November 03 (Friday)
유체기계(III)
Oral,
제4발표장(201B호),
11:00~12:00
  • Chair :
  •  리광훈(서울시립대)
Fr04C-3
11:00~12:00
냉각 튜브 나선형 그루브 형상이 가스터빈 블레이드 막냉각 성능에 미치는 영향
이연호, 이명우, LICHIHTAO(성균관대학교 대학원), 김윤제(성균관대학교)
The temperature of the air passing through the gas turbine affects the mechanical efficiency of the gas turbine. As the temperature of the air increases, the turbine efficiency also increases. Therefore, in order to improve the efficiency of the gas turbine engine, the temperature of the air passing through the gas turbine should be increased, and thus the cooling technology of the turbine blades is essential. In this study, the film cooling characteristics of gas turbine blades with various groove patterns were numerically investigated with respect to the inside wall of the cooling tube connecting between the working and the cooling fluid flow fields. The working and the cooling fluids were applied with air and carbon dioxide(CO2), respectively, and a blowing ratio of 1.0 was applied. Numerical analysis was performed using ANSYS CFX ver. 17.1. The film cooling effectiveness by the various groove-patterned configurations was derived through the surface temperature of the turbine blade and a high efficiency model was derived.
Keywords : Gas turbine(가스터빈), Film cooling(막냉각), Cooling tube(냉각 튜브), Groove pattern(그루브 패턴), Spiral configuration(나선형 형상)
Paper : Fr04C-3.pdf

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