A collector for collecting wash liquid from an engine washing operation include a frame; a height adjustable and expandable droplet separator package connected to the frame, the droplet separator package to receive a flow of wash liquid entrained in an airstream emanating from an engine; a height adjustable and extendable chute with side walls and a scissor lift, the chute connected to the droplet separator package and extending at least partially under an engine to collect liquid exiting the engine; a collector tank connected to the frame to collect liquid from the droplet separator package and the chute; and a drainage pipe connecting at least one of the chute and the droplet separator to the collector tank.

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.

A centrifugal compressor includes: a rotational shaft; a main casing surrounding at least a part of the rotational shaft, the main casing having an inlet and an outlet separated from each other in an axial direction of the rotational shaft and an annular space surrounding a section of the rotational shaft at a side of the inlet and communicating with the inlet; at least one impeller disposed in a fixed state to the rotational shaft inside the main casing; a flow guide member disposed inside the annular space and extending along the axial direction of the rotational shaft; a plurality of injection holes disposed along the flow guide member and separated from one another along the axial direction of the rotational shaft; and a flow path which extends inside the annular space and through which a cleaning fluid to be supplied to the plurality of injection holes is capable of flowing.

The present disclosure is directed to a method for in-situ (e.g. on-wing) cleaning one or more components of a gas turbine engine. The method includes injecting a dry detergent into the gas turbine engine. Further, the dry detergent contains a plurality of detergent particles having varying particle sizes. More specifically, the plurality of detergent particles includes a first set of particles having a median particle diameter within a first micron range and a second set of particles having a median particle diameter within a second micron range. Further, a median of the second micron range is larger than a median of the first micron range. In addition, the method includes circulating the dry detergent through at least a portion of the gas turbine engine so as to clean the one or more components thereof.

A method for forming an in situ temporary barrier within a gas turbine engine is provided. The method can include installing a bladder within the gas turbine engine, wherein the bladder defines a bladder body, and inflating the bladder with an inflating fluid such that the bladder body forms a circumferential seal within the gas turbine engine. The bladder body can be positioned between a row of stator vanes and an annular array of rotating blades to form a circumferential seal therebetween. A second bladder may be positioned circumferentially within the gas turbine engine.

The present disclosure is directed to a system and method for in-situ (e.g. on-wing) cleaning of gas turbine engine components. The method includes injecting a dry cleaning medium into the gas turbine engine at one or more locations. The dry cleaning medium includes a plurality of abrasive microparticles. Thus, the method also includes circulating the dry cleaning medium through at least a portion of the gas turbine engine such that the abrasive microparticles abrade a surface of the one or more components so as to clean the surface.

A monitoring system that monitors a steam-using facility includes a temperature sensor that is a trap temperature sensor configured to detect a temperature of a steam trap provided in a steam discharge unit and/or a steam temperature sensor configured to detect a temperature of steam flowing into the steam trap and a pressure sensor configured to detect a pressure of steam flowing into the steam trap. The monitoring system determines that there is an occurrence of an abnormality or a sign of the abnormality in the steam trap when (i) a temperature detection value obtained by the temperature sensor and/or statistical temperature data obtained by performing statistical processing on the temperature detection value deviates from a predetermined criterion thereof and (ii) a pressure detection value obtained by the pressure sensor and/or statistical pressure data obtained by performing statistical processing on the pressure detection value deviates from a predetermined criterion thereof.

The invention relates to a method for pickling a turbomachine component (1), comprising the following steps: positioning the component in a closed chamber (2), injecting a gas mixture (3) into the chamber (2), the gas mixture (3) comprising a halogenated gas, heating the chamber (2), the method being characterised in that: the gas mixture further comprises dihydrogen, the heating step is carried out at a temperature higher than 1000° C. and the step of injecting the gas mixture (3) is carried out by circulating through the chamber (2) a flow of gas mixture (3) having a flow rate between 6 and 15 times the volume of the chamber (2) per hour.

A turbine engine fleet wash management system is configured to electronically communicate with a turbine engine system, a fleet management service, and a cleaning management service. The turbine engine fleet wash system causes a cleaning of a turbine engine to occur based on information received from the turbine engine system and other sources. The turbine engine fleet wash management system includes a cleaning schedule optimizer that generates a cleaning schedule based on engine health monitoring data, engine operation data, maintenance schedules for the turbine engine, and cleaning regimen data. The cleaning schedule optimizer estimates turbine engine performance improvements based on the selected cleaning regimen, and calculating an estimate of carbon credits earned based on the predicted improvement in turbine engine performance.

A system includes a fluid distribution system. The fluid distribution system includes a first water wash nozzle configured to spray a wash fluid into an intake flow received through a bell mouth of a compressor during operation of the compressor in a water wash mode. The first water wash nozzle includes a first inlet end coupled to the bell mouth of the compressor, a first tip disposed opposite the first inlet end, and a first body of the first water wash nozzle extending from the first inlet end to the first tip toward an axis of the compressor. The first water was nozzle further includes a first outlet disposed at the first tip and configured to spray a first portion of the wash fluid into the intake flow during operation of the compressor in the water wash mode and a second outlet disposed along the first body and configured to spray a second portion of the wash fluid into the intake flow during operation of the compressor in the water wash mode.