A device for masking the inner periphery of a disc of a turbine engine generally includes a lower element, an upper element, and an elastic annular seal. The lower element, the upper element, and the elastic annular seal are coaxial, the elastic annular seal arranged longitudinally between the lower element and the upper element. The seal generally includes a lower annular part bearing radially and internally against the lower element, and an upper annular part bearing radially and internally against the upper element. The lower part and the upper part are connected to one another by an annular central part forming a return element. The elastic annular seal is configured to bear longitudinally, radially, and externally against each longitudinal end of said inner periphery of the disc to mask said inner periphery, and a clamping system capable of clamping the seal between the lower element and the upper element.

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 and apparatus for cleaning a vessel. The apparatus comprises a retractable assembly and a self-propelled cleaning carriage. The retractable assembly has a center section, a first segmented arm configured to extend in a first direction from the center section in an interior of a vessel, and a second segmented arm configured to extend in a second direction from the center section in the interior of the vessel. The second direction is opposite the first direction. The self-propelled cleaning carriage surrounds at least a portion of the retractable assembly. The self-propelled cleaning carriage is configured to move along at least one of the first segmented arm or the second segmented arm.

A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.

A system for on-wing engine washing and water reclamation is provided. The system has at least one spray device for introducing a cleaning liquid containing at least water into the engine while the engine is being operated, and an effluent trough for collecting the cleaning liquid from an exit end or underneath side of the engine. In a preferred embodiment, a source of the cleaning liquid and the effluent trough are located on a mobile unit. Further, a treatment system for treating the collected cleaning liquid is also located on a mobile unit.

Wands are used as parts of cleaning systems to conduct cleaning agents into gas turbine engine cores. Wands according to the present disclosure include inlet assemblies adapted to connect to cleaning agents, dispensers adapted to discharge cleaners into gas turbine engines, and conduits that extend from the inlet assemblies to the dispensers.

The centrifugal compressor is provided with a casing, a rotating shaft which is supported inside the casing, an impeller which is arranged on the rotating shaft and rotates to compress a fluid, and a washing liquid injection device which injects a washing liquid into a flow path formed by the impeller and the casing. The washing liquid injection device is provided with a plurality of nozzles which are arranged along a circumferential direction of the rotating shaft to inject the washing liquid into the flow path and a plurality of chambers which communicate with each corresponding nozzle among the plurality of nozzles and supply the washing liquid to the corresponding nozzle.

A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing.

A collection apparatus for collecting waste from cleaning operations performed on an aircraft turbine engine includes a frame structure, a support arm having a first end movably attached to the frame structure and an opposite second end, an actuator device adapted to enable raising and lowering the support arm, a waste storage tank, a duct having an inlet end and an opposite outlet end adapted to be removably connected to the waste storage tank, and a flexible duct portion having a flexible portion inlet end and a flexible portion outlet end. The inlet end of the duct is adjustably supported by the second end of the support arm. The flexible portion outlet end engages the inlet end of the duct in fluid communication, and is bendable both up/down and sideways and is expandable in length between the flexible portion inlet end and the flexible portion outlet end.

The present disclosure is directed to an auxiliary cleaning system for cleaning a gas turbine engine. The auxiliary cleaning system includes an external motoring source mechanically coupled to one or more engine shafts of the gas turbine engine. Thus, the external motoring source is configured to turn the one or more shafts. The auxiliary cleaning system also includes a cleaning apparatus configured to implement a cleaning procedure on the gas turbine engine while the external motoring source is turning the one or more shafts of the gas turbine engine.