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막냉각 홀의 형상에 따른 터빈 블레이드 끝벽에서의 막냉각 효율 측정
김석민(Seokmin Kim),이동은(Dong-Eun Lee),정희윤(Heeyoon Chung),강영석(Young Seok Kang),이동호(Dong-Ho Rhee) 한국추진공학회 2022 한국추진공학회 학술대회논문집 Vol.2022 No.5
현대의 가스터빈 엔진은 작동온도를 증가시켜 엔진의 효율을 높이기 위해 다양한 연구가 수행되어왔다. 이에 가스터빈 엔진에 적합한 냉각기술의 필요성이 나타났다. 막냉각 기술은 가스터빈에 적용되는 대표적인 냉각기술 중 하나로 본 연구에서는 터빈 블레이드 끝벽에 여러 형태의 막냉각 홀을 가공 후 막냉각 효율을 측정하였다. 막냉각 홀의 형상으로는 기본형상 막냉각 홀과 최적 확장형 홀, 그리고 단차구조를 가공한 홀에 대해 실험을 수행했으며, 막냉각 효율의 측정 방법으로는 압력감응페인트를 이용하였다. 실험 결과 기본형상에 비해 다른 막냉각 홀 형상들이 터빈 블레이드 끝벽에서 더욱 개선된 냉각 효율을 보여주었다. For enhancing the efficiency of the gas turbine engine by increasing the turbine inlet temperature, various researches have been conducted. Therefore, the need for cooling technology suitable for gas turbine engines appeared. One of the representative cooling technologies applied to gas turbine is film cooling. In this study, film cooling effectiveness was measured on the endwall of turbine blade with various types of film cooling holes. Experiments were conducted with baseline fan-shaped film cooling hole, optimal fan-shaped hole and baseline with staircase geometry. Cooling Effectiveness measurement was used by Pressure Sensitive Paint (PSP). As a result, improved film cooling holes show more increased cooling effectiveness compared to the baseline film cooling hole.
계단 형상의 단차가 적용된 팬 형상 막냉각 홀 하류에서의 막냉각 효율에 관한 실험적 연구
김석민(Seokmin Kim),이동은(Dong-Eun Lee),정희윤(Heeyoon Chung),강영석(Young Seok Kang),이동호(Dong-Ho Rhee) 한국유체기계학회 2021 유체기계 연구개발 발표회 논문집 Vol.2021 No.7
In this study, the adiabatic film cooling effectiveness downstream of a row of the fan-shaped film cooling holes with various staircase geometries at hole exit was measured and analyzed using a pressure sensitive paint method. Experiments were conducted with baseline fan-shaped film cooling hole and the three different configurations with staircase geometry, in which ‘two-step’ geometry was applied to the hole exit and its lateral length is changed from 2.3D to 6D. A low-speed open-type wind tunnel was used for the experiments and the density ratio of the main stream to coolant fluid was 1.0 and the blowing ratio ranged between 0.5 and 2.0. The result showed that the staircase geometry promotes lateral spreading of the coolant at the hole exit, which results in better film coverage near the hole. At low blowing ratio, the film cooling effectiveness distributions are quite similar for all the tested cases except near the hole exit because the momentum of the coolant is low and baseline configuration also has good coverage downstream of the hole. However as the blowing ratio becomes higher, the effect of the staircase geometry becomes stronger and higher film cooling effectiveness values are obtained due to increased film coverage with reduced momentum of the coolant on the whole measured area.