode operation of a set of monopropellant hydrazine thrusters producing $0.95lb_f$ of nominal steady-state thrust at an inlet pressure of 350 psia. The test data are reduced into the impulse bit, specific impulse, and force centroid that are the factors typically characterizing pulse-mode performance of small rocket engines. With a scrutiny to the performance parameters, their comparison to the reference criteria of 1 lbf standard monopropellant rocket engine are successfully made.