TY - JOUR
T1 - Heat transfer augmentation using a rib-dimple compound cooling technique
AU - Choi, Eun Yeong
AU - Choi, Yong Duck
AU - Lee, Won Suk
AU - Chung, Jin Teak
AU - Kwak, Jae Su
N1 - Funding Information:
This work was supported by a National Research Foundation of Korea grant funded by the Korean Government ( 2010-0016747 ).
PY - 2013
Y1 - 2013
N2 - Detailed distributions of the heat transfer coefficients in the channel with both angled ribs and dimples were measured using the transient liquid crystal technique. For comparison, heat transfer coefficients for dimpled and angle ribbed channels were also presented. The channel aspect ratio was designed to be 2 and 4 in order to simulate the internal coolant passage of a gas turbine blade. The rib pitch, rib angle, dimple diameter, and dimple center-to-center distance were 6 mm, 60°, 6 mm, and 7.2 mm, respectively. The Reynolds number based on the channel hydraulic diameter ranged between 30,000 and 50,000. Results show that the distribution of heat transfer coefficient was asymmetric due to the secondary flow induced by the angled ribs. Also, dimples fabricated between the ribs increased the heat coefficient with an acceptable increase in pressure drop. Thus, the compound cooling technique with angled rib sand dimples should be considered as a candidate for improving the heat transfer performance of a gas turbine blade internal cooling technique.
AB - Detailed distributions of the heat transfer coefficients in the channel with both angled ribs and dimples were measured using the transient liquid crystal technique. For comparison, heat transfer coefficients for dimpled and angle ribbed channels were also presented. The channel aspect ratio was designed to be 2 and 4 in order to simulate the internal coolant passage of a gas turbine blade. The rib pitch, rib angle, dimple diameter, and dimple center-to-center distance were 6 mm, 60°, 6 mm, and 7.2 mm, respectively. The Reynolds number based on the channel hydraulic diameter ranged between 30,000 and 50,000. Results show that the distribution of heat transfer coefficient was asymmetric due to the secondary flow induced by the angled ribs. Also, dimples fabricated between the ribs increased the heat coefficient with an acceptable increase in pressure drop. Thus, the compound cooling technique with angled rib sand dimples should be considered as a candidate for improving the heat transfer performance of a gas turbine blade internal cooling technique.
KW - Compound cooling
KW - Dimple cooling
KW - Gas turbine blade cooling
KW - Internal cooling
KW - Rib turbulated cooling
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U2 - 10.1016/j.applthermaleng.2012.09.041
DO - 10.1016/j.applthermaleng.2012.09.041
M3 - Article
AN - SCOPUS:84867748695
VL - 51
SP - 435
EP - 441
JO - Applied Thermal Engineering
JF - Applied Thermal Engineering
SN - 1359-4311
IS - 1-2
ER -