• Journal of Aerospace System Engineering
• /
• v.14 no.1
• /
• pp.1-7
• /
• 2020

This paper discusses a series of procedures and results for designing the gear part of a fuel transfer pump for an aircraft, developed as an independent technology for the first time in Korea. A gear pump type is selected because the design requirements of the fuel transfer pump are met by a gear pump with a characteristics of less leakage inside than a vane pump with superior overall performance. The gear housing is designed with suitable clearance, considering the outer diameter of the gear, which is the main factor on which the flow can be determined. Additionally, the calculation of the required hydraulic and axial force for the motor to drive the fuel transfer pump was performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.05a
• /
• pp.125-129
• /
• 2006

In the present study, preliminary design and analysis of flow distribution for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.464-468
• /
• 2005

In the present study, preliminary design and performance analysis for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.10 no.1
• /
• pp.38-43
• /
• 2006

In the present study, preliminary design and analysis for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.12
• /
• pp.1143-1150
• /
• 2007

The fuel transfer characteristics of the jet pump between fuel tanks, which is applied in the smart UAV fuel supply system, were experimentally investigated. The operating conditions of the jet pump were setup to meet the engine requirement according to mission profile, and the jet pump performance was evaluated at those conditions. The pressure ratio and the efficiency of the jet pump were measured with the variation of flow ratio. In addition, the area ratio was taken into the consideration to examine the effect on the jet pump performance. From the evaluation results, the jet pump met the fundamental requirement to transfer fuel with the flow ratio of 2.23. In the case of the jet pump that is focused on the fuel transfer quantity rather than its efficiency, the flow ratio would be adjusted through the variation of area ratio of the jet pump within the permitted limit of pressure ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.05a
• /
• pp.351-354
• /
• 2006

In the present work, performance analysis of fuel feed and transfer system for Smart UAV was conducted. For the fuel feed system, it was verified that minimum and maximum pressure requirements at the fuel inlet of engine were satisfied. For the fuel transfer system, design variables of jet pump were derived and performance was verified for the maximum acceleration flight condition by using ESDU design guide and flowmaster code.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.11
• /
• pp.1013-1021
• /
• 2007

Design and performance analysis of the jet pump to transfer fuel between tanks in the smart UAV fuel supply system were carried out through one dimensional flow analysis and the flow analysis using a commercial CFD code. From the analysis results, it was proved that the jet pump was designed with the flow ratio of 2.23 that is the fundamental requirement of the jet pump design. The comparison results showed that the primary nozzle pressure is higher in the CFD analysis than in one dimensional flow analysis, mainly due to the underestimated loss coefficient of the primary nozzles. Consequently, the loss coefficients of the jet pump components should be determined more precisely for the design of the jet pumps with high performance.

• Journal of Energy Engineering
• /
• v.20 no.3
• /
• pp.224-230
• /
• 2011

For developing high performance fuel cell, peripheral devices and key components have to be studied in priority. In this study, centrifugal pump was studied for heat recovery. For PEM fuel cell system, a four-impeller centrifugal pump was designed, tested and compared with result of commercial product (IWAKI). In addition, effects of number of impeller were analyzed by CFD. The experiment and analysis were progressed in the same conditions. The results showed the quantitative difference under 30% between the numerical and the experimental pressure difference and mass flow rate.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.21 no.11
• /
• pp.634-640
• /
• 2020

Failure analysis and heat-resistant were performed for an electric fuel pump that is installed in the fuel tank to transfer fuel to the engine of combat vehicles. The fuel pump with a DC motor was disassembled and inspected to determine the cause of failure. The failure phenomenon was classified into three categories based on observations of the inside of the housing: burnt winding, quick brush abrasion, and fuel leak into the pump. Based on the inspection results, it was estimated that overheating was the main cause of failure. The thermal test was conducted under the no-load condition in 24 hours, and the thermal sensor was installed on the stator surface and the brush holder to check the possibility of damage to the winding due to overheating. When the ambient temperature of the fuel pump was set to 68 ℃, the stator temperature increased to 135.9 ℃, and the winding of the motor was almost damaged. The test results confirmed the lack of heat resistance of fuel pump windings, and suggested that the type F of insulation class (below 155 ℃) of the windings and varnish should be replaced with type C or higher that can be used above 180 ℃.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.5-13
• /
• 2017

To lunch the Korea Space Launch Vehicle-II(KSLV-II), the second launch complex will be constructed on the Naro Space Center and Kerosene Filling System (KFS) will be also installed newly. KFS of KSLV-II launch complex system is being designed based on Naro Launch Complex. But this must supply fuel to fuel tanks of the vehicle with only a supply pump because KSLV-II is a 3-stage launch vehicle unlike Naro Launch Vehicle or Test Launch Vehicle (TLV). A sudden rise of pump output pressure is recognized during fuel filling scenario selection process. This occurs because return flow can not actively deal with a lot of flow change using flow control method of orifice type. To solve this problem, it is verified that fuel can be stably supplied by installation of accumulator and an appropriate adjustment of filling mode change sequence through flow analysis of various cases.