The turbojet which has the component, and this kind of component of the ceramic matrix composite material make which includes the hole and the said hole which can the laser by manner and the said manner which punch in the component of the ceramic matrix composite material make

摘要

The process for drilling holes in a ceramic matrix composite part e.g. combustion chamber wall or turbine blade of jet engine by a laser beam, comprises drilling an initial hole having an initial diameter and an axis (16) of hole by focussing the laser beam in a thickness of the part, drilling an intermediate hole coaxial with the initial hole by shifting the laser beam around the axis of hole, moving a focal point of the laser beam along the axis of the hole and activating the impulsions to obtain a final hole (30). The intermediate hole has a diameter higher than that of the initial hole. The process for drilling holes in a ceramic matrix composite part e.g. combustion chamber wall or turbine blade of jet engine by a laser beam, comprises drilling an initial hole having an initial diameter and an axis (16) of hole by focussing the laser beam in a thickness of the part, drilling an intermediate hole coaxial with the initial hole by shifting the laser beam around the axis of hole, moving a focal point of the laser beam along the axis of the hole and activating the impulsions to obtain a final hole (30). The intermediate hole has a diameter higher than that of the initial hole. The impulsions have a number of 1-5. The hole is oriented along an inclined axis of 30[deg] compared to a surface of the part.