In jet engines the blade resonant vibration amplitude is normally reduced by increasing the structural damping by using, for example, tip shrouds. These devices dissipate the energy generated at the contact surfaces between the relative motion and the friction force. Contact parameters, principally the friction coefficient and contact stiffness, are required to characterize the dynamics of shrouded blade system. Moreover, if at these contact surfaces severe wear occurs, a loss of interference takes place and the energy dissipated by the shroud decreases. Consequently the blade vibration amplitude increases and a catastrophic blade failure could take place. In this work a test rig for the contact parameter measurements and micro wear charact...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
In aircraft engines the blade resonant vibration amplitude is normally reduced by increasing the st...
The modelling of the friction interfaces has received much attention in recent years from the aerosp...
Bladed disk vibrations in turbomachinery can lead to failure due to High Cycle Fatigue. One way in w...
The fretting phenomena caused by small scale reciprocating motion. It causes failure through wear lo...
High cycle fatigue in blades is triggered by oscillating forces. Devices such as shrouds, that expl...
AbstractThis paper presents a novel test rig to study the effect of fretting wear and of the contact...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
High-cycle fatigue is one of the most frequent reasons of failure for turbomachinery and in early de...
Superalloy coatings of the CoMoCrSi family (e.g. Tribaloy® T800) are applied to mitigate wear effect...
In the blade/ disk contact of aero-engines, movements induced by the engine regime changes may lead ...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
In aircraft engines the blade resonant vibration amplitude is normally reduced by increasing the st...
The modelling of the friction interfaces has received much attention in recent years from the aerosp...
Bladed disk vibrations in turbomachinery can lead to failure due to High Cycle Fatigue. One way in w...
The fretting phenomena caused by small scale reciprocating motion. It causes failure through wear lo...
High cycle fatigue in blades is triggered by oscillating forces. Devices such as shrouds, that expl...
AbstractThis paper presents a novel test rig to study the effect of fretting wear and of the contact...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
High-cycle fatigue is one of the most frequent reasons of failure for turbomachinery and in early de...
Superalloy coatings of the CoMoCrSi family (e.g. Tribaloy® T800) are applied to mitigate wear effect...
In the blade/ disk contact of aero-engines, movements induced by the engine regime changes may lead ...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...
This paper investigates the effect of contact geometry, temperature and displacement amplitude on th...