Abstract: A method of joining a first work piece and a second workpiece. The first and second workpieces may be rotor wheels of a rotor for a turbomachine. At least one of the workpieces includes an oxide dispersion strengthened alloy material and the first and second work pieces may be joined by welding a cladding on at least one of the workpieces to the other of the workpieces, without welding a substrate of the at least one workpiece which includes an oxide dispersion strengthened alloy material.

Abstract: A method of joining a first work piece and a second workpiece. The first and second workpieces may be rotor wheels of a rotor for a turbomachine. At least one of the workpieces includes an oxide dispersion strengthened alloy material and the first and second work pieces may be joined by welding a cladding on at least one of the workpieces to the other of the workpieces, without welding a substrate of the at least one workpiece which includes an oxide dispersion strengthened alloy material.

Abstract: A chemical composition for selectively removing an aluminum-containing material from a substrate comprises an acid having a formula of HxAF6, a precursor thereof, and a mixture of said acid and said precursor; wherein A is selected from the group consisting of Si, Ge, Ti, Zr, Al, and Ga; and x is in a range from 1 to 6, inclusive. The chemical composition can comprise at least another acid selected from the group consisting of phosphoric acid, nitric acid, sulfuric acid, hydrochloric acid, hydrofluoric acid, hydrobromic acid, hydriodic acid, acetic acid, perchloric acid, phosphorous acid, phosphinic acid, alkyl sulfonic acids, mixtures thereof, and precursors thereof. The chemical composition can be used to remove aluminum seal strips selectively from the dovetail of a turbine-engine blade.

Abstract: A wear reduction kit for a combustion system of a gas turbine includes:a) a plurality of U-shaped inserts for use with a gas turbine transition piece having a peripheral end frame at one end thereof, the peripheral end frame having a continuous peripheral slot therein, open in a radially outward direction wherein the plurality of U-shaped inserts are adapted for insertion within the peripheral slot, and further wherein the U-shaped inserts are formed of material having a hardness greater than the end frame;b) at least a pair of guide block elements for use in securing a transition piece of a gas turbine combustor to a transition piece support, wherein each of the guide block elements is secured to the transition piece and adapted for engagement with cooperating guide finger elements secured to the support; and at least a pair of covers for the guide finger elements, and wherein the guide blocks are formed of material having a hardness greater than the finger element covers; andc) cooperating combustor flow sl