Abstract: A detection device for a turbine blade of an aircraft engine includes a machine table, a fixing frame, a dip coating mechanism, and a detection mechanism. A sliding cavity is formed in an upper end of the machine table, a support plate is slidably arranged in the sliding cavity, a side end of the support plate is rotatably connected to a chuck, the fixing frame is in an inverted “U” shape and is fixed on the upper end of the machine table, and a mounting barrel is rotatably arranged on the fixing frame. The dip coating mechanism and the detection mechanism are arranged on the machine table, such that wall-hanging sediments in an air film hole and a cooling channel will be exposed to a first photosensitive camera and a second photosensitive camera through fluorescent liquid, thus completing wall hanging and blockage detection of the blade synchronously.

Abstract: A detection device for a turbine blade of an aircraft engine includes a machine table, a fixing frame, a dip coating mechanism, and a detection mechanism. A sliding cavity is formed in an upper end of the machine table, a support plate is slidably arranged in the sliding cavity, a side end of the support plate is rotatably connected to a chuck, the fixing frame is in an inverted “U” shape and is fixed on the upper end of the machine table, and a mounting barrel is rotatably arranged on the fixing frame. The dip coating mechanism and the detection mechanism are arranged on the machine table, such that wall-hanging sediments in an air film hole and a cooling channel will be exposed to a first photosensitive camera and a second photosensitive camera through fluorescent liquid, thus completing wall hanging and blockage detection of the blade synchronously.