A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.

A method of cleaning a component within a turbine that includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component.

A wash system for a gas turbine engine includes a core turning assembly having a motor configured to be mechanically coupled to the gas turbine engine. The rotor of the core turning assembly is further configured to rotate one or more components of a compressor section or a turbine section of the gas turbine engine at a rotational speed greater than two (2) revolutions per minute and less than five hundred (500) revolutions per minute during washing operations of the gas turbine engine.

An aircraft engine includes an air inlet duct and at least one strut having a leading edge and a trailing edge. The at least one strut extends across at least part of the air inlet duct and has a strut passage. The trailing edge has one or more edge contours, each defining a contour edge wall recessed from a baseline surface of the trailing edge. The one or more edge contours have a recessed tap in fluid communication with the strut passage.

A method and system for cleaning a fuel nozzle during engine operation is provided. Operations include operating the compressor section to provide the flow of oxidizer at a first oxidizer flow condition to the combustion chamber, wherein the first oxidizer flow condition comprises an environmental parameter; operating the fuel system at a first fuel flow condition to produce a fuel-oxidizer ratio at the combustion chamber; comparing the environmental parameter to a first environmental parameter threshold; and transitioning the fuel system to a second fuel flow condition corresponding to a cleaning condition at the fuel nozzle if the environmental parameter is equal to or greater than the first environmental threshold.

A method for cleaning components of a gas turbine engine is presented. The method includes introducing a working fluid into a gas flow path or a cooling circuit defined by the one or more components of the gas turbine engine such that the working fluid impinges upon a surface of the one or more components of the gas turbine engine, wherein the working fluid includes a plurality of detergent droplets entrained in a flow of steam. A system for cleaning components of a gas turbine engine are also presented.

A method for cleaning a jet engine includes introducing a cleaning medium having solid materials into the engine by way of at least one discharging device, wherein the cleaning medium exits from the discharging device at an exit speed of 80 m/s or less.

Provided is a turbine, including: an accommodating portion configured to accommodate a turbine impeller; an exhaust flow passage configured to allow communication between the accommodating portion and an exhaust-air introduction port; a discharge flow passage configured to allow communication between the accommodating portion and an exhaust-air discharge port; a bypass flow passage configured to allow communication between the exhaust flow passage and the discharge flow passage while detouring the accommodating portion; and a branching portion between the exhaust flow passage and the bypass flow passage. The branching portion has a flow passage sectional area of 0.6 times or more a flow passage sectional area of the exhaust-air introduction port.

Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion section. The method includes receiving a pressurized fluid from a source and directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid. The method includes injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system upstream from a combustor plenum of the combustion section to clean the one or more cooling passages associated with the combustion chamber.

This steam turbine plant comprises: a boiler; a steam turbine; a condenser; a condensate pump; a main steam line that is capable of guiding, to the steam turbine, steam generated in the boiler; a bypass line that is branched from the main steam line and is connected to the condenser; a condensate line that is capable of guiding, to the condensate pump, water in the condenser; a condensate outlet valve that is provided in the condensate line; a water supply line that is capable of guiding, to the boiler, water having a pressure which has been increased in the condensate pump; a first connection unit that is, in the condensate line, branched from a position which is closer to the condenser than the condensate outlet valve is; and a second connection unit that is, in the condensate line, branched from a position which is closer to the condensate pump than the condensate outlet valve is. The first connection unit has a first connection seating that is connectable with a first line. The second connection unit has a second connection seating that is connectable with a second line.