• Journal of the Korean Professional Engineers Association
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• v.33 no.5
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• pp.77-82
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• 2000

In this study, effect of freezing and cryogenic crushing on physico-chemical characteristics of sardine, pollack and sqiud representative for domestic frozen fishery products was investigated and some product using them was tried to be prepared. Dehead and viscerated, washed fishes were subjection to freezing without air circulation and liquid N2 gas at -20$\^{C}$,-40$\^{C}$ and -80$\^{C}$, and then frozen fishes were crushed by hammermill, masscolloider and the product was stored added with anti-freeze such as sorbitol, phosphates, starch and egg Powder, qualify of frozen squid surimi was not changes during 70 days at below -20$\^{C}$ . The results of quality characteristics and sensory evaluation of patties and nugget which made from shattered squid and pollack were similar to commercial products in flavor, color and texture, but sardine meat was inferior to commercial products in flavor and color.

• Proceedings of the Korea Institute of Applied Superconductivity and Cryogenics Conference
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• 1999.02a
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• pp.169-172
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• 1999

The exergy method is used for analysis and evaluation of the cryogenic nitrogen production process which is operated by expansion turbene and liquid nitrogen. The exergy loss and thermodynamic effeciency are calculated for the each process. Also the operating efficiency and the exergy distribution are examined for each unit of proces. The optimal conditions to minimize the exergy loss of nitrogen column are found that nitrogen recovery ratio is maximum and operating pressure is 5.0 kg/cm2g. The exergy method can be used to design a plant and to evaluate its process.

• Progress in Superconductivity and Cryogenics
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• v.15 no.3
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• pp.20-23
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• 2013

In the development of high temperature superconducting (HTS) power machines, HTS bushing is one of core technologies. In particular, the insulation body with sheds and electrical insulation at cryogenic temperature have attracted a great deal of interest from the view point of the size, weight and efficiency of bushing. In this study, the electrical and mechanical characteristics of various insulators for body in liquid nitrogen ($LN_2$) were investigated. And the surface discharge distance, collar length of GFRP sheds were studied. To emit bubbles between sheds, the shape and arrangement of shed were studied. The shed structure for 60 kV class HTS bushing were designed with regular arrangement.

• Progress in Superconductivity and Cryogenics
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• v.7 no.3
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• pp.43-46
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• 2005

A Protomodel Space Infrared Cryogenic System (PSICS) cooled by a stirling cryocooler was designed. The PSICS has an IR sensor inside a cold box which is cooled by a stilting cryocooler with refrigeration capacity of 500mw at 80K in a vacuum vessel. It is important to minimize heat load for reducing background thermal noise. In order to design the cryogenic system of low heat load and to reduce heat load, we did several numerical analyses and tested using boil-off calorimetry with liquid nitrogen to measure the heat leak of the system. In this paper, we present the results obtained by thermal analysis and heat load measurement for designing the PSICS.

• Journal of computational fluids engineering
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• v.9 no.3
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• pp.49-56
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• 2004

A heated and expanded helium is used to pressurize liquid propellants in propellant tanks of propulsion system of liquid propellant launch vehicles. To produce a heated and expanded helium, an hot-gas heat exchanger is used by utilizing heat source from an exhausted gas, which was generated in a gas generator to operate turbine of turbo-pump and dumped out through an exhaust duct of engine. Both experimental and numerical approaches of hot-gas heat exchanger design were conducted in the present study. Experimentally, siliconites - electrical resistance types - were used to simulate the full heat condition instead of an exhausted gas. Cryogenic heat exchangers, which were immersed in a liquid nitrogen pool, were used to feed cryogenic gaseous helium in a hot-gas heat exchanger. Numerical simulation was made using commercially utilized solver - Fluent V.6.0 - to validate experimental results. Helically coiled stainless steel pipe and stainless steel exhausted duct were consisted of tetrahedron unstructured mesh. Helium was a working fluid Inside helical heat coil and regarded as an ideal gas. Realizable k-』 turbulent modeling was adopted to take turbulent mixing effects in consideration. Comparisons between experimental results and numerical solutions are Presented. It is observed that a resulted hot-gas heat exchanger design is reliable based on the comparison of both results.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.68-73
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• 2011

For the launch preparation of KSLV-I, gaseous nitrogen with various level of pressure and cryogenic liquid nitrogen are required. Nitrogen Supply System on launch complex has been developed to perform the production of high pressure gaseous nitrogen, the production of gaseous nitrogen with temperature of 273 ${\pm}$ 2K for protection purge of launch vehicle after loading of propellant and the supply of cryogenic liquid nitrogen for cooling of fuel (kerosene) and oxidizer (liquid oxygen). The operational instability of vaporizer mainly caused by its heat transfer characteristics which sensitively depends on the atmospheric conditions was removed by introducing parallel installation of two vaporizer and their switching operation. The developed Nitrogen Supply System carried out its function successfully in preparation of KSLV-I flight tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.590-593
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• 2010

The processes of supplying propellants into propellant tanks play important roles during launch preparation of satellite launch vehicle. The total weight of launch vehicle greatly depends on the accuracy of filling quantity of propellant during launch preparation. Among propellants used for launch vehicles a cryogenic propellant such as liquid oxygen is widely adapted as an oxidizer for launch vehicles. Such cryogenic propellant usually resides in a propellant tank as two-phase fluid with liquid and gas, which needs an accurate level measurement system to detect the position of propellant surface precisely. In this paper the fabricating process of a level measurement system using capacitance type with three electrodes is analyzed. In addition, the change of electric signal according to the height of liquid is verified by testing the level measurement system under consideration. The results of tests shows as expected the linear trend of voltage according to the change of water height in a tank.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.752-757
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• 2010

For the launch preparation of KSLV-I, gaseous nitrogen with various level of pressure and cryogenic liquid nitrogen are required. Nitrogen Supply System on launch complex has been developed to perform the production of high pressure gaseous nitrogen, the production of gaseous nitrogen with temperature of $273{\pm}2K$ for protection purge of launch vehicle after loading of propellant and the supply of cryogenic liquid nitrogen for cooling of fuel (kerosene) and oxidizer (liquid oxygen). The operational instability of vaporizer mainly caused by its heat transfer characteristics which sensitively depends on the atmospheric conditions was removed by introducing parallel installation of two vaporizer and their switching operation. The developed Nitrogen Supply System carried out its function successfully in preparation of KSLV-I flight tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.3
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• pp.119-126
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• 2019

For rockets using cryogenic liquid hydrogen or liquid oxygen, chilling is required to avoid cavitation and surge problems. Chilling is categorized by the initial chilling/filling stage and the low-temperature maintenance stage. In addition, to improve satellite insertion capability, a multi-ignition capability is required and accordingly chilling to prepare for the next ignition during low-gravity coasting is also required. This paper describes the overall aspects of filling and low temperature maintain marinating for the booster and the upper stage engine including chilling for multi-ignition.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.3
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• pp.59-70
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• 2020

Obtaining external forced convection heat transfer from bubble boiling and validating it with experimental results using cryogenic liquids are suggested to derive total heat transfer coefficient with pool boiling condition in the case of coil type heat exchanger with a bundle of tubes and to overcome the limitation of using the empirical correlation. Experiment is conducted with pool boiling heat transfer of saturate liquid nitrogen with helical coil type heat exchanger using liquid oxygen as hot stream fluid. Experimentally measured heat transfer coefficient is well-agreed with the estimated curve considering nucleate boiling and forced convection induced by bubble rise.