• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.699-703
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• 2017

Numerical simulations of closed-type and open-type single injectors were conducted to investigate the flow characteristics of a swirl-coaxial injector used in a liquid rocket engine. Numerical analysis was conducted using a commercial program ANSYS FLUENT. The injectors has three models with different recess length. Numerical analysis was conducted to investigate the variation of the flow characteristics of the injector when the flow condition were changed. It was also compare and analyzed with experimental results. The results obtained from the numerical simulation show that the difference between the inlet pressure and the discharge coefficient is not significant.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.6
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• pp.108-119
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• 2020

Dynamic pressure sensor used in liquid rocket engine combustor and gas turbine is recess-mounted usually because it should work in high temperature environment. Although recess-mounted method can protect it from combustion gas in high temperature, tube resonance occurs in a tube-cavity system. To reduce it, the infinite tube probe(ITP) was introduced in this study. The ITP model suggested in previous literature was validated with experimental data and frequency response characteristics were analyzed. Guidelines for designing the ITP were suggested as frequency response profiles varied with geometric information and physical properties using this model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.457-460
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• 2012

Design and fabrication of a sub-scale thrust chamber for verification of 7 tonf-class thrust chamber injectors were described in this paper. The 7 tonf-class thrust chamber consists of mixing head with 90 coaxial swirl injectors and regeneratively combustion chamber cooled by kerosene. The coaxial swirl injectors with different pressure drop and recess number were designed for 7 tonf full-scale thrust chamber. By applying the designed injectors to the sub-scale thrust chamber before applying them to the full-scale thrust chamber, the injector performance and functioning were verified. The sub-scale thrust chamber consists of 19 injectors, has chamber pressure of 70 bar, total propellant mass flow rate of 4.3 kg/s, mixture ratio(O/F) of 2.45.

• Korean Chemical Engineering Research
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• v.60 no.2
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• pp.313-319
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• 2022

AlGaN/GaN based HfO₂ MOSHEMT (metal oxide semiconductor high electron transistor) with different gate recess depth was simulate to demonstrate a successful normally-off operation of the transistor. Three types of the HEMT structures including a conventional HEMT, a gate-recessed HEMT with 3 nm thick AlGaN layer, and MIS-HEMT without AlGaN layer in the gate region. The conventional HEMT showed a normally-on characteristics with a drain current of 0.35 A at V_G = 0 V and V_DS = 15 V. The recessed HEMT with 3 nm AlGaN layer exhibited a decreased drain current of 0.15 A under the same bias condition due to the decrease of electron concentration in 2DEG (2-dimensional electron gas) channel. For the last HEMT structure, distinctive normally- off behavior of the transistor was observed, and the turn-on voltage was shifted to 0 V.

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.33-35
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• 2012

This study has been mainly motivated to numerically model the supercritical mixing and combustion processes encountered in the liquid propellant rocket engines. In the present approach, turbulence is represented by the extended k-e model. To account for the real fluid effects, the propellant mixture properties are calculated by using generalized cubic equation of state. In order to realistically represent the turbulence-chemistry interaction in the turbulent nonpremixed flames, the flamelet approach based on the real fluid flamelet library has been adopted. Based on numerical results, the detailed discussions are made for the effects of swirl number on flame structure of supercritical kerosene/LOx double swirl coaxial injector.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.197-201
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• 2006

In the development process of a fuel-rich gas generator using kerosene and LOx for a 30 tonf class liquid rocket engine, a heat damage occurred at the LOx post of swirl coaxial injectors used in the gas generator and the problem has been examined. To prevent the heat damage, injectors are redesigned to have an increased recess while maintaining internal mixing, which minimizes recirculation region to prevent anchoring of the flame in the recirculation region. The combustion test results of the sub-scale gas generator showed that this scheme can prevent heat damage of the LOx post in the swirl coaxial injectors of the fuel-rich gas generator.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.02a
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• pp.219-219
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• 2010

기존의 플로팅 타입의 메모리는 소자의 소형화에 따른 인접 셀 간의 커플링 현상과 전계에 따른 누설전류의 증가 등과 같은 문제가 발생한다. 이에 대한 해결책으로서 전하 저장 층을 폴리실리콘에서 유전체를 사용하는 SONOS 형태의 메모리와 NFGM (Nano-Floating Gate Memory)연구가 되고 있다. 그러나 높은 구동 전압, 느린 쓰기/지우기 속도 그리고 10년의 전하보존에 대한 리텐션 특성을 만족을 시키지 못하는 문제가 있다. 이러한 문제를 해결 하고자 터널베리어를 엔지니어링 하는 TBM (Tunnel Barrier Engineering Memory) 기술에 대한 연구가 활발히 진행 중이다. TBM 기술은 터널 층을 매우 얇은 다층의 유전체를 사용하여 전계에 따른 터널베리어의 민감도를 증가시킴으로써 빠른 쓰기/지우기 동작이 가능하며, 10년의 전하 보존 특성을 만족 시킬 수 있는 차세대 비휘발성 메모리 기술이다. 또한 고유전율 물질을 터널층으로 이용하면 메모리 특성을 향상 시킬 수가 있다. 일반적으로 TBM 기술에는 VARIOT 구조와 CRESTED 구조로 나눠지는데 본 연구에서는 두 구조의 장점을 가지는 Staggered tunnel barrier 구조를 $Si_3N_4$와 HfAlO을 이용하여 디자인 하였다. 이때 HfO2와 Al2O3의 조성비는 3:1의 조성을 갖는다. $Si_3N_4$와 HfAlO을 각각 3 nm로 적층하여 리세스(Recess) 구조의 트랜지스터를 제작하여 차세대 비휘발성 메모리로써의 가능성을 알아보았다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.30 no.4
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• pp.282-285
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• 2019

A 100-nm gate-length metamorphic high electron mobility transistor(mHEMT) with a T-shaped gate was fabricated using a two-step gate recess and characterized for DC and microwave performance. The mHEMT device exhibited DC output characteristics having drain current($I_{dss}$), an extrinsic transconductance($g_m$) of 1,090 mS/mm and a threshold voltage($V_{th}$) of -0.65 V. The $f_T$ and $f_{max}$ obtained for the 100-nm mHEMT device were 190 and 260 GHz, respectively. The developed mHEMT will be applied in fabricating W-band monolithic microwave integrated circuits(MMICs).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.171-176
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• 2006

An experimental study on a fuel-rich gas generator was carried out. Thirty seven double-swirl injectors with recess number of 1.5 were distributed and installed in the injector head, which significantly influences the combustion performance. In the paper, the characteristics of combustion stability are inspected by the parametric varations such as changing length and diameter of a combustion chamber and installing a turbulence ring. The experimental results show that as a resonant frequency took place in a high region, the amplitude of the dynamic pressure generally diminished, however, the combustion instability could not be suppressed perfectly.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.335-340
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• 2005

A study on the variation of combustion characteristics by injector geometries was conducted. Coaxial swirl injectors were used. Existence of swirl chamber and variation of a nozzle length become key parameters. Injectors were identified as open, closed and mixed type by existence of swirl chamber. Variation of nozzle length was made extruding the both nozzle along the axis while other design parameters remain the same. A uni-element combustor with ablative material liner and a water cooled nozzle made by oxygen free copper with outer stainless steel casing were used.