摘要
With the development of aero-engines, the turbine inlet temperature continues to rise. In order to ensure the safety and reliability of the turbine blades, cooling structures must be set inside turbine blades to cool them. Heat transfer coefficient and flow resistance are the key parameters to measure the cooling characteristics of internal cooling structures. In this paper, the characteristics of flow resistance in a rotating ribbed channel is presented numerical simulation under different rib spacings, rib angles, and thermal boundary conditions. The results show that, separation and reattachment of fluid between ribs is the key effect of rib spacing on flow resistance. The flow resistance is small when the rib spacing is small, because it's difficult for the fluid to form reattachment between the ribs. With the increase of rib spacing, the reattachment phenomenon is more obvious and the flow resistance increases accordingly. In general,p: e=10 channel has the maximum flow resistance. Secondary flow caused by the ribs is the key factor affecting the flow resistance characteristics with different rib angles. The secondary flow interacts with the main flow and causes flow loss through mixing, thus affecting the flow resistance of the channel. Under static condition, the flow resistance of 60°ribbed channel is the largest. The flow resistance of channel was affected by the temperature rise ratio also. And with the increase of the Ro, the temperature rise ratio has a more obvious effect on the flow resistance of the ribbed channel.When Ro=0.45, the flow resistance of the channel with a temperature rise ratio of 0.4 is 2.4 times that of the channel without temperature rise, while when Ro=0.3, it is 1.6 times, and when Ro=0.15, it is 1.2 times.
作者
由儒全
许云腾
李海旺
Ru-quan You;Yun-teng Xu;Hai-wang Li(National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics,Beihang University;Research Institute of Aero-Engine,Beihang University;Advanced Jet Propulsion Innovation Center,AEAC;Tianmushan Laboratory)
出处
《风机技术》
2024年第2期51-61,共11页
Chinese Journal of Turbomachinery
基金
Beijing Nova Program (No. 20220484129)
National Natural Science Foundation of China (No.52376042)
Advanced Aerodynamic Innovation Workstation (Grant No. HKCX2022-01-07)
National Science and Technology Major Project (Grant No. J2019-II-0022-0043)。
