TY - GEN
T1 - FLOW AND HEAT TRANSFER MECHANISM OF JET IMPINGEMENT COOLING ONTO MID-CHORD REGINE OF TWISTED BLADE
AU - Jin, W.
AU - Peng, S. E.
AU - Wu, J. M.
AU - Lei, J.
AU - Ji, W. T.
N1 - Publisher Copyright:
© 2021 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Jet impingement cooling is the most effective method to improve the local heat transfer coefficient. The paper numerically studied flow and heat transfer mechanism of impingement cooling onto the mid-chord region of the twisted blade with considering the thermal conductivity of the solid wall. Jet-to-jet spacing of the impingement holes are L/Di=8 and R/Di=6, jet-to-target spacing of the impingement holes is H/Di=0.8, and the diameter of the impingement holes (Di) is 0.001m. The inlet Reynolds number of mainstream is 167309, the inlet temperature of mainstream is 709K, and the pressure ratio (PT,c/PT,0) is 1.05-1.2. The results indicate that the thermal conductivity of the blade material significantly affect the temperature distribution on the blade wall. Impingement cooling significantly reduces the temperature of the suction surface of the blade, but makes the heat transfer effect of the pressure surface worse. And the stronger the transverse flow, the worse the impingement cooling effect. Besides, the curvature of the mid-chord region of the blade also affects the impingement cooling characteristics, and the higher the pressure ratio (PT,c/PT,0) is, the better the heat transfer effect is. Results of the study will provide some reference for the cooling design of real twisted blades.
AB - Jet impingement cooling is the most effective method to improve the local heat transfer coefficient. The paper numerically studied flow and heat transfer mechanism of impingement cooling onto the mid-chord region of the twisted blade with considering the thermal conductivity of the solid wall. Jet-to-jet spacing of the impingement holes are L/Di=8 and R/Di=6, jet-to-target spacing of the impingement holes is H/Di=0.8, and the diameter of the impingement holes (Di) is 0.001m. The inlet Reynolds number of mainstream is 167309, the inlet temperature of mainstream is 709K, and the pressure ratio (PT,c/PT,0) is 1.05-1.2. The results indicate that the thermal conductivity of the blade material significantly affect the temperature distribution on the blade wall. Impingement cooling significantly reduces the temperature of the suction surface of the blade, but makes the heat transfer effect of the pressure surface worse. And the stronger the transverse flow, the worse the impingement cooling effect. Besides, the curvature of the mid-chord region of the blade also affects the impingement cooling characteristics, and the higher the pressure ratio (PT,c/PT,0) is, the better the heat transfer effect is. Results of the study will provide some reference for the cooling design of real twisted blades.
KW - Flow heat transfer mechanism
KW - Jet impingement
KW - Mid-chord region
KW - Solid material
KW - Twisted blade
UR - https://www.scopus.com/pages/publications/85124459470
M3 - 会议稿件
AN - SCOPUS:85124459470
T3 - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
BT - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
PB - International Council of the Aeronautical Sciences
T2 - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
Y2 - 6 September 2021 through 10 September 2021
ER -