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Flow Resistance Characteristics of Rotary Ribbed Channels

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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.

Blade CoolingRibbed PassageRotationFlow Resistance Characteristics

Ru-quan You、Yun-teng Xu、Hai-wang Li

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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

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Beijing Nova ProgramNational Natural Science Foundation of ChinaAdvanced Aerodynamic Innovation WorkstationNational Science and Technology Major Project

2022048412952376042HKCX2022-01-07J2019-II-0022-0043

2024

10.16492/j.fjjs.2024.02.0008

风机技术
沈阳豉风机研究所（有限公司）

风机技术

影响因子：0.643
ISSN：1006-8155
年,卷(期)：2024.66(2)
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