The bladed disks in aircraft engines are subject to vibration during operation, excitations shorten their lifespan and raise the possibility of crack formation, both of which can result in catastrophic damages. The conventional method for vibration measurement on turbomachinery blades is to apply strain gauges on the blade surface. In recent years, a non-intrusive alternative technique for measuring blade vibration using a non-contact method has gained popularity. The Blade-Tip Timing (BTT) technique works based on the concept of time of arrival (TOA) of the blades passing in front of stationary sensors, placed on the casing around the blades. In absence of any structural vibration, the TOA would depend only on the rotational speed of the blade.