System and Method for Cleaning a Gas Turbine Engine and Related Wash Stand

Abstract

A system for cleaning a gas turbine engine may generally include a wash stand having a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine. The nozzles may be configured to inject a cleaning fluid through an inlet of the fan casing of the engine as the fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the rotating fan blades and into a compressor inlet of the engine. Additionally, each nozzle may be oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades. The system may also include a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles.

1 . A system for cleaning a gas turbine engine, the gas turbine engine including a plurality of fan blades and a fan casing surrounding the plurality of fan blades, the system comprising:
 a wash stand, the wash stand comprising a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine, the plurality of fluid injection nozzles configured to inject a cleaning fluid through an inlet of the fan casing as the plurality of fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the plurality of rotating fan blades and into a compressor inlet of the gas turbine engine; and   a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles,   wherein each fluid injection nozzle is oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades.   
     
     
         2 . The system of  claim 1 , wherein each of the plurality of fan blades includes a leading edge and a trailing edge and defines a stagger angle between the leading and trailing edges, the stagger angle corresponding to a negative tangential angle defined relative to the rotational direction of the plurality of fan blades. 
     
     
         3 . The system of  claim 2 , wherein the negative tangential angle ranges from less than zero degrees to −60 degrees at a radial location at which the cleaning fluid is directed past the plurality of rotating fan blades. 
     
     
         4 . The system of  claim 1 , wherein the positive tangential angle ranges from greater than zero degrees to 60 degrees. 
     
     
         5 . The system of  claim 1 , wherein each fluid injection nozzle is oriented radially inwardly relative to a centerline of the gas turbine. 
     
     
         6 . The system of  claim 1 , wherein the cleaning fluid is supplied to the plurality of fluid injection nozzles at a pressure ranging from 60 psi to 900 psi. 
     
     
         7 . The system of  claim 1 , wherein at least one of a tangential orientation or a radial orientation of each of the plurality of fluid injection nozzles is adjustable relative to the base frame. 
     
     
         8 . The system of  claim 7 , wherein the at least one of the tangential orientation or the radial orientation of each of the plurality of fluid injection nozzles is configured to be adjusted based on a rotor speed at which the gas turbine engine is turning while the cleaning fluid is being injected through the inlet of the fan casing. 
     
     
         9 . The system of  claim 1 , wherein the plurality of fluid injection nozzles are coupled to the base frame so as to form an annular array of nozzles. 
     
     
         10 . The system of  claim 9 , wherein the plurality of fluid injection nozzles are coupled to the base frame via a ring-shaped nozzle manifold. 
     
     
         11 . The system of  claim 1 , wherein the plurality of fluid injection nozzles are configured to inject the cleaning fluid through the inlet of the fan casing as the gas turbine engine is being operated at a rotor speed that is equal to or greater than a rotor speed associated with at least one of a dry motoring speed, an idle speed or a partial throttle speed for the gas turbine engine. 
     
     
         12 . A method for cleaning a gas turbine engine, the gas turbine engine including a plurality of fan blades and a fan casing surrounding the plurality of fan blades, the method comprising:
 positioning a wash stand relative to the gas turbine engine, the wash stand including a plurality of fluid injection nozzles configured to be vertically supported at a location adjacent to the gas turbine engine;   operating the gas turbine engine such that the plurality of fan blades are rotated in a rotational direction about a centerline of the gas turbine engine; and   injecting a cleaning fluid from the plurality of fluid injection nozzles through an inlet of the fan casing as the plurality of fan blades are being rotated such that the cleaning fluid is directed past the plurality of rotating fan blades and into a compressor inlet of the gas turbine engine,   wherein each fluid injection nozzle is oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades.   
     
     
         13 . The method of  claim 12 , wherein each of the plurality of fan blades includes a leading edge and a trailing edge and defines a stagger angle between the leading and trailing edges, the stagger angle corresponding to a negative tangential angle defined relative to the rotational direction of the plurality of fan blades. 
     
     
         14 . The method of  claim 13 , wherein the negative tangential angle ranges from less than zero degrees to −60 degrees at a radial location at which the cleaning fluid is directed past the plurality of rotating fan blades. 
     
     
         15 . The method of  claim 12 , wherein the positive tangential angle ranges from greater than zero degrees to 60 degrees. 
     
     
         16 . The method of  claim 12 , wherein each fluid injection nozzle is oriented radially inwardly relative to the centerline of the gas turbine engine. 
     
     
         17 . The method of  claim 12 , further comprising supplying the cleaning fluid to the plurality of fluid injection nozzle from a fluid source, wherein the cleaning fluid is supplied to the plurality of fluid injection nozzles at a pressure ranging from 60 psi to 900 psi. 
     
     
         18 . The method of  claim 12 , wherein at least one of a tangential orientation or a radial orientation of each of the plurality of fluid injection nozzles is adjustable relative to the centerline of the gas turbine engine. 
     
     
         19 . The method of  claim 12 , wherein the wash stand further includes a base frame, the plurality of fluid injection nozzles being coupled to the base frame so as to form an annular array of nozzles, wherein positioning the wash stand relative to the gas turbine engine comprises positioning the wash stand relative to the gas turbine engine such that a centerline of the annular array of nozzles is aligned with the centerline of the gas turbine engine. 
     
     
         20 . The method of  claim 12 , wherein operating the gas turbine engine comprises operating the gas turbine engine at a rotor speed that is equal to or greater than a rotor speed associated with at least one of a dry motoring speed, an idle speed or a partial throttle speed for the gas turbine engine.