TY - JOUR
T1 - Design and Experimental Study of Turbine Blade Cooling Structure for an Engine
AU - Jiang, Jintao
AU - Dong, Suyan
AU - Dong, Rongxiao
AU - Wang, Zhisheng
AU - Fu, Yi
AU - Liu, Penghui
AU - Fan, Wei
N1 - Publisher Copyright:
© 2025 by the authors.
PY - 2025/10
Y1 - 2025/10
N2 - To address issues such as leading-edge and trailing-edge ablation and cracking of turbine blades during operation in an engine, this study integrates the characteristics of additive manufacturing technology and utilizes a comprehensive simulation and design platform for turbine-cooled blades to design three schemes of film cooling structures. Numerical simulations were employed to optimize the blade cooling configurations, resulting in a finalized cooling structure scheme, which was then subjected to experimental evaluation of its cooling performance. An experimental platform for turbine blade cooling effectiveness was established, capable of simulating actual engine operating parameters. Based on this platform, experimental studies were conducted to investigate the effects of key parameters—including pressure ratio(β), temperature ratio(K), and flow ratio(B) on the cooling effectiveness and the dimensionless temperature distribution on the blade surface. Experimental results show that within the studied operating conditions, the β has a greater impact on the cooling effectiveness of the blade compared to variations in B and K. When the β = 1.2, the cooling effectiveness of the blade surface is 0.130, and when β = 1.6, the effectiveness increases to 0.176, representing a 35.38% improvement. Within the tested range, variations in flow ratio resulted in a 19.12% increase in cooling effectiveness, while changes in temperature ratio led to a 26.62% improvement.
AB - To address issues such as leading-edge and trailing-edge ablation and cracking of turbine blades during operation in an engine, this study integrates the characteristics of additive manufacturing technology and utilizes a comprehensive simulation and design platform for turbine-cooled blades to design three schemes of film cooling structures. Numerical simulations were employed to optimize the blade cooling configurations, resulting in a finalized cooling structure scheme, which was then subjected to experimental evaluation of its cooling performance. An experimental platform for turbine blade cooling effectiveness was established, capable of simulating actual engine operating parameters. Based on this platform, experimental studies were conducted to investigate the effects of key parameters—including pressure ratio(β), temperature ratio(K), and flow ratio(B) on the cooling effectiveness and the dimensionless temperature distribution on the blade surface. Experimental results show that within the studied operating conditions, the β has a greater impact on the cooling effectiveness of the blade compared to variations in B and K. When the β = 1.2, the cooling effectiveness of the blade surface is 0.130, and when β = 1.6, the effectiveness increases to 0.176, representing a 35.38% improvement. Within the tested range, variations in flow ratio resulted in a 19.12% increase in cooling effectiveness, while changes in temperature ratio led to a 26.62% improvement.
KW - additive manufacturing
KW - cooling efficiency
KW - cooling structure
KW - film cooling
KW - turbine blade
UR - https://www.scopus.com/pages/publications/105020161878
U2 - 10.3390/aerospace12100873
DO - 10.3390/aerospace12100873
M3 - 文章
AN - SCOPUS:105020161878
SN - 2226-4310
VL - 12
JO - Aerospace
JF - Aerospace
IS - 10
M1 - 873
ER -