Wall element instrumenting method for combustion chamber of e.g. jet engine, of aircraft, involves forming blind holes in wall element made up of ceramic matrix composite material, and introducing and fixing sensors in holes

摘要

The method involves forming blind holes (16) in a wall element (10) made up of ceramic matrix composite (CMC) material from its outer surface (18) by a pulsed yttrium aluminum garnet laser beam, by regulating the depth of the holes formed in the element from the number of laser pulses per hole. Sensors (14) are introduced and fixed in the blind holes. The sensors are connected to data processing and acquisition units. An independent claim is also included for wall elements of a combustion chamber of a turbine engine.