TY - JOUR
T1 - Numerical study of 3D heat transfer for turbine blade with air cooling
AU - Zhang, Li Fen
AU - Liu, Zhen Xia
AU - Lian, Xiao Chun
PY - 2007/8
Y1 - 2007/8
N2 - A coupled flow-thermal model was established for 3D heat transfer of turbine blade with air cooling. Radiation heat was added into the energy equation as a source of heat radiation. Using coupled flow-thermal model, 3-D conjugated heat transfer for turbine blade with air cooling was accomplished. And, heat radiation was solved with P-1 model. The different surface temperatures and temperature distributions of the blades with/without heat radiation was compared. The results show that, for high-temperature gas at 1600 K, heat radiation is a significant heat source. If radiation heat is considered, the surface temperature of the blade is improved greatly, leading to obvious difference of temperature distribution.
AB - A coupled flow-thermal model was established for 3D heat transfer of turbine blade with air cooling. Radiation heat was added into the energy equation as a source of heat radiation. Using coupled flow-thermal model, 3-D conjugated heat transfer for turbine blade with air cooling was accomplished. And, heat radiation was solved with P-1 model. The different surface temperatures and temperature distributions of the blades with/without heat radiation was compared. The results show that, for high-temperature gas at 1600 K, heat radiation is a significant heat source. If radiation heat is considered, the surface temperature of the blade is improved greatly, leading to obvious difference of temperature distribution.
KW - Aerospace propulsion system
KW - Conjugate heat transfer
KW - Coupled flow-thermal method
KW - Radiation
KW - Turbine blade with air cooling
UR - http://www.scopus.com/inward/record.url?scp=34548507237&partnerID=8YFLogxK
M3 - 文章
AN - SCOPUS:34548507237
SN - 1000-8055
VL - 22
SP - 1268
EP - 1272
JO - Hangkong Dongli Xuebao/Journal of Aerospace Power
JF - Hangkong Dongli Xuebao/Journal of Aerospace Power
IS - 8
ER -