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연소실 냉각을 위한 충돌제트/유출냉각기법에서 유출판에서의 열전달특성
이동호,조형희,Rhee, Dong-Ho,Cho, Hyung-Hee 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.3
The present study is conducted to investigate the local heat/mass transfer characteristics for flow through perforated plates. A naphthalene sublimation method is employed to determine the local heat/mass transfer coefficients on the effusion plate. Two parallel perforated plates are arranged for the two different ways: staggered and shifted in one direction. The experiments are conducted for hole pitch-to-diameter ratios of 6.0, for gap distance between the perforated plates of 0.33 to 10 hole diameters, and for Reynolds numbers of 5,000 to 12,000. The result shows that the high transfer region is formed at stagnation region and at the mid-line of the adjacent impinging jets due to secondary vortices and flow acceleration to the effusion hole. For flows through the perforated plates, the mass transfer rates on the surface of the effusion plate are about six to ten times higher than for effusion cooling alone (single perforated plate). More uniform and higher heat/mass transfer characteristic is obtained in overall region with small gap between two perforated plates.
정사각 막냉각홀 내부에서의 열/물질전달 및 유동 특성 (II) - 비대칭 입구조건 효과 -
이동호,강승구,조형희,Rhee, Dong-Ho,Kang, Seung-Goo,Cho, Hyung-Hee 대한기계학회 2002 大韓機械學會論文集B Vol.26 No.7
An experimental study has been conducted to investigate the heat/mass transfer characteristics within a square film cooling hole with asymmetric inlet now condition. The asymmetric inlet now condition is achieved by making distances between side walls of the secondary now duct and the film cooling hole different; one side wall is $2D_h$ apart from the center of the film cooling hole, while the other side wall is $1.5D_h$ apart from the center of the film cooling hole. The heat/mass transfer experiments for this study have been performed using a naphthalene sublimation method and the now field has been analyzed by numerical calculation using a commercial code. Swirl now is generated at the inlet region and the heat/mass transfer pattem with the asymmetric inlet now condition is changed significantly from that with the symmetric condition. In the exit region, the effect of mainstream on the inside hole now is reduced with the asymmetric condition. The average heat/mass transfer coefficient is higher than that with the symmetric condition due to the swirl now generated by the asymmetric inlet condition.
변형된 단일 막냉각홀 주위에서의 열/물질전달 및 막냉각효율 특성
이동호,김병기,조형희,Rhee, Dong Ho,Kim, Byunggi,Cho, Hyung-Hee 대한기계학회 1999 大韓機械學會論文集B Vol.23 No.5
Two problems with jet injection through the cylindrical film cooling hole are 1) penetration of jet into mainstream rather than covering the surface at high blowing rates and 2) nonuniformity of the film cooling effectiveness in the lateral direction. Compound angle injection is employed to reduce those two problems. Compound angle injection increases the film cooling effectiveness and spreads more widely. However, there is still lift off at high blowing rates. Shaped film cooling hole is a possible means to reduce those two problems. Film cooling with the shaped hole is investigated in this study experimentally. Film cooling hole used in present study is a shaped hole with conically enlarged exit and Inlet-to-exit area ratio is 2.55. Naphthalene sublimation method has been employed to study the local heat/mass transfer coefficient and film cooling effectiveness for compound injection angles and various blowing rates around the shaped film cooling hole. Enlarged hole exit area reduces the momentum of the jet at the hole exit and prevents the penetration of injected jet into the mainstream effectively. Hence, higher and more uniform film cooling effectiveness values are obtained even at relatively high blowing rates and the film cooling jet spreads more widely with the shaped film cooling hole. And the injected jet protects the surface effectively at low blowing rates and spreads more widely with the compound angle injections than the axial injection.
항공용 가스터빈 고압터빈 냉각설계기술 및 시험평가기술 연구
이동호(Dong-Ho Rhee),강영석(Young Seok Kang),허재성(Jaesung Huh),김형모(Hyung Mo Kim),박부민(Pu Min Park),유두환(Du Hwan Ryu),김춘택(Chun Taek Kim),차봉준(Bong Jun Cha) 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.5
한국항공우주연구원에서는 항공용 가스터빈엔진의 고압터빈 냉각설계기술 및 시험평가기술 연구의 일환으로 지난 2011년 10월부터 산업통상자원부의 지원을 받아 4개 대학과 함께 “중소형 항공기용 터보팬 엔진의 고압터빈 냉각설계기술 개발 및 시험평가기술 구축“ 사업을 수행 중에 있으며, 본 논문에서는 한국항공우주연구원에서 현재 수행 중인 항공용 가스터빈엔진의 고압터빈 냉각설계기술 및 시험평가기술 연구과제의 주요 연구결과에 대하여 소개하였다. Korea Aerospace Research Institute (KARI) has conducted the project on cooling design and performance test for high pressure turbine of aviation gas turbine engine with four participating universities since 2011. This project is funded by Ministry of Trade, Industry and Energy (MOTIE). This paper introduced the research activities on cooling design and performance test for high pressure turbine of aviation gas turbine engines conducted by KARI.