Patent ID: 7543500
Filing Date: 2009-06-09
Classification: G01N

Abstract:
1. A method for non-destructive testing of components of gas turbine engines made of monocrystalline materials for the presence of cracks in a certain, critical area of a component upon expiry of a specific operating time, comprising: generating a reference signal, in an installed state of the components in an engine, on a component-specific geometrical contour adjacent to the critical area by use of first longitudinal ultrasonic waves for fine-positioning and, upon availability of the reference signal, emitting second longitudinal ultrasonic waves positionally correct at a local distance from the first ultrasonic waves, corresponding to the location of the critical area to cover the critical area and produce a flaw signal in the event of a crack formation in the critical area, with the first and second ultrasonic waves being previously rough-positioned by use of an ultrasonic probe form-fitted to an outer contour of the components under camera-visual control.