摘要
The fretting damage of the dovetail joints between blades and disks in turbojet engines has significant effect on fatigue life of the joints.In order to improve the resistibility to of dovetail joints fretting damage,an effective method provided,which palliates the fretting wear of the joint.By modifying the shape of the local interface to adjust the distribution of the mechanical parameters.The numerical analysis of the joints with the Boundary Element Method indicates that for the modified joints the peak reaction on the interface drops greatly but the peak stress does not rise at both the contacting and non contacting interface in elastic bodies.Comparative experiments have been carried out.The results show that the fretting wear of the modified dovetail joints is palliated,especially at the root of contact surface.The fatigure life of the appropriately modified dovetail joints increases twice.
The fretting damage of the dovetail joints between blades and disks in turbojet engines has significant effect on fatigue life of the joints.In order to improve the resistibility to of dovetail joints fretting damage,an effective method provided,which palliates the fretting wear of the joint.By modifying the shape of the local interface to adjust the distribution of the mechanical parameters.The numerical analysis of the joints with the Boundary Element Method indicates that for the modified joints the peak reaction on the interface drops greatly but the peak stress does not rise at both the contacting and non contacting interface in elastic bodies.Comparative experiments have been carried out.The results show that the fretting wear of the modified dovetail joints is palliated,especially at the root of contact surface.The fatigure life of the appropriately modified dovetail joints increases twice.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1990年第4期347-348,共2页
Journal of Aerospace Power
