TY - GEN
T1 - Film cooling performance on the trailing edge cutback of turbine blade with various slot inner angles
AU - Chen, Mingfeng
AU - Ling, Changming
AU - Zhang, Yuwen
N1 - Publisher Copyright:
© 2018 Association for Computing Machinery.
PY - 2018/1/8
Y1 - 2018/1/8
N2 - In order to study the impact of the slot inner angle on the film cooling performance of the trailing edge cutback for turbine blade, physical model and the three-dimensional mathematical model were established. The temperature distribution on the pressure side close to the wall was obtained through numerical simulation method, and the adiabatic temperature difference ratio and actual temperature difference ratio on the trailing edge cutback with various slot inner angles were analyzed. The results showed that, as slot inner angle increases, the average adiabatic temperature difference ratio on the trailing edge cutback and the effect of thermal insulation of gas film are increased. The impact of actual temperature difference ratio on the trailing edge cutback suffers slot inner angle is small, and it is conducive to lower the wall temperature of trailing edge when reduces the slot inner angle. For the study of film cooling performance on the trailing edge cutback of turbine blade, in addition to evaluate the adiabatic temperature difference ratio, it should also assess the actual temperature difference ratio.
AB - In order to study the impact of the slot inner angle on the film cooling performance of the trailing edge cutback for turbine blade, physical model and the three-dimensional mathematical model were established. The temperature distribution on the pressure side close to the wall was obtained through numerical simulation method, and the adiabatic temperature difference ratio and actual temperature difference ratio on the trailing edge cutback with various slot inner angles were analyzed. The results showed that, as slot inner angle increases, the average adiabatic temperature difference ratio on the trailing edge cutback and the effect of thermal insulation of gas film are increased. The impact of actual temperature difference ratio on the trailing edge cutback suffers slot inner angle is small, and it is conducive to lower the wall temperature of trailing edge when reduces the slot inner angle. For the study of film cooling performance on the trailing edge cutback of turbine blade, in addition to evaluate the adiabatic temperature difference ratio, it should also assess the actual temperature difference ratio.
KW - Film cooling
KW - Numerical simulation
KW - Slot inner angle
KW - Trailing edge cutback
KW - Turbine blade
UR - https://www.scopus.com/pages/publications/85049834361
U2 - 10.1145/3177457.3191706
DO - 10.1145/3177457.3191706
M3 - 会议稿件
AN - SCOPUS:85049834361
T3 - ACM International Conference Proceeding Series
SP - 192
EP - 196
BT - Proceedings of the 10th International Conference on Computer Modeling and Simulation, ICCMS 2018
PB - Association for Computing Machinery
T2 - 10th International Conference on Computer Modeling and Simulation, ICCMS 2018
Y2 - 8 January 2018 through 10 January 2018
ER -