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임주현(Ju Hyun Im),김명호(Myung Ho Kim),김용련(Yeong Ryeon Kim) 한국추진공학회 2015 한국추진공학회지 Vol.19 No.1
The cooling of hot exhaust gas is an important issue for the construction of combustor test facility. Water spray is an effective method for exhaust gas cooling due to its large latent heat in process of evaporation. In this study, 1-D analysis has been performed based on continuity, energy conservation, and saturated vapor property to understand water spray cooling of combustion gas. In the exhaust duct of combustor test facility, the injected water decreases combustion gas temperature, and evaporates in the combustion gas. However, some of the injected water is collected in the sump due to condensation. The evaporation of water helps combustion gas cooling, but causes pressure increase inside the exhaust duct due to increase of vapor pressure. These phenomena has been analyzed by 1-D modeling in this study. From 1-D analysis, the adequate mass flow rate of water spray to cool combustion gas and to avoid excessive pressure rise inside the exhaust duct has been decided.
엔진베이 환기용 탠덤 이젝터의 1차원 해석모델링 기법 개발
임주현(Ju Hyun Im),김명호(Myung Ho Kim),김용련(Yeong Ryeon Kim),전상인(Sang In Jun) 한국추진공학회 2014 한국추진공학회지 Vol.18 No.4
Tandem-ejector has been devised for engine-bay cooling. In this study, 1-D model has been developed to analyze Tandem-ejector. In the model, the primary, the secondary and the tertiary flow conditions have been analyzed with isentropic process. The mixing process has been analyzed with conservation laws based on the control volume analysis. The total pressure loss of the primary flow has been analyzed under the matching condition between the static pressure of Tandem-ejector discharge flow and atmospheric pressure. Consequently, 1-D model can predict Tandem-ejector performance accurately and provide the performance map.
임주현(Ju Hyun Im),김선제(Sun Je Kim),김명호(Myung Ho Kim),김유일(Youil Kim),김용련(Yeong Ryeon Kim) 한국추진공학회 2018 한국추진공학회 학술대회논문집 Vol.2018 No.5
가스터빈엔진 고도시험설비 운용특성탐색 및 설비튜닝 연구와 유량/추력 측정방안 검증을 위한 엔진 시뮬레이션덕트 설계연구를 수행하였다. 설비 운용특성 검증은 배압/추력 제어가 필요하므로 Spikecone type의 가변노즐을 적용하였으며, 유량검증용 ISO 쵸킹노즐의 추가장착이 가능토록 설계하였다. 시뮬레이션덕트 주유로 면적은 1D Sizing으로 결정하고, 노즐면적변화에 따른 시뮬레이션덕트 내부 유동특성은 1D/CFD 해석으로 조사하였으며, 해석결과로부터 설비운용특성 탐색 및 유량/추력 검증시험을 위한 공기공급부 시험조건을 도출하였다. Spike 노즐 구동부는 시험 전운용 구간에서 공력하중조건을 견디도록 모터, 리니어 볼스크류 등의 부품모델을 선정하였으며, 시험 시 10mm/s의 이송속도가 가능하도록 설계하였다. Design study of gas turbine engine simulation duct for investigation of Altitude Engine Test Facility operating characteristics and facility control gain tuning has been conducted. The simulation duct design includes variable spike nozzle and ISO standard choking nozzle to verify the measurement devices such as mass flow rate and thrust. Simulation duct air flow area was decided to satisfy Ma 0.4 at Aerodynamic Interface Plane at engine design condition. The test conditions for verifying the AETF controls and measurement devices were deduced from 1D and CFD analysis results. The spike-cone driving part was designed to withstand the applied aero-load, and satisfy the axial traversing speed of 10 mm/s at whole operation envelops.
Water spray를 이용한 연소 가스 냉각 1차원 해석
임주현(Ju Hyun Im),김명호(Myung Ho Kim),김용련(Yeong Ryeon Kim) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.5
연소기 시험 장치의 구축에서 고려되는 요구 조건 중 하나는 고온의 연소 가스를 적절한 냉각을 통해 대기로 배출하는 것이다. 연소 가스 냉각을 위한 물 분무(Water Spray) 냉각 방식은 증발 과정에서의 물의 잠열을 이용하는 것으로, 연소 가스의 효과적인 냉각이 가능하다. 본 연구에서는 연소기 시험설비 구축의 준비 과정의 일환으로, Water Spray를 이용한 연소 가스의 냉각을 이해하기 위하여 연속 방정식, 에너지 보존식과 포화 증기의 압력-온도 관계식을 이용한 1차원 해석을 수행하였다. 연소기 시험 장치에서 배출되는 고온, 고압의 연소 가스는 물 분사를 통해 연소 가스의 온도는 낮아지며, 분무된 물의 일부는 기화하여 연소가스와 함께 배출되고, 일부는 다시 응축 되어 집수조로 모인다. 냉각수는 연소 가스의 온도를 낮춰주는 동시에, 증발된 증기는 연소기 내부의 압력을 증가시키므로 1차원 해석에서 증기의 압력-온도 관계식을 고려하여 해석을 수행하였다. 1차원 해석으로부터 연소가스의 적절한 냉각과 배기 덕트 내부의 압력의 지나친 상승을 피하기 위한 최적의 물 분사량을 발견하였으며, Water Spray를 이용한 연소가스 냉각에 대한 물리적인 이해를 얻을 수 있었다. The cooling of hot exhaust gas from combustor is an important issue for the construction of combustor test facility. Water spray is an effective method for exhaust gas cooling due to its large latent heat in process of evaporation. In this study, 1-D analysis has been performed based on continuity, energy conservation, and saturated vapor property to understand water spray cooling of combustion gas. In the exhaust duct of combustor test facility, the injected water decreases combustion gas temperature, and evaporates in the combustion gas. However, some of the injected water is collected in the sump due to condensation. The evaporation of water helps combustion gas cooling, but causes pressure increase inside the exhaust duct due to increase of vapor pressure. These phenomena has been analyzed by 1-D modeling in the study. From the results of 1-D analysis, the adequate mass flow rate of water spray to cool combustion gas adequately and to avoid excessive pressure rise inside the exhaust duct.
AIP면 유동측정 정확도 향상을 위한 가스터빈엔진 입구덕트 설계 연구
임주현(Ju Hyun Im),김성돈(Sung Don Kim),김용련(Yong Ryeon Kim) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.3
In this study, gas turbine engine inlet duct was designed to satisfy uniform flow at aerodynamic interface plane (AIP). Haack-series was selected as nose cone profile and duct outer radius(r<SUB>o</SUB>) was designed to satisfy to match with area change rate between the nose cone and outer duct wall by the 1-D sizing. The design object of the inlet duct wall profile which has the gradual area change rate was uniform Mach number in the core flow region and minimum boundary later thickness at the both inner nose wall and outer duct wall. The flow characteristics inside the inlet duct was evaluated using CFD. The static pressure distribution at the AIP showed uniform pattern within 0.16%. Based on Mach number profile, the boundary layer thickness was 2% of channel height. Kiel temperature rake location was decided less than 100 mm in front of nose cone where the Mach number is less than 0.1 in order to maximize the temperature probe recovery rate.
임주현(Ju Hyun Im),김선제(Sun Je Kim),김명호(Myung Ho Kim),김유일(You Il Kim),김용련(Yeong Ryeon Kim) 한국추진공학회 2019 한국추진공학회지 Vol.23 No.1
A design study of gas turbine engine simulation duct was conducted to investigate the operating characteristics and control gain tunning of the Altitude Engine Test Facility(AETF). The simulation duct design involved testing variable spike nozzle and ISO standard choking nozzle to verify the measurements such as mass flow rate and thrust. The simulation duct air flow area was designed to satisfy Ma 0.4 at the aerodynamic interface plane(AIP) at engine design condition. The test conditions for verifying the AETF controls and measurement devices were deduced from 1D analysis and CFD calculation results. The spike-cone driving part was designed to withstand the applied aero-load, and satisfy the axial traversing speed of 10 ㎜/s at whole operation envelops.
Influence of Blade Surface Roughness on Flow Characteristics in a Linear Compressor Cascade
Ju Hyun Im(임주현),June Hyuck Sohn(손준혁),Jin Wook Kim(김진욱),Seung Jin Song(송성진) 대한기계학회 2007 대한기계학회 춘추학술대회 Vol.2007 No.10
Experiments were conducted in a linear compressor cascade to investigate influence of blade surface roughness on flow characteristics. Rotor blade surface of a land-based gas turbine compressor has been measured to investigate blade surface degradation. Centerline averaged roughness increased from 0.20μm to 5.31μm due to surface degradation. Blade roughness of the real compressor was simulated in the experiment setup by matching the roughness Reynolds number. To apply roughness on the cascade blade, emery grain is attached to the blade surfaces with doubled-sided adhesive tape. Static pressure on blade surface, total pressure loss at downstream and deviation angle are measured in cascade experiment. Turbulent separation is detected at the blade suction side and separation position moves upstream with increasing roughness. Area averaged loss coefficient increases by 232% for the k+ of 96. Area averaged deviation angle increased by 23% for the k+ of 96.