Abstract: A method of inspecting a component in an assembled gas turbine engine includes inserting a boroscope and a conduit through an aperture in a casing of the engine. The conduit has an applicator tip. The boroscope and conduit are directed to the component to be inspected. A dye penetrant is supplied through the conduit to the applicator tip. The applicator tip is arranged to contact the surface of the component and dye penetrant is supplied onto the surface of the component from the applicator tip such that the dye penetrant enters any defects in the surface of the component. The applicator tip includes a porous and malleable member. Light is directed onto the component and the surface of the component is viewed through the boroscope to determine if any defects are present in the surface of the component.

Abstract: A method of inspecting a component in an assembled gas turbine engine includes inserting a boroscope and a conduit through an aperture in a casing of the engine. The conduit has an applicator tip. The boroscope and conduit are directed to the component to be inspected. A dye penetrant is supplied through the conduit to the applicator tip. The applicator tip is arranged to contact the surface of the component and dye penetrant is supplied onto the surface of the component from the applicator tip such that the dye penetrant enters any defects in the surface of the component. The applicator tip includes a porous and malleable member. Light is directed onto the component and the surface of the component is viewed through the boroscope to determine if any defects are present in the surface of the component.

Abstract: Single-crystal components of gas turbine engines, like turbine blades, are inspected in the installed state within the engine for cracking in certain critical areas using longitudinal ultrasonic waves. A first, rough orientation of the ultrasonic waves onto the critical area is accomplished under camera-visual control using an ultrasonic probe whose shape conforms to the respective component area and which, therefore, can be form-fitted to the component. For fine-positioning of the ultrasonic waves in the critical area, a reference signal is generated at a component-specific geometrical contour adjacent to the critical area by second ultrasonic waves emitted at a local distance to the first ultrasonic waves. The presence of this signal ensures the safe, disturbance-free detection of cracks in the critical blade area by means of longitudinal sonic waves. The invention includes an apparatus for the performance of the method.

Abstract: Single-crystal components of gas turbine engines, like turbine blades, are inspected in the installed state within the engine for cracking in certain critical areas using longitudinal ultrasonic waves. A first, rough orientation of the ultrasonic waves onto the critical area is accomplished under camera-visual control using an ultrasonic probe whose shape conforms to the respective component area and which, therefore, can be form-fitted to the component. For fine-positioning of the ultrasonic waves in the critical area, a reference signal is generated at a component-specific geometrical contour adjacent to the critical area by second ultrasonic waves emitted at a local distance to the first ultrasonic waves. The presence of this signal ensures the safe, disturbance-free detection of cracks in the critical blade area by means of longitudinal sonic waves. The invention includes an apparatus for the performance of the method.