The present invention relates to an impingement cooling mechanism that ejects a cooling gas toward a cooling target (2) from a plurality of impingement holes (3b) formed in a facing member (3) that is disposed facing the cooling target (2). Blocking members (5) that block a crossflow (CF), which is a flow formed by the cooling gas after being ejected from the impingement holes (3b), are installed on at least the upstream side of the crossflow (CF) with respect to at least a portion of the impingement holes (3b). Turbulent flow promoting portions (6) are provided in the flow path (R) of the crossflow (CF) regulated by the blocking members (5).

A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

A reconfigurable maintenance apparatus includes a body configured to operate within a cavity. The body has a first shape in a first configuration and a second shape in a second configuration. The first configuration facilitates the body entering the cavity. The reconfigurable apparatus also includes at least one maintenance device operably coupled to the body. The second configuration facilitates the at least one maintenance device of the reconfigurable apparatus performing a maintenance operation.

The production method comprises the steps for producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then assembling the preform to the turbine engine part by diffusion brazing. The thermal amplitude of the main transformation peak (A1) of the brazing material used to make the preform must at least be twice that of each of the respective thermal amplitudes of the secondary transformation peaks (A2, A3) of this brazing material.

The present disclosure is directed to a system and method for preventing damage to one or more components of the gas turbine engine during a repair procedure. The method includes locating one or more gaps of one or more components of the gas turbine engine in the vicinity of the defect. Further, the method includes filling the one or more gaps with a filler material so as to prevent arcing over the gaps during repair. Thus, the method also includes applying an electrical discharge to the defect.

The present invention discloses a novel and improved method for repairing a shrouded blade and a reconditioned shrouded blade. More specifically, a way of measuring a set of previously-operated blades to determine their post-operation geometric characteristics is provided where an offset due to deformation of the hardface surfaces of the shroud is determined. The hardface surfaces of the shroud are rough-machined and blade-compatible material is added to the hardface surfaces. A first side hardface surface of the shroud is then machined to a desired dimension offset relative to an originally manufactured blade after which a second side hardface surface is machined such that the distance between the hardface surfaces satisfies the cross-shroud dimension, which is similar to that of an originally manufactured blade.

Methods for repairing gas turbine engine casings and repaired casings are provided. In this regard, a representative method for repairing a gas turbine engine casing includes: removing an annular portion of the engine casing; and attaching an annular replacement portion to the engine casing.

A Method for modifying a plurality of cooling holes of a turbine component includes disposing a recess-shaped modification in a recess of the component comprising a plurality of cooling hole outlets, wherein the recess-shaped modification is formed to substantially fill the recess and comprising a plurality of modified cooling holes passing there through. The method further includes aligning the plurality of modified cooling holes of the recess-shaped modification with the plurality of cooling hole outlets of the component, inserting at least one alignment pin into at least one of aligned pair of holes and hole outlets, bonding the recess-shaped modification disposed in the recess to the component, and removing the at least one alignment pin after bonding, wherein the plurality of modified cooling holes of the recess-shaped modification is fluidly connected with the plurality of cooling holes of the component.

The present application discloses a wind turbine blade having on the outer surface thereof a polyurethane-based coating including a polyurethane binder prepared from polyol(s) having an average functionality of ≧2.0 and <8.0; at least 50% (w/w) of the polyols have aliphatic polyester segments included therein and have a Mw of 300-3,000 g/mol; and polyisocyanate(s) having an average functionality of <3.0; at least 50% (w/w) of the polyisocyanate(s) are selected from: (i) polyisocyanates having aliphatic polyester segments included therein, and having a molecular weight of 500-3,000 g/mol and a functionality of ≧2.0 and <3.0; (ii) polyisocyanates of the allophanate type having a Mw of 250-2,000 g/mol and a functionality of ≧2.0 and <3.0; and (iii) polyisocyanates of the uretdion type having a Mw of 250-2,000 g/mol and a functionality of ≧2.0 and <3.0. The application also discloses corresponding coating compositions and a method for coating a substrate.

Methods for material build-up on a tip of a blade of a gas turbine engine are provided. The method can include inserting a material supply and an inflatable bladder between the tip and a shroud such that the material supply is exposed to the tip and the inflatable bladder is positioned between the material supply and a shroud, inflating the inflatable bladder to force contact between the material supply and the tip, and causing relative movement between the material supply and the tip. The relative movement, in combination with the radial biased contact between the material supply and the tip, creates heat through friction. As such, the relative movement can frictionally weld new material from the material supply onto the tip of the blade. For example, the heat created can be sufficient to melt the surface of the material supply to transfer material from the material supply to the tip.