According to an embodiment, a rotor blade cover section is integrated with the rotor blades at leading ends thereof. A plurality of sealing fins is disposed at the rotor blade cover section, the sealing fins forming a predetermined clearance relative to an inner peripheral portion of the nozzle outer ring. An annular solid particle trapping space is disposed at the inner peripheral portion of the nozzle outer ring, the solid particle trapping space communicating with an inlet of a steam leak and trapping solid particles that flow in with steam. In the sealing structure, the nozzle outer ring has a through hole through which the solid particles are to be discharged from the solid particle trapping space toward a downstream stage of the steam turbine.

A cooling option for a steam turbine is provided, wherein the steam turbine includes a high-pressure zone and a medium-pressure zone, wherein the saturated steam streaming out of the high-pressure zone is discharged via a saturated steam conduit to a first pressure chamber in a second flow channel of the medium-pressure zone and thus the possibility of the saturated steam causing damage by corrosion and erosion in the high-pressure zone is prevented.

A compressor assembly may include a compressor housing and a compressor impeller disposed within the compressor housing. The compressor housing may have an internal aerodynamic surface that defines a circumferentially extending volute, and the compressor impeller may have an external aerodynamic surface that faces toward at least a portion of the internal aerodynamic surface of the compressor housing. A nonstick coating may be formed on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller. The nonstick coating may prevent foreign material introduced into the compressor assembly from collecting on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller.

Components having an environmental barrier coating and a sintered layer overlying the environmental barrier coating, the sintered layer defining an outer surface having a lower surface roughness than the environmental barrier coating. The sintered layer is formed from a slurry applied to and then sintered on the environmental barrier coating. The sintered layer comprises a primary material, at least one sintering aid dissolved in the primary material, and optionally a secondary material. The sintering aid contains at least one doping composition. The primary material is a rare earth disilicate or a rare earth monosilicate and is doped with the doping composition so as to be either a doped rare earth disilicate or a doped rare earth monosilicate. The optional secondary material is a reaction product of the primary material and any of the sintering aid not dissolved in the primary material.

Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction piping and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods. An anti-corrosion mixture is selectively supplied as an aqueous solution to the compressor and/or the turbine sections of the gas turbine engine to coat the gas turbine engine components therein with a metal passivation coating which mitigates corrosion in the gas turbine engine.

An article may include a substrate and a coating system on the substrate. The coating system may include an environmental barrier coating (EBC) layer and a CMAS resistant layer on the EBC layer (e.g., as the top coat of the system). The CMAS layer includes a rare-earth (RE) monosilicate composition including a plurality of RE metal cations, wherein RE monosilicate composition is configured to react with CMAS to form a reaction product including a RE apatite phase with a RE.sub.2O.sub.3.SiO.sub.2 composition, wherein the RE of the RE.sub.2O.sub.3.SiO.sub.2 composition includes at least one of the plurality of RE metal cations of the RE monosilicate.

A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

A method of manufacturing a substrate (16) with a ceramic thermal barrier coating (28, 32). The interface between layers of the coating contains an engineered surface roughness (12, 24) to enhance the mechanical integrity of the bond there between. The surface roughness is formed in a surface of a mold (10,20) and is infused by a subsequently cast layer of material (16, 28). The substrate may be partially sintered (76) prior to application of the coating layer(s) and the coated substrate and coating layer(s) may be co-sintered to form a fully coherent strain-free interlayer.

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.

A method of forming a ceramic matrix composite component according to an exemplary embodiment of this disclosure, among other possible things includes laying up plies of ceramic reinforcement material with sacrificial plies to form a preform, infiltrating the preform with a ceramic matrix material, and machining away the sacrificial plies to reveal a surface profile of the ceramic matrix composite component. A preform for a ceramic matrix composite component is also disclosed.