Device and method for testing trailing-edge delamination in composite gas turbine engine blades

A device for testing trailing-edge delamination of a typical composite engine blade component, comprising a foreign object impact launching subsystem, a typical blade component test rig, and a high-speed camera monitoring subsystem, wherein the typical blade component test rig comprises a tooling, a typical blade component fixture, and a floor-mounted adjustable slide rail;

• the tooling is connected to the floor-mounted adjustable slide rail;
• the typical blade component fixture is connected to the tooling;
• the foreign object impact launching subsystem is configured to launch bird projectiles;
• the typical blade component test rig is configured to fix a typical blade component, such that the typical blade component is subjected to impact by the bird projectiles;
• the high-speed camera monitoring subsystem is configured to monitor a bird projectile impact process and record bird projectile impact test data;
• the tooling is configured to fix the typical blade component fixture and position the typical blade component, ensuring stability of the typical blade component during the impact process;
• the typical blade component fixture is configured to fix the typical blade component and adjust a height and an angle of the typical blade component;
• the adjustable slide rail is an embedded lifting slide rail, configured to allow the tooling to be horizontally fixed on the floor or elevated above the floor and translated, thereby adjusting a height and an angle of the typical blade component to achieve adjustment of an impact height and an impact angle;
• the typical blade component fixture is a single-side clamping structure and comprises a front cover plate and a rear base plate, and the front cover plate and the rear base plate are both L-shaped;
• two columns of threaded holes are provided on the front cover plate in a vertical direction, wherein an upper threaded hole and a lower threaded hole in a right column of the threaded holes are configured to provide right-side clamping force of a clamping region;
• a row of slotted holes is provided at a bottom portion of the front cover plate in a horizontal direction, configured to fix the front cover plate to the tooling;
• two rows of threaded holes are provided on the rear base plate in a vertical direction, wherein a left column of the threaded holes is an embedded slotted hole, configured to connect with the front cover plate, to fix the typical blade component, and to provide left-side clamping force of a clamping region;
• and three rows of threaded holes are provided at a bottom portion of the rear base plate in a horizontal direction, configured to connect the tooling at fixed positions.