An enhanced damping system for a turbine bucket. The damping system includes a damper pocket and a damper pin with an offset center of gravity positioned within the damper pocket.

A penetration system for a pipe entering a duct wall at a pipe stub. The penetration system may include a thermal sleeve surrounding the pipe stub and a bellows positioned below the thermal sleeve and about the pipe.

A secondary combustion system for a stage one turbine nozzle. The secondary combustion system may include a supply tube extending into the stage one nozzle, a number of injectors extending from the supply tube to an outer surface of the stage one nozzle, and an air gap surrounding each of the number of injectors.

A power converting apparatus and method providing for the addition of a fourth power connection wire to the neutral point of the normal three phase load circuit. This allows delivery of combined current from the center of the DC link voltage to load. The added control enables a third harmonic injection to flow and allows for increased power rating per peak amp handled by the conversion system. Limiting of faults to the positive half versus the negative half of the DC system allows for more robus…

A method of manufacturing a turbine blade includes (a) supporting a turbine blade internal core support at opposite ends such that radially inner and outer ends of the turbine blade remain open during casting; (b) casting the blade including the airfoil portion, wherein the radially outer edge of the airfoil portion is inclined relative to horizontal; (c) machining the radially outer edge of the airfoil portion to form a peripheral shoulder about a radially outer opening in the airfoil portion; …

Vapour turbine operating with geothermal vapours containing corrosive agents or aggressive substances such as chlorides and/or sulfides in particular. The turbine comprises a series of stator blades and a series of rotor blades, each stator blade of the series of stator blades comprises a surfacing consisting of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapours, at the same time maintaining a high useful life of the se…

A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable …

The present invention involves a process for increasing coolant side surface roughness on castings such as airfoils, shrouds, nozzles or the like by electrical discharge machining (EDM). An EDM electrode is shaped to fill completely or a portion of a cavity in the casting, the electrode is then connected to an electric discharge machine, and the internal surfaces of the internal core cavity are then machined to form a roughened surface.

A kit for setting turbine probe depth. The kit may include a male measurement fixture having an extended leg and an alignment barrel and a female measurement fixture having a depth rod.

A gas turbine engine system. The system includes a compressor with a first compressor stage and a second compressor stage, a turbine with a first turbine stage and a second turbine stage, a first flow path connecting the first compressor stage and the first turbine stage, a second flow path connecting the second compressor stage and the second turbine stage, a crossover flow path connecting the first flow path and the second flow path, and an ejector positioned about the crossover flow path and …