Abstract: An optical probe with high stability for measurement of radiation information of a turbine disk of an aeroengine includes a one-piece outer casing, a pressing ring, a sapphire window piece, an inner spacer, an outer spacer, a lens, first fixing nuts, second fixing nuts, fixing ropes and fixing screws. The one-piece outer casing is made from GH3044 solid solution strengthened nickel-based antioxidant alloy. An interior of the probe is divided into eight parts, which are as follows from a proximal hot end to a right end of the probe in sequence: a pressing ring chamber, a cold air vent, a sapphire window piece chamber, an outer spacer fixing chamber, a lens chamber, a beam chamber, a beam focusing chamber, and an optical fiber chamber.