A process of modifying a passage in a component is provided. The process includes inserting a first material into the passage; blocking at least one end of the passage; inserting an elongated member into the passage through the first material; heat treating the passage, the first material, and the elongated member to form a solid interior in component; and machining through the solid interior to form a modified passage in the component.

The valve device includes: a valve casing that includes a valve casing main body, in which an inlet flow path, an intermediate flow path, and an outlet flow path are formed, and a lid portion that closes an external opening portion formed in the valve casing main body; an intermediate valve seat portion that is detachable from the valve casing main body; a strainer that extends in a direction connecting the lid portion and the intermediate valve seat portion and is disposed between the lid portion and the intermediate valve seat portion; and an energizing member that is disposed between the strainer and the intermediate valve seat portion and is energized the intermediate valve seat portion toward the valve casing main body. The strainer is disposed with the energizing member pressed toward the valve casing main body.

A cleaning system for cleaning gas paths in an engine core of a gas turbine engine includes a source of an engine cleaning liquid, an engine cleaning mist forming unit, a delivery device, a pump, and a mist collecting arrangement. The forming unit vapourises the cleaning liquid to form a cleaning mist and delivers the mist into the engine core. The delivery device delivers the cleaning liquid to the forming unit. The pump draws the mist through the engine core to clean the gas paths within the engine core. The mist collecting arrangement includes a condensing chamber, collects the mist that has passed through the engine core, and condenses the collected mist in the condensing chamber. The pump is arranged between and interconnects a rear engine core exhaust nozzle of the engine core and the condensing chamber.

An assembly for manually rotating a rotor includes a housing enclosing a first shaft and a second shaft accessible through an exterior wall of the housing. The first shaft extends from a first end rotationally coupled to the rotor to a second end selectively engageable with the second shaft. The second shaft includes a thrust plate extending from and rotatable with the second shaft. A spring disposed between the thrust plate and the housing biases the second shaft towards the exterior wall of the housing.

A blade damage evaluation apparatus includes: a registration unit for design information of a turbine and maintenance information; an acquisition processor for detection data of sensors; a first discrimination processor for first facility states of the turbine at a plurality of past time points; a classification processor for classes C.sub.n of a plurality of first facility states; a first determination processor for first operating state values of the turbine; another registration unit for first damage rates at past time points; a setting processor of a characteristic function for each of the classes C.sub.n; a second discrimination processor for a second facility state of the turbine at the current time point; a second determination processor for a second operating state value of the turbine at the current time point; and an analyzer for a second damage rate at the current time point.

A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.

A system and method for predicting a remaining oil life of oil in a gearbox of an air turbine starter of a vehicle. The method includes generating a temperature data, generating an environmental data set by an environmental sensor, predicting a remaining oil life based on the temperature data set and the environmental data set and scheduling a maintenance event in response to the prediction of the remaining oil life.

A gas turbine engine system includes a compressor, gas turbine, and combustor including a plurality of late lean fuel injectors supplied with secondary fuel to its interior. The gas turbine engine system includes a wash system in communication with the late lean fuel injectors. The wash system includes a water source; water pump; anti-corrosion agent fluid source with an anti-corrosion agent including a amine corrosion inhibitor; anti-corrosion agent supply piping in fluid communication with the anti-corrosion agent fluid source; mixing chamber receiving water and anti-corrosion agent to produce an anti-corrosion mixture in fluid communication with the mixing chamber and the plurality of late lean fuel injectors. Fluid from the mixing chamber including the water, the anti-corrosion agent fluid source, or a mixture thereof is injected, while the gas turbine engine is off-line, into the combustor and at least one of the plurality of late lean fuel injectors.

The present invention relates to a method for characterizing a coating, in which method a mass and/or a volume of a basic body is/are measured prior to coating; a mass and a volume of the basic body with the applied coating are measured; for characterizing the coating, a density of the coating is determined from the volume and mass measurements; wherein the volume is optically measured.

A turbine nozzle assembly system includes a plurality of nozzle sets, where each nozzle set forms an annulus. The nozzles in each set include an inner endwall and an outer endwall that include joint openings to receive the respective endwall mount ends of an airfoil. The airfoils across the plurality of nozzle sets have an inner endwall mount end and an outer endwall mount end that are identical amongst the plurality of nozzle sets. A wing portion of the airfoil has a selected wing shape that is identical within the respective nozzle set but different amongst the plurality of nozzle sets. In this manner, the endwalls can be removed from an airfoil and replaced with an airfoil having a different wing shape that provides a different pairwise throat area. The system allows changing of a pairwise throat area for a nozzle set without replacing the entirety of each nozzle.