Abstract: A method of inspecting and recording inspection data of machine components, the method including selecting a machine component among a plurality of machine components for inspection; identifying predefined areas of the selected machine component for inspection; identifying a fixed set of conditions allowed to be reported for the select machine component; inspecting the predefined areas of the select machine component; and recording inspection data as continuous numerical values to quantify entry for subsequent querying over a chosen set of machine components.

Abstract: A method of inspecting and recording inspection data of machine components, the method including selecting a machine component among a plurality of machine components for inspection; identifying predefined areas of the selected machine component for inspection; identifying a fixed set of conditions allowed to be reported for the select machine component; inspecting the predefined areas of the select machine component; and recording inspection data as continuous numerical values to quantify entry for subsequent querying over a chosen set of machine components.

Abstract: The method for in situ inspection includes providing a pair of adjacent impingement sleeves forming part of a combustor. A robotic inspection tool carrying an inspection head is inserted through an opening in the outer casing of the gas turbine and manipulated to locate the inspection head between the adjacent impingement sleeves. After inspecting the exterior surface of an impingement sleeve, the inspection tool is withdrawn from the casing. Additionally, a transition piece body forming part of a combustor is inspected by securing a robotic manipulator to an open end of the combustion casing, locating an inspection head on an inspection arm of the manipulator and manipulating the arm to locate the inspection head to inspect interior wall portions of the transition body by displacing the head axially and radially toward wall portions of the transition body.

Abstract: Metallic cloth seals backed by stiff high temperature-resistant shims depend from a bracket for engagement in a slot of a transition piece for sealing between the transition piece and a first-stage nozzle. The high pressure acting on the shim forces the metallic cloth into engagement with the sealing surface in the slot. The lower edge of the shim is bent about, and overlies, the edge of the metallic cloth in a direction toward the sealing surface of the slot to choke any flow from the high pressure region past the seal. Elongated spline seals are also inserted into opposed registering slots of adjacent transition pieces. The spline seals comprise metallic cloth folded onto itself backed by elongated stiff high temperature-resistant shims having lateral edges overlying the lateral edges of the cloth material. The overlying edges prevent leakage flow about the spline seals from the high pressure to the low pressure regions.

Abstract: A robotic inspection system for gas turbine combustion components includes an exterior manipulator for visual inspection of the exterior surface of the impingement sleeve, an interior manipulator for visual inspection of the interior of the transition piece body and an annulus manipulator for inspecting the side weld seams of the transition piece body. The exterior manipulator includes an arcuate segment extending about the annular spaced impingement sleeves and a robotic subassembly including a linear rail and an upper arm and forearm mounting an inspection head pivotally coupled to one another for visual inspection of the top, bottom and side external surfaces of the impingement sleeve. The interior manipulator mounts to the open end of the combustion casing and includes an arm mounted for universal pivotal movement to the mount, actuators for pivoting the arm and motors for extending and rotating an inspection head about pan and tilt axes within the interior of the transition piece body.

Abstract: A combustion liner and cooling sleeve assembly for a turbine combustor includes a substantially cylindrical combustion liner; and a substantially cylindrical outer cooling sleeve surrounding at least an axial portion of the combustion liner; wherein the outer cooling sleeve is secured to the combustion liner by a weld at one end of the cooling sleeve at its aft end, with a predetermined radial gap therebetween, the gap determined by respective operating temperatures and thermal expansion coefficients.

Abstract: A turbine spline seal includes an elongated turbine seal member. The seal member has an elongated, imperforate, and manually-flexible first portion and a manually-rigid second portion lengthwise adjoining the first portion. The turbine assembly includes the turbine spline seal and also includes first and second turbine members. The first and second turbine members are spaced apart to define a fluid-path leakage gap therebetween, and the seal member is placed in the gap. Each lengthwise edge of the seal member engages a respective one of two opposing surface grooves of the first and second turbine members.