Abstract: A method is provided for in situ inspection of a wear pad gap in a gas turbine engine combustor. The wear pad gap is defined between a wear pad of a transition piece impingement sleeve and a forward ring of a flow duct of the combustor. The method includes coupling a guide to the combustor such that the guide at least partially extends within a space between the impingement sleeve and a body of the transition piece, displacing an inspection head along the guide within the space between the impingement sleeve and the transition piece body such that the inspection head is positioned adjacent a wear pad, and inspecting the wear pad gap.

Abstract: An inspection system, in an exemplary embodiment, includes at least two base members spaced apart from each other, a support arm mounted to each base member, a linear track extending between and supported by the support arms, and a transport member coupled to the linear track. The transport member is movable along the linear track. The system further includes a transducer support arm pivotably coupled to the transport member, and a transducer assembly coupled to the transducer support arm.